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EXECUTIVE OFFICE OF THE PRESIDENT 

NATIONAL AERONAUTICS AND SPACE COUNCIL 

WASHINGTON, D. C. 20jo 2 

16 
TO THE CONGRESS OF THE UNITED STATES 

America's space and aeronautics programs made brilliant progress in 

1966. We developed our equipment and refined our knowledge to bring 

travel and exploration beyond earth's atmosphere measurably closer. 

And we played a major part in preparing for the peaceful use of outer 

space. 

In December the United Nations, following this country's lead, reached 

agreement on the Outer Space Treaty. 

ical significance for the new age of space exploration. 'I It bars weapons 

of mass destruction from space. 

celestial bodies. 

At that time I said it had "historIt restricts military activities on 

It guarantees access to all areas by all nations. 

GEMINI manned missions were completed with a final record of constructive and dramatic achievement. 

pilot hours in orbit. 

experiments. 

12 hours. 

Our astronauts spent more than 1,900 

They performed pioneering rendezvous and docking 

They "walked" in space outside their vehicles for about 

We orbited a total of 95 spacecraft around the earth and sent five others on 

escape flights, a record number of successful launches for the period. We 

launched weather satellites , communications satellites , and orbiting obs ervatories. We performed solar experiments and took hundreds of pictures of 

the moon from LUNAR ORBITERS. 

and then returned over 11, 000 pictures of its surroundings for scientific 

examination. 

SURVEYOR I landed gently on the moon 

Major progress was made during the year on the APOLLO-SATURN moon 

program and the MANNED ORBITING LABORATORY. 

These accomplishments -- and the promise of more to come -- are the fruits 

of the greatest concerted effort ever undertaken by any nation to advance human 

knowledge and activity. Space, so recently a mystery, now affects and benefits the lives of all Americans. 

Our national investment in space has stimulated the invention and manufacture of a flood of new products. 

secure as a Nation and more effective as leaders in the search for peace. 

This knowledge is hastening the ultimate solution of social and economic 

problems that combined to obstruct peace. 

Our new knowledge has made us more 

It is with pride and pleasure that I transmit this record of achievement to 

you the members of Congress. Without your support, no achievement 

would be possible. 

THE WHITE HOUSE 

January 31, 1967 
TABLE OF CONTENTS 

Chapter 

Chapter 

Chapter 

Chapter 

Chapter 

Chapter 

Chapter 

Chapter 

Chapter 

Chapter 

Chapter 

Chapter 

Chapter 

Chapter 

I 

I1 

I11 

IV 

V 

VI 

VI1 

VI11 

IX 

Appendix A-1 

Appendix A-2 

Appendix A-3 

Appendix B 

Appendix C 

Appendix D 

Appendix E 

Appendix F-1 

Appendix F-2 

Appendix F-3 

Index 

X 

XI 

XI1 

XI11 

XIV 

U . S . Aeronautics and Space Activities.. 

1965 Summary ................ 

National Aeronautics and Space Administration . 

Atomic Energy Commission ........... Department of State ............... National Science Foundation ........... Department of Commerce ............ National Academy of Sciences . 

Federal Research Council ........... Smithsonian Astrophysical Observatory ..... Federal Aviation Agency ............. Federal Communications Commission ...... United States Information Agency ........ Arms Control and Disarmament Agency ..... 

National Aeronautics and Space Council 

Department of Defense .............. 

..... 

U . S . Launching Record (Chart) ......... U.S. Launching Record (Table) ......... Successful U.S. Launches . 1966 ........ U . S . Space Launch Vehicles ........... Listing of Major Space "Firsts" Achieved 

by the U . S . and the U . S . S.R. ........ Historical Summary of Project GEMINI ..... SNAP Radioisotopic Electric Power 

Units for Space ............... Historical Summary and FY 1967 Budget 

Recommendations (New Obligational 

Authority ) .................. Historical Summary and FY 1967 Budget 

Recommendations (Expenditures) ...... Space Activities Budget ............ 

1 

7 

11 

53 

75 

81 

87 

91 

111 

119 

125 

133 

137 

143 

145 

146 

147 

161 

162 

164 

165 

166 

167 

168 

........................... 169 

. 
CHAPTER 

I 

U. S. AERONAUTICS AND 

SPACE ACTIVITIES 1966 

SUMMARY 

In 1966, the national space program of the United States reached new heights of 

accomplishment and excellence. 

its impressive record was surpassed by the competence generated in 1966. 

The challenge of the previous year was met and 

During this past year, we put into earth orbit or escape missions 100 spacecraft, 

the largest number ever successfully launched byany nation in an equal period of 

time; the GEMINI program was completed with a magnificent record; thousands of 

excellent pictures of the moon and the earth were taken from space; increasing space 

capabilities contributed to our national security; manifold benefits of our growing 

technology and managerial ability became increasingly evident; and international 

competition in space showed useful advances, particularly with the accomplishment 

of the United Nations Space Treaty. 

The national space program continued to produce benefits for all mankind, and the 

knowledge gained from the program has created great potential for the solution of 

serious economic and social problems on earth. 

The GEMINI program merits special mention. The crews of these spacecraft showed 

the advantages of native ability combined with superb training and reliable equipment. 

They added significantly to the knowledge essential to successful manned space flights 

and particularly to the scheduled manned flight to the moon. 

and docking experiments and extravehicular activity, the GEMINI pilots made major 

contributions. Moreover, great credit for this successful program should also go 

to the producers of the GEMINI spacecraft, the TITAN booster, the AGENA target 

vehicle, and other essential equipment. 

Through rendezvous 

1 
Even a summary report on the GEMINI program would be incomplete without special 

notice of the excellent teamwork between NASA and the Defense Department, as well 

as between agencies of Government and the private contractors. 

The APOLLO lunar craft made successful suborbital reentry tests leading to its 

first manned launch scheduled for 1967. 

is destined to travel, and on which its LUNAR EXCURSION MODULE will land, was 

photographed thousands of times in impressive detail by the soft-landing SURVEYOR I 

and by LUNAR ORBITERS I and II. 

new knowledge about the lunar environment and gave considerable information regarding possible landing sites for astronauts. 

And the goal toward which the APOLLO 

Such photographic acquisitions contributed much 

The moon was not all that was photographed from space, as numerous shots were 

taken of earth, furnishing added knowledge as well as dramatic pictures. 

Also sharing the spotlight of this nation's forward thrust of technology during 1966 

was the field of aeronautics. Significant strides were made toward increasing the 

safety of civilian transports. Progress was also made in improvements in existing 

aircraft as well as in the development of new aircraft. Probably the most important of the latter was in the field of the Supersonic Transport concerning which major 

studies and decisions were made. 

The United States continued to implement its policies of peaceful space objectives 

and of international cooperation toward the attainment of such objectives. Of major 

importance was the successful leadership shown by the United States and the 

cooperation of the Soviet Union in the development of a United Nations Space Treaty 

banning nuclear weapons in space and specifying the moon and other celestial bodies 

as being available only for peaceful activities. 

Important progress was made during the year in the development of the MANNED 

ORBITING LABORATORY, a project designed to evaluate the extent to which man in 

space can contribute to our national security. 

a means by which aggressive actions can be perpetuated, and it is in no way in 

conflict with the established peaceful policies of this nation. 

to improve the prospects for world peace. 

It is not a weapons system, it is not 

Rather, it is expected 

The United States operational weather satellite system continued to warn the world 

of major weather disturbances, and four more weather satellites were successfully 

orbited and operated for this purpose. More parts of the world were linked together 

with live television and other forms of communications as the United States, through 

the Communications Satellite Corporation, continued to orbit synchronous communications satellites in conjunction with the INTELSAT international consortium. 

Though the Soviet Union maintained its practice of putting more weight into orbit 

during a given year, the United States made significant progress in its program to 

develop large boosters, and the 58,537 pounds carried into space by an UpratedSATURN I during an APOLLO test may be a world's record for a single launch. 

Development flights of the TITAN IIIB and IIIC were continued with the use of new 

and improved upper stages. 

success, and the giant 7,500,000 pound thrust SATURN V is being readied for its 

first test early next year. 

T.he Uprated- SATURN I was used with complete 

2 
In spite of the impressive record developed by the United States, there is no basis 

for complacency as the $oviet Union was far from idle. Though they have made no 

manned launches into space for about 21 months, the vigorous nature of the Soviet 

program indicates that this hiatus could be attributed to the transition from one 

manned project to the next, and that new and significant manned space flights will 

be witnessed in the near future. The Soviets continued to concentrate on their lunar 

program during the year, and landed two picture-taking spacecraft on the lunar 

surface while orbiting two spacecraft around it. The Soviet Union also implemented 

their weather and communications satellite programs. The U. S. S. R. gave tangible 

evidence of the advantages they attribute to space progress by devoting a significantly 

larger percentage of their gross national product to space than we do. 

Among the many major accomplishments by the United States during 1966 were the 

following : 

1. The five successful flights completing the two-man GEMINI program produced 

a number of major achievements, such as the first docking and the first station 

keeping with another spacecraft by use of a tether line, a manned spacecraft altitude 

record of 851 miles, and useful activity of man outside orbiting spacecraft. 

2. The major studies were completed, and important decisions were made 

regarding the development and construction of a U. S. commercial supersonic 

transport (SST). 

3. 

continued, and twelve future astronauts were selected for the program. 

Development of the Department of Defense MANNED ORBITING LABORATORY 

4. A series of three unmanned flights of the APOLLO-SATURN I vehicle were 

successfully completed. The flights tested the heat shield during reentry conditions, 

the operation of the spacecraft systems under flight conditions, and testing of the 

Uprated 9 SATURN I second stage, which will be the third stage of the SATURN V. 

5. Significant progress was made in the testing and qualification of the threestage SATURN V for its initial launching in 1967. Problems which occurred in the 

second stage appear to have been solved. 

6. The TITAN IIIC underwent three flight tests during the year, launching 

seven military communications satellites and a gravity gradient experiment during 

the first test, and a modified GEMINI heat shield along with other experiments 

associated with the MANNED ORBITING LABORATORY during the third test. 

the second test flight the vehicle destroyed itself after the fairing failed. 

On 

7. SURVEYOR I landed gently on the moon and then returned over 11,000 

pictures of its surroundings. 

survived through several lunar day-night cycles. 

Its power supply and housekeeping electronic systems 

8. LUNAR ORBITERS I and 11 returned hundreds of useful pictures of potential 

APOLLO landing sites, pictures of the far side of the moon, and the first pictures 

of the entire visible face of the earth as seen from the vicinity of the moon. 

3 
9. The CENTAUR test program was successfully completed with the ninth and 

last ATLAS-CENTAUR test vehicle carrying a mass model of SURVEYOR to an 

imaginary rendezvous with the moon. 

10. 

the interplanetary medium between the orbit of earth and an orbit 12 million miles 

farther out. 

PIONEER 7 made a successful flight to measure radiation and particles in 

11. Tests of the nation's first NERVA nuclear-rocket engine (a "breadboard" 

engine which contained flight-type components but in a non-flight arrangement) 

demonstrated its high performance and stability over a wide range of operating 

conditions. 

12. The United Nations, following the lead of the United States, reached agreement on a "Treaty on Principles Governing the Activities of States in the Exploration 

and Use of Outer Space, including the Moon and Other Celestial Bodies. I' The 

treaty, which will be sent to the U. S. Senate for ratification, forbids the placing of 

weapons of mass destruction in outer space or on celestial bodies, restricts military 

activities on celestial bodies, and bars claims of sovereignty and national appropriation. 

13. The Air Force F-111A fighter-bomber flew for the first time at Mach 2.5. 

14. The U. S. operational weather satellite system continued to warn the 

world of impending storms and four more weather satellites were orbited for this 

purpose. 

15. A space thermoelectric generator was fueled for the first time with 

curium 242 and was successfully tested for 90 days under simulated lunar conditions. 

16. Improvements in the atomic clock have brought its accuracy to the equivalent of one second in 6,000 years. 

more accurate. 

Modifications are being made to make it even 

17. An ORBITING OBSERVATORY (OGO 111) was launched into earth orbit 

and continues to carry out its geophysical mission. 

18. 

boom tests. 

The XB-70 experimental aircraft was utilized for supersonic and sonic 

Its sister ship was destroyed as a result of a mid-air collision. 

19. PAGEOS I, a large sphere passive geodetic earth-orbiting satellite was 

launched into a near circular polar orbit, and simultaneous observation from 

41 portable camera stations around the world makes it possible to obtain more 

accurate measurements of distance between widely separated points on earth. 

20. 

atmosphere; the other to investigate possible radiation hazards to astronauts in 

deep space. 

Two more EXPLORER satellites were launched -- one to study the earth's 

21. The first Applications Technology Satellite (ATS) was placed in synchronous 

orbit to conduct communications, meteorological, and geophysical experiments. 

4 
22. MARINER IV (launched in 1964) transmitted data to earth as it passed 

behind the sun, marking the first time that radio-frequency energy had passed 

through the solar corona and been received by an earth-based station. 

23. Preliminary design of the Mars orbiting VOYAGER was completed. 

24. A BIOSATELLITE was launched on a three-day flight to investigate the 

effects of weightlessness, radiation, and other stresses of the space environment 

on the various life forms on board. 

being recovered, although telemetry developed some information. 

Difficulties prevented the spacecraft from 

25. The X-15 research aircraft continued to be used for a wide variety of 

aeronautical and space flight experiments, including flights with the large external 

tanks to be used later for Mach 8 speeds. 

26. Studies were completed on the feasibility of using V/STOL concepts for 

short haul commercial transports. 

27. Components of the 1.. 5 million pound thrust M-1 engine were successfully 

tested and yielded valuable data. 

28. The 260-inch diameter solid rocket motor was static tested, burning for 

about 2 minutes and developing a maximum thrust of over 3.5 million pounds. 

29. Two lifting body vehicles, the M-2 and the HL-10 were in the initial phases 

of their flight test program. 

30. The first SNAP 8 power conversion system was operated, achieving a 

35 KW electrical output. 

31. A single ion engine was endurance tested for over 8,000 hours, leading to 

the decision to prepare a second flight in the Space Electric Rocket Test program. 

32. Preparations were made for the PHOEBUS 1-B nnclear reactor tests. 

33. The nation's largest fully steerable antenna, a 210-foot diameter parabolic 

antenna, was added to the Deep Space Network. 

34. Through 1966, 72 countries had cooperated with the United States in space 

research. The following is indicative: 6 satellites launched for 4 countrie,& and 

9 other satellites under agreement for later launches; 19 countries entered ink 

agreements for cooperative sounding rocket programs; 4 experiments from 2 couatries flown and 14 other experiments selected for subsequent flights; and automatic 

picture transmission facilities in over 30 countries for receiving cloud-cover 

pictures from U. S. weather satellites. 

35. The U. S. launched a total of 100 payloads into earth orbit and on lunar 

and solar trips. 

5 
NATIONAL AERONAUTICS AND 

SPACE COUNCIL 

INTRODUCTION 

CHAPTER 

I1 

In accordance with established legislation and policy, the National Aeronautics and 

Space Council is responsible for advising and assisting the President in such matters as surveying and evaluating aeronautical and space activities of all departments 

and agencies engaging therein and in developing comprehensive programs for such 

activities, and in providing effective cooperation and coordination between the various agencies with aeronautical and space responsibilities. 

During 1966, under the leadership of the Vice President, the Council continued to 

carry out its responsibilities, with due attention to resolving difficulties and recommending actions for improved efficiency through both formal and informal contacts 

with policy-level representatives of Government agencies. 

BENEFITS 

Continuous study and public emphasis have been given to the multiple benefits to be 

derived from the national space program as well as from advancements in the field 

of aeronautics. These benefits comprise the returns from the taxpayers' investment in progress, all of which investment helps broaden our economic base and 

increase the size of our gross national product. In so doing, new and improved 

methods, techniques, and procedures are developed, which can increase the 

efficiency of much of the Nation's business. 

Benefits from our aerospace endeavors include positive contributions to our national 

security, inventions and improvements of products and services, enhancement of 

the quality of education, and progress toward the attainment of world peace. 

aspect of the peace role of the space program, its technological progress and 

contributions to higher standards of living reflect favorably throughout the world 

upon the nature and vitality of our economy. 

positively to the presentation of such an international picture of the United States. 

Moreover, it furnishes a constructive alternative to aggression and thereby gives 

a productive outlet for technological skills and the use of modern facilities. 

As an 

The space program contributes 

INFORMATION 

In addition to its being appropriate for the Federal Government to keep the public 

well informed regarding the advantages and developments in the aerospace field, 

it also is a reasonable responsibility for private companies and individuals with 

knowledge regarding aerospace benefits likewise to engage vigorously in such educational endeavor. 

7 
INTERNATIONAL COOPERATION 

International cooperation in the field of space is a policy with practical implications, 

not only for other countries, but also for the United States. 

capabilities can advisedly be used to provide coordinated and compatible services 

to the domestic economy in communications, in weather prediction, in navigation, 

and in observation. In addition to giving a major amount of attention to the practical aspects of international cooperation, with specific attention to improving 

cooperation with international organizations and with individual nations; continuing 

assistance and encouragement was given to the United Nations Space Treaty, from 

its initiation to its successful conclusion. 

Operational space 

FUTURE PLANS 

In addition to speeches, visits to space and aeronautical facilities, briefings, and 

informal coordination sessions, the Council held both formal and informal sessions 

on a variety of important aerospace issues. For example, meetings were held for 

the exchange of information and the evaluation of views regarding both the FY 1967 

and FY 1968 budgets on present and future space and aeronautical programs. 

Attention was given to all aspects of such programs, including operational defense 

satellites, plans for manned orbiting laboratories, nuclear rocket and space nuclear 

power projects, improved methods of propulsion, post-APOLLO proposals, and 

res ear ch and development in the field of aeronautics. 

Considerable attention was focused upon identifying various options that this country 

might pursue in space after the initial manned landing on the moon and upon how 

best to utilize the large investment this country already has in space capability -- 

in trained manpower, in specialized equipment, and in hard-earned invaluable 

experience. 

country is engaged in a technological competition and that only a leadership position 

can be justified. Leadership, however, can and should include increasing progress 

in international cooperation. 

Throughout all such evaluation, it was kept clearly in mind that this 

As for future space programs, consideration was given to the relative merits of 

large orbiting space stations, extended lunar exploration, manned and unmanned 

planetary exploration, space science needs for the coming years, and direct 

practical applications of space competence to communications, observation, 

navigation, and weather. 

to be alternatives necessarily as various constructive activities can and should 

be carried on concurrently. 

priorities, emphasis, and timing. 

These various plans and projects were not considered 

Rather, careful thought was given to questions of 

Throughout all of the program evaluations, the Council members were urged to 

keep in mind the many demands for funds which the President has to consider and 

therefore to stress those projects and proposals which seemed the most urgent and 

which promised the greatest returns on the investment. 

major projects was also examined and conclusions indicated that postponements or 

slowdowns may increase total costs and lessen total returns. 

The impact of delays on 

8 
AERONAUTICS 

Mindful of the aeronautical aspects of its responsibilities, the Council and the 

Council staff maintained continuing interest in the Supersonic Transport program 

as well as in what might be done to accelerate solutions to such problems as air 

safety and traffic control and aircraft noise and sonic boom. 

tion of such issues, it was emphasized that future airline growth, in both passenger 

traffic and freight cargo, will increase at a very rapid rate during the next decade. 

Those agencies with aeronautical responsibilities were urged to give special attention to see if enough was being done to solve civilian airline problems and whether 

current resources were effectively distributed to such end. 

During the examinaSOVIET SPACE PROGRAM 

The United States continues to lead the space technology competition in number and 

variety of successful missions, but the USSR maintains its lead in weight of payloads 

orbited. Both countries give substantial promise of more complex and challenging 

projects for the near future. 

during 1966 is no basis for complacency on our part as their preparations for future 

flights appear to be ambitious and the resources being devoted to space competence 

and performance are absolutely and relatively impressive. 

Certainly the hiatus in Soviet manned space activity 

SUMMARY 

In addition to the various sessions held, the Council directly and through its staff 

engaged in a broad range of policy, coordinating, and informational activities. 

Among these were: 

a. 

b. 

C. 

d. 

e. 

f. 

g* 

Supervised and edited the President's Annual Report to the Congress 

on Aeronautics and Space Activities for 1966. 

Submitted regular reports to the President on significant space 

activities and plans. 

Increased public understanding of the national space program through 

numerous speeches, articles, correspondence, and other public contacts. 

Participated in analysis of and made recommendations concerning the 

FY 1968 budgets for space and aeronautics. 

kamined the problems and alternative solutions regarding the 

implementation and development of space res cue capabilities. 

Continued to coordinate for the President the issues and decisions 

involved in the launching of nuclear power units in spacecraft. 

Participated in the development of policy recommendations relative to 

the growth of communication satellite systems and the export of 

related technology. 

9 
h. Examined the status and potential of navigational satellite utilization. 

i. 

j. 

k. 

1. 

m. 

n. 

0. 

P. 

9. 

r. 

Surveyed the development of on-board space power supply alternatives. 

Furnished briefing materials, including space photographs, for appropriate 

use in connection with visits to Washington of high officials of other nations. 

Participated in the planning for aeronautical and space exhibits abroad. 

Examined need for legislative changes affecting space and aeronautics. 

Maintained liaison with the technological and aerospace management 

communities . 

Contributed to the planning for foreign visits of U. S. astronauts. 

Reviewed the status of meteorological satellite projects. 

Visited space installations, examined facilities, and engaged in inter - 

agency as well as Government-industry meetings and briefings on new 

developments in aeronautics, space technology, and space benefits. 

Analyzed the impact of our national space program at home and abroad. 

Maintained a current record of U. S. and Soviet space launches, 

developed comparisons between U. S. and USSR space activities, and 

reviewed space accomplishments and potentials of other nations. 

10 
NATIONAL AERONAUTICS AND 

SPACE ADM I Nl S TR AT IO N 

CHAPTER 

I11 

INTRODUCTION 

Nineteen sixty-six was a year of continued accomplishment for the National 

Aeronautics and Space Admini stration. 

Five successful GEMINI flights, which demonstrated our capability for extravehicular activity, rendezvous and docking, station keeping, and orbital plane 

changes, brought this phase of the manned space flight program to a close. 

test flights in the APOLLO SATURN series were also completed with satisfactory 

results . 

Three 

Space sciences and applications programs made significant contributions to our 

knowledge of the moon, the sun, and interplanetary space. Two LUNAR ORBITER 

spacecraft sent back a remarkable series of pictures of the lunar surface, and 

SURVEYOR L soft landed on the moon and televised pictures of its surroundings to 

earth. The two types of views of the potential landing sites for manned spacecraft 

have given scientists unprecedented information about the nature of the surface of 

the moon and the lunar environment. 

0 RBITING ASTRONOMICAL OBSERVATORY, APPLI CATIONS TECHNO LOGY 

SATELLITE, and BIOSATELLITE programs. 

In addition, launches were made in the 

Advanced research and technology programs continued to provide the new technology 

to support aeronautics and space research. 

were used for a broad spectrum of aeronautical and space flight experiments; 

extensive investigations were made on problems relating to vertical and short takeoff and landing aircraft; and the XB-70 was assigned to collect data on sonic boom 

for the National Supersonic Transport program. A 260-inch solid motor developed 

over 3.5 million pounds of thrust in a successful 2-minute test firing early in 

the year. 

The three X-15 research airplanes 

In the nuclear power generation program, the first power conversion system 

(breadboard) began operating, and components and subassemblies of the SNAP-27 

generator were being delivered. Also, two major tests, associated with the 

NERVA reactor and engine system efforts, were conducted, and work was continuing on the facilities for testing of ground experimental engines. 

Other NASA programs continued to provide the support necessary to advance the 

Agency's major activities. 

11 
MANNED SPACE FLIGHT 

NASA's manned space flight program overcame a succession of problems and 

achieved its most significant successes during the year. These achievements 

included the final five manned GEMINl missions and the first three APOLLO unmanned missions. Additionally, the Agency made very substantial progress in providing 

the broad-based national capability for future manned space flights. This capability 

will be effectively demonstrated through the lunar mission planned for the 1968-69 

time period. 

GEMINI Program 

Five manned missions brought the GEMINI program to a successful completion in 

1966. All program objectives were accomplished. 

The acceleration of the GEMINI schedule, begun in 1965, permitted completion two 

months earlier than planned. 

Altogether, 10 two-man missions were conducted. The astronauts returned safely 

each time. 

including about 12 hours of activity outside the GEMINI space craft. 

The program provided 1940 man-hours of space flight experience, 

Participating in GEMINI were more than 25, 000 people of the industry and universities, including 50 major contractors, more than 150 subcontractors, and numerous 

vendors and suppliers. Within the government, the program was supported by the 

Departments of Defense; State; Health, Education and Welfare; and Commerce, as 

well as the Atomic Energy Commission. 

the Space Systems Division of the Air Force Systems Command, the National Range 

Division of the Air Force, and the recovery forces of the Navy. Tracking and other 

types of support were provided by six foreign countries--United Kingdom, Australia, 

Malagasy, Mexico, Nigeria and Spain. 

Department of Defense participants included 

The principal objectives of GEMINI were to gain experience in long duration flight, 

in rendezvous and docking, in the use of the docked vehicles to pioneer new 

frontiers of flight, in extravehicular activity, in controlled reentry from orbit, and 

in the conduct of experiments. 

GEMINI long-duration flights were completed in December 1965, when Astronauts 

Frank Borman and James A. Lovell, Jr. carried out the GEMINI 7 mission lasting 13 days, 18 hours and 35 minutes--almost twice the duration of a flight to the 

moon and back. 

Rendezvous was accomplished on all five GEMINI missions of 1966 and docking on 

four of the five. Different means of achieving rendezvous were employed on each 

flight to amass a body of knowledge about such maneuvers. 

Astronauts Neil A. Armstrong and David R. Scott performed the first docking in 

space when they joined their spacecraft with the AGENA target in the GEMINI 8 

mission on March 16, 1966. Also successful in docking with the AGENA were 

Astronauts John W. Young and Michael Collins on GEMINI 10, July 18; Charles 

Conrad, Jr. and Richard F. Gordon on GEMINI 11, September 12; and Love11 and 

Edwin E. Aldrin on GEMINI 12, November 11. On the GEMINI 9 -A mission, 

12 
June 3, Astronauts Thomas P. Stafford and Eugene Cernan performed rendezvous 

with their Augmented Target Docking Adapter but were unable to dock because a 

protective shroud had failed to separate from the vehicle as planned. 

The most advanced of the five 1966 rendezvous maneuvers was on GEMINI 11, when 

Conrad and Gordon joined with the AGENA target vehicle on the first revolution of 

the earth, one hour and 34 minutes after liftoff. 

A noteworthy event of 1966 was the space emergency that occurred during the 

GEMINI 8 mission. Twenty-seven minutes after Armstrong and Scott confirmed 

the docking, the spacecraft/AGENA combination encountered unexpected roll and 

yaw motion. They reduced the rates sufficiently to undock from the AGENA, and 

began trouble-shooting to determine the cause of the problem. 

the unexpected roll rates increased to a peak of about 50 revolutions per minute. 

Subsequently, the crew activated and used the Reentry Control System to stop the 

motion. 

During this activity, 

In accordance with previously developed rules, it was decided to terminate the 

mission during the seventh revolution, after 10 hours and 42 minutes of a scheduled 

three-day mission. 

to the Atlantic Ocean. 

recovery was made by the USS Mason, three hours and 14 minutes later. 

analysis showed that the problem resulted from a short-circuit in the electrical 

wiring of a thruster of the GEMINI spacecraft. 

The spacecraft was returned to the Western Pacific instead of 

Aircraft stationed in the area observed the touchdown and 

Data 

Of the 16 United States manned space flight missions, GEMINI 8 was the only one 

to experience an emergency significant enough to cause the mission to be terminated 

earlier than planned. 

combined with the satisfactory accomplishment of plans on other missions, illus - 

trates the value of the comprehensive testing, mission preparations, and contingency 

planning that have characterized the MERCURY and GEMINI programs. 

The success of the efforts to overcome this emergency, 

On two GEMINI missions of 1966, U. S. astronauts employed the AGENA as a 

propulsion unit to fly higher and faster than man had ever flown before. 

GEMINI 10, Young and Collins reached a speed of 17,700 statute miles an hour and 

an altitude of 475 miles. 

17, 943 miles an hour and an altitude of 851 miles. 

On 

On GEMINI 11, Conrad and Gordon achieved a speed of 

Four astronauts ventured outside their GEMINI spacecraft during 1966, bringing to 

five the number of Americans who have engaged in such activity. 

encountered on the first three 1966 flights. Cernan on GEMINI 9-A and Gordon on 

GEMINI 11 had difficulties with extravehicular tasks. 

GEMINI 10 ran short of spacecraft fuel. 

vehicular activity is somewhat more difficult than had been anticipated by some. 

On the GEMINI 12 mission, Aldrin employed body tethers and other hand and foot 

holds. 

with electrical and fluid connectors, hook-and-ring combinations, plastic strips, 

and fixed and removable bolts. 

in his cockpit and once attached with a tether--for a total of five hours and 37 

minutes, and accomplished all extravehicular objectives. 

responses were good throughout. 

Problems were 

EVA was curtailed when 

These problems indicated that extraHe obtained a quantity of baseline data, through performance of basic tasks 

He was in space on three occasions--twice standing 

His physiological 

13 
Except for GEMINI 8, which landed within a few miles of the contingency area, all 

1966 GEMINI missions returned to earth within a few miles of the center of the 

primary recovery area and were visible from the carrier. 

missions, reentry was performed under the manual control of the astronauts. 

GEMINI 11 and 12, control was automatically performed through the spacecraft 

computer after initiation by the astronauts. 

communications satellite, carrier recovery operations were seen by television 

viewers in the United States and elsewhere. 

On the year's first three 

On 

Through the use of the EARLY BIRD 

Numerous scientific, technological and operational experiments were performed on 

the GEMINI missions, demonstrating the utility of man as an experimenter in space. 

One of the most significant took place on the GEMINI 12 mission on November 12, 

when Love11 and Aldrin photographed a total eclipse of the sun as they approached 

the west coast of South America. 

Results of medical experiments performed during the 1966 missions indicated that 

man can perform satisfactorily and without ill effect on all of the operations 

conducted. 

APOLLO Program 

Substantial progress was made in the APOLLO program during 1966. Despite 

problems in testing and qualification of some of the flight hardware, the overall 

program continued on its schedule leading to the manned lunar landing and safe 

return before the decade is out. 

for achievement and a demonstration of broad-based national capability in manned 

space flight, which is the program objective. 

The APOLLO mission milestones serve as a focus 

The first major flight phase -- the all-systems-up unmanned flight testing of the 

command and service modules of the spacecraft and the uprated SATURN I launch 

vehicle -- was completed according to plan. Preparations neared completion for 

the beginning of APOLLO-uprated SATURN I manned flights. Arrangements were 

well advanced for the beginning of unmanned flights of the runar module and of the 

APOLLO-SATURN V, the vehicle that will be employed on the lunar missions. 

A schedule of seven major phases was established for the APOLLO flight operitions 

The first phase was that of unmanned flights of the APOLLO-uprated SATURN I 

vehicle, previously called SATURN IB, completed in 1966. Other phases and their 

scheduled dates are as follows: 

Manned APOLLO-uprated SATURN I flights (Block I 

Command and Service Modules) 

Unmanned Lunar Module-SATURN I flights 

Manned dual missions (Block 11 Command and 

Service Modules, Lunar Module) both launched 

by an uprated SATURN I 

Unmanned APOLLO-SATURN V flights, all 

systems up 

1967 

1967 

1967 or 1968 

1967 

14 
Manned APOLLO-SATURN V flights, simulating 

lunar mission in earth orbit 1968 

Manned missions, open ended, with equipment 

capable of lunar mission 1969 

APOLLO-uprated SATURN I -- A series of three unmanned flights was completed 

successfully in the qualification of the APOLLO-uprated SATURN I vehicle for three - 

man earth-orbital flights of the command and service modules. 

Two of the three flights carried the spacecraft on suborbital trajectories to certify 

the structural integrity and compatibility of the launch vehicle and spacecraft, the 

operation of spacecraft systems under flight conditions and the performance of the 

heat shield during entry to the atmosphere. 

uprated SATURN I second stage--which is the same as the third stage of the SATURN 

V-- to verify system performance and operation and to provide information on the 

behavior and management of its fuel, liquid hydrogen, in earth orbit. This latter 

information was needed because the lunar mission calls for a restart of the SATURN V 

third stage following a coasting phase in earth orbit. Following is a listing of the 

three flights and their highlights. 

The other was an orbital test of the 

APOLLO RESULTS 1966 

Mission - Date Mission Highlights 

AS -20 1 February 26 

AS -20 3 

AS-202 

July 5 

August 25 

Suborbital flight from Cape Kennedy to 

South Atlantic; unmanned; demonstrated 

compatibility and structural integrity of 

launch vehicle -space craft combination, 

evaluated heat shield performance; at high 

heat rate entry, spacecraft recovered. 

Second stage (S-IVB) of uprated SATURN I 

placed in orbit for evaluation of separation 

from instrument unit, storage of liquid 

hydrogen and liquid oxygen at zero gravity, 

vent and restart capability; pressure and 

structural test conducted to destruction on 

fourth orbit. 

Flight from Cape Kennedy to Western 

Pacific; unmanned; test of Command and 

Service Module subsystems and space 

vehicle structural integrity and compatibility; evaluated heat shield performance at 

high heat lead entry; spacecraft recovered. 

The thrust of the H-1 engine employed in the uprated SATURN I first stage was 

uprated to 205,000, thus increasing the total thrust of the eight-engine stage from 

1,600,000 to 1,640,000 pounds. 

the second-stage J-2 engine was increased from 225,000 to 230,000 pounds and its 

requalification was completed. 

Engine qualification was completed. The thrust of 

15 
Comprehensive ground tests were completed in qualifying the APOLLO-uprated 

SATURN I vehicle for manned flight. 

test of a ground-test spacecraft under simulated space conditions in the thermalvacuum chamber at the Manned Spacecraft Center, Houston, Texas. 

A major milestone was the successful manned 

The principal problem in qualifying this vehicle resulted from the discovery that the 

titanium material of the Service Module fuel tanks was weakened when exposed under 

pressure to anhydrous methyl alcohol, a fluid employed to test their ability to withstand high pressure. Replacement was made of all tanks exposed to methyl alcohol 

and distilled water was substituted for pressure tests. 

At year's end, checkout was in progress at Cape Kennedy on the vehicle for the first 

manned flight, designated APOLLCLuprated SATURN 204 (AS-204). 

hicle was erected at Launch Complex 34 and the spacecraft was undergoing final 

tests prior to placement atop the launch vehicle. 

was a series of manned runs in the Kennedy Space Center vacuum chamber. 

The launch veA principal phase of these tests 

During the first vacuum chamber tests in October, difficulties were encountered 

with the spacecraft Environmental Control Unit. Among the problems were those in 

the operation of a water boiler, impaired by the clogging of a porous distribution 

plate, and the failure of an oxygen regulator because of improper valve design. The 

faulty equipment was replaced, and an extended qualification program was instituted 

to substantiate the adequacy of design and manufacturing changes. 

For the first mission, the trajectory was established, the flight and experiments 

plan was completed, and the Mission Control Center-Houston was reconfigured for 

APOLLO. The assigned astronauts are Virgil I. Grissom, Edward H. White 111, and 

Roger B. Chaffee. The backup crew consists of Walter M. Schirra, Jr., Donn F. 

Eisele and Walter Cunningham. The mission is planned as open ended, up to 14 days 

in duration. 

LUNAR MODULE -- The peak effort was reached in the testing and qualification 

of the LUNAR MODULE--the two-stage, two-manned spacecraft that will descend 

from lunar orbit to the moon and then return to rendezvous and dock with the 

COMMAND and SERVICE MODULES in lunar orbit. The LUNAR MODULE is the 

first manned spacecraft designed to operate exclusively outside the earth's atmosphere. The first unmanned flight of this vehicle, designated APOLLO-SATURN 206 

(AS-206), is planned to follow the AS-204 mission. 

Problems in the development of the LUNAR MODULE have focused on its overall 

weight, the performance of its ascent and descent engines, and the sensitivity of its 

titanium tanks to the liquid oxidizer , nitrogen tetroxide. 

A program was conducted to exercise tight control of the LUNAR MODULE weight, 

resulting in a reduction well below the control weight. 

to accommodate nominal increases if necessary or to load additional propellant for 

mission flexibility. 

This now permits the vehicle 

Qualification of design was completed for the descent engine to be employed in the 

first two flights and engines were manufactured in accordance with an improved design for later flights. Modifications of the ascent engine injector design were completed during the year and found satisfactory. Testing of ascent and descent engines 

16 
proceeded satisfactorily at the White Sands Test Facility, N. Mex. 

Just as in the SERVICE MODULE, the compatibility of fluids with the titanium tank 

materials has been a problem in the LUNAR MODULE. 

verified that a small amount of nitric oxide added to nitrogen tetroxide inhibits the 

corrosion due to this fluid. 

A test program during 1966 

A step contributing to program progress was the successful performance of the radar 

on the SURVEYOR I unmanned spacecraft, which is similar to that in the LUNAR 

MODULE. 

At the end of 1966, the launch vehicle for the AS-206 mission was accepted for delivery to the Kennedy Space Center and the preparations neared completion at the 

manufacturer's plant for the shipment of the LUNAR MODULE to KSC. 

be from Complex 37B. 

Launch will 

Dual Mission -- Plans were established for the first of a series of dual APOLLO-uprated SATURN I missions, in which the COMMAND and SERVICE MODULES rendezvous and dock with the LUNAR MODULE in earth orbit to provide for manned flight 

of the spacecraft in its lunar mission configuration. 

APOLLO-SATURN 205/208. The AS-205 vehicle consists of an uprated SATURN I 

launch vehicle with COMMAND and SERVICE MODULES of the Block I1 design to be 

used on the lunar missions. The AS-208 vehicle consists of an uprated SATURN I 

launch vehicle and a LUNAR MODULE. 

The mission is designated 

The mission plan calls for manned launch of the AS-205 vehicle, followed a day 

later by unmanned launch of AS-208 with rendezvous, docking, and operation of the 

combined spacecraft in earth orbit. 

APOLLO-SATURN V -- Significant progress was made in the testing and qualification of the three-stage SATURN V launch vehicle in preparation for the beginning of 

all-systems-up flight tests. 

status for acceptance tests of the second stage. 

Space Center reached operational status for vehicle assembly and checkout. 

first and third stages and the instrument unit for the first flight test were assembled 

with a dummy second stage on the mobile launch stand within the Vehicle Assembly 

Building at KSC. 

The Mississippi Test Facility reached operational 

Launch Complex 39 at the Kennedy 

The 

On the first stage, the most powerful assembly of rocket engines yet produced by the 

United States, component qualification was essentially completed and the thrust of 

the F-1 engine was uprated from 1,500,000 to 1,522,000 pounds. 

engine stage generates total thrust of 7,610,000 pounds. 

were completed on the first three flight vehicles. 

duced by the contractor at the Michoud Assembly Facility, New Orleans, La. 

Thus the fiveAcceptance test firings 

The third was the first proThe first flight second-stage acceptance test firings were underway at Mississippi 

Test Facility. 

stage from 1, 125,000 to 1, 150,000 pounds effective on the fourth flight vehicle. 

Uprating of the 5-2 engine increases the thrust of this five-engine 

For the third stage and instrument unit, which are the same as the second stage and 

instrument unit of the uprated SATURN I, ground qualification tests were complete 

and the units performed satisfactorily in the 1966 flights. 

17 
The major problems in the development of the SATURN V launch vehicle have been 

in the second stage (S-11). 

one in 1965 and one in 1966. 

In May 1966, an All Systems test vehicle was lost at Mississippi Test Facility as the 

result of inadvertent over-pressurization of the liquid hydrogen tank with gaseous 

helium in a leak test. 

static firing program had been completed in preparation for the acceptance firing of 

the flight stages. 

and plans for use of remaining hardware. 

Two test vehicles have been destroyed in ground tests, 

The vehicle lost in 1965 was intended for dynamic tests. 

This occurred at a time when seven-eights of the planned 

The loss of these stages forced rescheduling of the test program 

Another problem consisted of cracks in the liquid hydrogen tanks, and leaks in the 

liquid oxygen tanks, caused by stresses resulting from forming and assembly operations, and brittleness of the aluminum. Actions taken were repair, reinforcement, 

and application of sealing material to tanks in early flight vehicles, followed by design modifications in later vehicles. 

The NASA spaceport at Merritt Island, north of Cape Kennedy, became operational 

during 1966. 

the Launch Umbilical Tower within the Vehicle Assembly Building to test the facilities. On May 25, the crawler-transporter carried the tower and the vehicle out the 

building's door and onto the specially constructed roadway, where it traveled in a 

vertical position more than three miles to Pad A. 

porter and tower were returned to the Assembly Building, the test vehicle was disassembled, and assembly and checkout of the first APOLLO-SATURN V flight vehicle 

we re begun. 

A ground version of the APOLLO-SATURN V vehicle was erected on 

Later in the year, the transAt least two unmanned orbital flights of the APOLLO-SATURN V are scheduled for 

1967. 

flights of the APOLLO-SATURN V are completed successfully, the program will 

proceed to the phase of manned earth-orbital flights of the APOLLO-SATURN V. 

When the dual missions of the APOLLO-uprated SATURN I and the unmanned 

Planning also progressed during 1966 for the actual manned lunar missions. Essential information of the moon's surface was supplied fro- unmanned SURVEYOR I 

and LUNAR ORBITER I and I1 flights. Detailed arrangements, including computer 

programs, were established for the stay on the lunar surface--lasting 18 hours on 

the first APOLLO lunar mission. 

was completed, and qualification of the complete spacesuit system was well advanced. 

Test hardware was being produced for the APOLLO Lunar Surface Experiment 

Package (ALSEP), which will be deployed on the moon 300 feet from the landing site, 

to transmit information to earth after the astronauts' departure. The USS Vanguard, 

first of three instrumentation ships designed for APOLLO tracking and data acquisition, was delivered and underwent limited use on the GEMINI 12 mission. The first 

of eight APOLLO instrumentation aircraft was also employed on GEMINI 12. Two of 

the remaining aircraft were delivered. 

Qualification of components of the lunar spacesuit 

APPOLO ADDlications 

The definition of the first phases of a program to follow the APOLLO program moved 

forward in 1966. This program will employ APOLLO space flight hardware and 

capabilities to meet other objectives than those previously planned for the lunar 

missions. 

18 
Planning moved ahead in two intereating areas. One is an airlock attached to the 

empty hydrogen tank of the second stage of the SATURN I to convert the stage to a 

habitable space structure. 

lock after rendezvous and docking with an APOLLO spacecraft. 

stage equipped with a life support system and used in this manner will be called an 

Orbital Workshop. 

Astronauts will be able to enter the tank through the airThe spent SATURN I 

Another is the APOLLO Telescope Mount, a major set of observational equipment 

consisting of a group of telescopes and other instruments mounted on a rack attached 

to the LUNAR MODULE. 

SPACE SCIENCE AND APPLICATIONS 

Continuing a trend toward the development of observatory-type spacecraft as a 

marked advance over the smaller EXPLORER class of geophysical satellites, NASA 

launched its first ORBITING ASTRONOMICAL OBSERVATORY and a third ORBITING 

GEOPHYSICAL OBSERVATORY this year. 

an important part in the unmanned space science program. 

Sounding rockets also continued to play 

To take full advantage of the unique role of astronauts as sensors, manipulators, 

evaluators, and investigators in space and on lunar and planetary surfaces, the 

Agency planned numerous experiments and other tasks for them during future 

manned missions. 

In other substantial accomplishments in the field of scientific investigations in space, 

two LUNAR ORBITER photographic laboratories and a SURVEY OR spacecraft transmitted thousands of high-resolution pictures of the moon's surface to pinpoint landing 

sites for astronauts and provide invaluable lunar data. 

Also, during 1966, an improved, completely-instrumented NIMBUS spacecraft was 

orbited making more accurate weather forecasts possible, and the national operational meteorological satellite system was inaugurated with the orbiting of ESSA I 

and 11 in February. In addition, NASA launched a second communications satellite 

for the Communications Satellite Corporation--the first over the Pacific Ocean. 

And, to round out 12 months of noteworthy progress, the Agency launched its first 

APPLICATIONS TECHNOLOGY SATELLITE and its first BIOSATELLITE- -an 

orbiting biological laboratory--in December. 

Orbiting Observatories 

On April 8 NASA launched its first ORBITING ASTRONOMICAL OBSERVATORY 

(OAO-1) into a nearly circular orbit at a height of about 500 miles. The 3,900- 

pound spacecraft was able to point to a star with an accuracy of one minute of arc. 

It carried instruments weighing 1,000 pounds, but on its second day a faulty circuit 

component ended its operation before any data could be transmitted by them. 

OGO-111, an ORBITING GEOPHYSICAL OBSERVATORY, was launched on June 6. 

This observatory was placed into a highly elliptical orbit (183 to 75,874 miles) 

reaching beyond the boundary of earth's magnetic field. 

box with several booms carrying 21 experiments for a well-rounded program of 

measurements in the space environment. 

OGO-111 is a 1,135-pound 

19 
The ORBITING GEOPHYSICAL OBSERVATORIES are designed to achieve three-axes 

stabilization with one surface facing the earth. OGO-I11 was the first to be stabilized 

in this manner for the full planned 30-day period. 

zation for 46 days, and, when ordered on July 25 into the alternate scheduled spin, 

continued to provide data from its experiments. 

It maintained this type of stabiliEXPLORER Satellites 

The atmospheric EXPLORER XXXII--a 35-inch stainless steel sphere weighing 495 

pounds--was positioned into an orbit ranging from 173 to 1,629 miles above the earth. 

This satellite uses mass spectrometry to detect neutral, un-ionized atoms and 

molecules of hydrogen, helium, nitrogen, and oxygen; density gauges to determine 

neutral particle density; and mass spectrometry with electrostatic probes to detect 

atomic ions of hydrogen, helium, nitrogen, and oxygen and to measure low-energy 

electrons. EXPLORER XXXII's orbit greatly exceeded the planned one. For this 

reason it spent a larger part of its time at greater distances than scheduled, but its 

instruments were reprogrammed permitting all experiments to return data. 

Another EXPLORER (XXXIII) was launched on July 1, an INTERPLANETARY 

MONITORING EXPLORER (IMP), the spacecraft was designed to reach deep into 

space to search for hazards to manned flight caused by energetic particles. The 

satellite went into an earth orbit ranging from 25, 350 miles to a maximum of 

295,920 miles. Its experiments measure magnetic fields, low energy particles in 

the solar wind, and solar cosmic rays. 

PION E ER 

PIONEER VI1 was orbited about the sun on August 17 to measure the interplanetary 

magnetic field, cosmic rays, and the total electron content in space, and to investigate the solar wind. 

vided information on the streaming of particles ejected by the sun in the solar wind 

and as cosmic rays. 

extends the distances to which these probes can be followed. 

Data from PIONEER VI (launched December 16, 1965) has proThe 210-foot radio telescope at Goldstone, Calif., greatly 

SURVEY OR 

The first SURVEYOR spacecraft was launched on May 30 and made a soft landing on 

the lunar surface about 63 and 1/2 hours later. The spacecraft performed almost 

flawlessly both during a 234,200-mile flight to the moon and as it carried out complex operations on its surface. 

SURVEYOR I sent back 10, 338 high-quality photographs showing details as small as 

.02 of an inch. After hibernating through the two-week lunar night, it was again 

turned on during the second lunar day and took 899 additional photographs. 

During the first lunar day (two earth weeks), 

SURVEYOR I accomplished and exceeded all planned mission objectives, transmitting data on soft-landing systems and the nature of the moon's surface which will 

contribute greatly toward the national goal of a manned lunar landing during this 

decade. 

On September 20 SURVEYOR I1 was successfully launched on a similar mission, but 

at the midcourse correction thrust phase one of the three vernier engines failed to 

ignite. This resulted in severe tumbling of the spacecraft and the loss of the spacecraft. The cause of this malfunction is being investigated. 

20 
Five flights remain in the SURVEYOR program--the next scheduled for early in 1967. 

In addition to an engineering payload, SURVEYORS C and D will carry a surface 

sampler to determine the physical properties of the lunar surface and subsurface, 

and SURVEYORS E, F, and G will carry an alpha-scatter measuring instrument for 

determining the relative abundance of chemical elements in this surface. 

LUNAR ORBITER 

The first in a series of five LUNAR ORBITER spacecraft was launched in August, 

and, after a 91-hour flight, placed in a close-in orbit about the moon, to become the 

first U. S. satellite to orbit a planetary body other than the earth. 

photographed nine selected potential sites for the manned landings of Project APOLLO, 

seven other areas within the APOLLO zone of interest, an area on the east limb of 

the moon, and eleven different areas on its far side. The spacecraft also provided 

the first pictures of the earth taken from the immediate vicinity of the moon. 

LUNAR ORBITER 

The 850-pound satellite supplied information on micrometeoroid flux and levels of 

radiation in the near-lunar environment, as well as data on the moon's gravitational 

field. 

A second LUNAR ORBITER spacecraft launched in November photographed thirteen 

other selected potential APOLLO landing sites, as well as thirteen secondary areas 

of interest on the front side and four on the back. 

ORBITER flights are scheduled for 1967. 

The three remaining LUNAR 

MARINER 

MARINER IV (launched in November 1964) continued in orbit about the sun after 

successfully completing its flyby within 6, 118 miles of Mars in July 1965. 

new 210-foot diameter antenna at Goldstone, Calif. , received tracking data from the 

spacecraft at a range of 219 million miles. 

MARINER IV transmitted coherent radio-frequency energy through the solar corona 

which was monitored by earth-based receiving stations. 

NASA's 

And as it passed behind the sun, 

A MARINER spacecraft, built as a back-up for MARINER IVY was modified to fly 

past Venus in mid-1967. The spacecraft is designed to obtain information on the 

origin and nature of Venus and its environment, complementing and extending data 

provided by the Venus flyby of MARINER 11 in 1962. This MARINER will also provide engineering experience in converting and operating a spacecraft designed for 

flight to Mars into one to be flown to Venus, and supply data on the interplanetary 

environment during a period of increasing solar activity. 

violet photometer , occultation experiments, trapped radiation detector, magnetome - 

ter, and plasma probe to supply data on the dense atmosphere surrounding the planet 

and possibly information on the planet's surface temperature. 

It will carry an ultraThe spacecraft is scheduled to pass within 2,000 miles of the planet's surface. 

(MARINER 11's closest approach was 21,600 miles. ) Its scientific components were 

delivered to the test facility for inclusion with spacecraft tests; spacecraft fabrication, assembly, and testing progressed satisfactorily. 

NASA also approved two MARINER flybys of Mars during 1969 as an intermediate 

step between MARINER IV and VOYAGER scheduled for a 1973 launch. These 

21 
missions will make exploratory investigations of Mars to set the stage for future 

experiments, particularly searches for extraterrestrial life. 

carry an ultraviolet spectrometer, infrared spectrometer, infrared radiometer, 

and two TV cameras designed for high and low resolution pictures of the Martian 

surface as they pass three times closer to the planet than did MARINER IV. 

Each spacecraft will 

During 1966, designs of these MARINER to Mars spacecraft systems were established, their missions defined, and subcontractors selected to perform the detailed 

design and fabrication of all flight hardware. 

VOYAGER 

Funding limitations have caused the first VOYAGER flights to Mars to be postponed 

from 1971 to 1973. These flights will include orbiter and survivable landing missions. 

During this year overall mission design and conceptual design studies of the landing 

capsule were emphasized. Preliminary design of the orbiting spacecraft was completed in January. 

SATURN V to launch two VOYAGER planetary vehicles (each vehicle consisting of 

an orbiting spacecraft and a landing capsule) is feasible and can assure a substantial number of scientific experiments. 

Mission and capsule studies indicate that using a single 

These capsule design studies also established that the design and development of a 

soft-landing delivery system for the 1973 mission is feasible, and that a clean interface could be obtained between the soft-landing delivery system and the landed payload. This will permit the design and development of a soft-landing delivery system 

for several Martian missions while the landed payload is changed from one to 

another. 

of the capsule system. 

The capsule design studies have paved the way for the preliminary design 

Manned Space Science 

In September Project GEMINI astronauts took pictures from their spacecraft revealing, for the first time, that there were absorption lines of iron and magnesium in 

the ultraviolet light of the stars as well as in the ultraviolet light of the sun. The 

stars photographed were in the constellations Orion, Scorpius, and Carina. 

Planning for future astronauts to carry out other scientific investigations in space, 

the Agency approved an APOLLO TELESCOPE MOUNT (ATM). 

APOLLO Lunar Surface Experiments Package -- System tests of the engineering 

model of the APOLLO Lunar Surface Experiments Package (ALSEP) began in 

November. A part of the program of experiments to be conducted and activated on 

the lunar surface by astronauts, the experiments will be carried to the moon aboard 

the APOLLO LUNAR MODULE (LM). 

obtain scientific data and telemeter it to the earth for a year. 

provide information on the changing and residual magnetic fields of the moon; the 

lunar interior, thickness, and density; the charged particle environment of the moon; 

and the pressure and composition of ions in the atmosphere. 

This geophysical station is being designed to 

Its experiments will 

The complete ALSEP system is made up of eight experiments (five to six to be 

carried on each APOLLO flight), a central station to receive commands and transmit 

22 
data to the earth, and the SNAP-27 Radioisotope Thermoelectric Generator 

viding nuclear power to operate it. 

different lunar locations. 

proThree ALSEPs will operate simultaneously at 

Sounding Rockets 

Fifty sounding rockets were launched by NASA into the region about 100 miles above 

the earth to continue studies in ultraviolet and X-ray astronomy. 

Goddard Space Flight Center have developed a stabilizer for these rockets which 

allows astronomers to point their instruments at the planets and the stars with much 

greater accuracy. 

Scientists at 

BIOSCIENCE PROGRAMS 

B io satellite s 

NASA's first BIOSATELLITE, launched on a three-day flight on December 14, was 

designed to carry experiments to study the effects of weightlessness on various life 

forms, and of weightlessness combined with an on-board source of gamma radiation. 

This marked the first flight of a new recoverable orbiting spacecraft with a natural 

atmosphere life support system and programmed remote control of complex biological experiments. 

planned, possibly because the retro-rocket failed to fire. 

The satellite could not be recovered on December 17 as 

It continues in orbit. 

Env i r onm e nt a1 B io10 g y 

Recent studies show that the regular changes in physiological functions in biological 

organisms occurring in about 24-hour cycles can break down completely and result 

in illness or death. The 24-hour rhythmic activities of rodents exposed to complete 

darkness shifted greatly, but disintegrated in continuous light. 

continuous darkness and then to constant light, the rodents rhythmic activities broke 

up into disconnected components. 

need to be kept on a regular light-dark schedule. 

When exposed to 

These experiments indicate that astronauts may 

Exobiology 

Scientists have identified certain molecules as "fossils" to extend their knowledge of 

the history of life on earth. 

ancient sediments, discovering biological chemicals that showed life definitely 

existed 3. 1 billion years ago. Fossil remains of certain micro-organisms 2. 7 

billion years old were also discovered. 

led bioscientists to recommend that a planet's fossil remains be investigated as 

possible clues to its biology. 

They used high-resolution mass spectrometry to analyze 

Identification of these molecular "fossils" 

Micro-organisms (mold spores and virus phage) survived six hours of exposure outside the spacecraft during the GEMINI 9 flight in June. 

vived two months when exposed to the vacuum and radiation of space aboard the 

orbiting AG ENA Target Vehicle. 

These organisms also sur23 
SPACE APPLICATIONS PROGRAMS 

Communications 

APPLICATIONS TECHNOLOGY SATELLITE - - The first spin-stabilized version of 

the APPLICATIONS TECHNOLOGY SATELLITE (ATS) was launched on December 6 

and placed into a near geostationary orbit on the following day. 

ing about 1,550 pounds at launch, will conduct experiments in communications, 

meteorology , and geophysics. 

The satellite, weighThe prototype of the 6,000-mile orbit, gravity gradient- stabilized spacecraft 

(scheduled for flight in mid-1967) was also completed. 

INTELSAT -- On October 26 NASA launched the first INTELSAT-11 satellite for the 

Communications Satellite Corporation. 

even though it did not achieve the desired geostationary orbit. 

commercial communications satellite INTELSAT-I (EARLY BIRD) launched by 

NASA for the Corporation in April 1965, continues to function satisfactorily in its 

geostationary orbit over the Atlantic with no noticeable signs of degradation. 

It is operating normally over the Pacific, 

The world's first 

Plans call for two more INTELSAT-I1 satellites to be positioned in geostationary 

orbits--one over the Atlantic, the other, the Pacific. More than twice as powerful 

as the first INTELSAT, these satellites will increase greatly the present coverage. 

The Pacific satellite will link Asia and Australia with North America, and the 

Atlantic' satellite will link South America and Africa, also expanding the current 

capacity between North America and Europe. 

Each satellite will satisfy some of the communications requirements of the APOLLO 

lunar program and provide additional commercial service. 

Gravity Gradient Test Satellite (GGTS) -- On June 16 a two-axes stabilized satellite, 

using a gravity gradient system made up of 52-foot long booms, was successfully 

launched from Cape Kennedy. A TITAN 111-C rocket injected the GGTS into a nearly 

synchronous, equatorial orbit, and it was demonstrated that the earth's gravitational 

pull can stabilize spacecraft in high orbits. 

Meteorology 

TIROS -- The nation's operational meteorological satellite system was inaugurated 

with the launchings of ESSA I and 11 (TIROS OT-3 and OT-2) on February 3 and 28. 

Based on the TIROS IX design, these satellites provided, on a daily basis, global 

daytime cloud cover data to national users as well as local cloud pictures to 

Automatic Picture Transmission (APT) users throughout the world. 

(TOS-A) launched October 2 is the first of the TIROS Operational Satellites to use 

the improved remote camera system developed and flight tested on NIMBUS I and 11. 

ESSA 111 

TIROS VI1 continued to set new records for longevity. 

111,000 useable pictures in over three and one-half years of operation. 

lite, together with TIROS IX and X, provides engineering data and cloud cover 

information. 

It has furnished more than 

This satelNIMBUS -- NIMBUS 11 (the second NIMBUS) was orbited on May 15. The satellite 

24 
carries Automatic Picture Transmission, an Advanced Vidicon Camera System, 

and a High Resolution Infrared Radiometer (HRIR) similar to sensors on the 

NIMBUS I flight. 

to ground stations modified to receive these data, and, for the first time, a Medium 

Resolution Infrared Radiometer to measure the heat balance of the entire earth daily. 

The HRIR also provides local nighttime cloud-cover information 

Hardware for the third NIMBUS (NIMBUS B) was being developed and the engineering 

model of the spacecraft and its flight experiments completed and tested. In addition 

to several new sensors to measure the earth's radiation, including the ultraviolet 

and infrared regions, the satellite will carry a meteorological data collection system 

to gather information on a global scale. NIMBUS B will also carry a radioisotope 

thermoelectric generator (SNAP- 19) to determine the feasibility of using this power 

source for meteorological satellites. Development of the NIMBUS D spacecraft was 

begun and its flight experiments were selected. Improvements will be incorporated 

primarily into its control system and in its data handling and transmission system. 

The 11 flight experiments of this spacecraft will be more advanced than those flown 

on NIMBUS B and provide more quantitative measurements of the earth's atmosphere 

on a global scale through infrared sounding and extensive earth platform interrogation. 

Meteorological Sounding Rockets -- NASA launched 53 research meteorological 

rockets carrying experiments to heights of 60 miles. 

grenade firings, sodium releases, and Pitot-static tube measurements) were carried 

out in the upper atmosphere to measure wind, temperature, and density. 

The experiments (acoustic 

Geodesy 

The GEOS-I geodetic satellite, orbited November 6, 1965, continues to supply data 

to 110 stations located around the world. The information is sent to the Geodetic 

Satellites Data Service, National Space Science Data Center, at Goddard Space 

Flight Center. GEOS-B (the next geodetic satellite) is scheduled for a 1967 launch. 

PAGEOS (a Passive Geodetic Earth-Orbiting Satellite) is a 100-foot diameter mylar 

and aluminum sphere which was successfully launched on June 23. 

ground stations photograph the satellite, which carries no instruments, to help 

determine the location of continents, land masses, islands and other geographic 

points for a unified global geodetic control reference system. 

Worldwide 

Earth Resources Survey 

Spacecraft-acquired data applied to agriculture, forestry, and mineral, water, cultural, and marine resources cover the wide range of the Earth Resources Survey 

Program. The Departments of Agriculture, Interior, Commerce, and other agencies are considering how such data can be beneficial. 

During this year the scientific phenomena to be measured, instruments to be used, 

and possible missions to be flown were determined. And prototypes of instruments 

to be carried aboard spacecraft were flown by aircraft over carefully selected test 

sites gathering earth resources survey data to help scientists demonstrate the 

feasibility of such measurements. 

25 
LIGHT AND MEDIUM LAUNCH VEHICLES 

During the year SCOUT, THOR-DELTA, THOR-AGENA, ATLAS-AGENA, and 

ATLAS-CENTAUR launch vehicles were used for the Agency's unmanned missions. 

The four-stage solid propellant SCOUT vehicle launched nine spacecraft--chalking 

up a record of 22 consecutive successful launches. 

THOR-DELTA orbited three meteorological satellites for the Weather Bureau and 

communications spacecraft for the Communications Satellite Corporation. Also, 

THOR-DELTA launched four satellites in NASA's Space Science and Applications 

Program, including the first BIOSATELLITE, to perform successfully in 40 of 43 

launch attempts. 

a 

AGENA successfully supported seven unmanned missions, with ATLAS-AGENA 

launches of the first ORBITING ASTRONOMICAL OBSERVATORY, the first 

APPLICATIONS TECHNOLOGY SATELLITE, two LUNAR ORBITERS, and an 

ORBITING GEOPHYSICAL OBSERVATORY; THOR-AGENA launched a NIMBUS 

weather satellite and PAGEOS, a passive geodetic satellite. 

The seventh ATLAS-CENTAUR development vehicle (launched April 8 to simulate a 

two-burn SURVEYOR mission to the moon) did not achieve a nominal CENTAUR 

second burn but remained in an earth-parking orbit instead. 

(May 30) was the first direct ascent production flight of the CENTAUR vehicle, which 

placed the SURVEYOR I spacecraft into a lunar transfer trajectory to soft land it on 

the moon. The ninth flight placed the SURVEYOR I1 spacecraft into its desired lunar 

transfer trajectory on September 20, but spacecraft problems prevented a successful 

soft landing on the moon. 

at which time all program objectives were achieved. 

hicles are scheduled to launch SURVEYOR spacecraft to the moon in 1967. 

The eighth flight 

The tenth and last development flight was on October 26, 

Four ATLAS-CENTAUR veADVANCED RESEARCH AND TECHNOLOGY 

This area of activity, which is the source of the new technology needed for present 

research and future leadership in aeronautics and space, continued to move forward 

on a broad front. 

Basic and Applied Research 

Fluid Physics -- Progress was made in determining, for the first time, the radiative properties of air at temperatures exceeding 15, OOOo F. 

essential in designing the configuration and heat protection systems of post-APOLLO 

spacecraft since radiation energy transfer is the dominant heating mechanism for 

bodies returning from interplanetary flights. Data obtained in ballistic ranges, 

shock tubes, and constricted arcs showed relatively good agreement with each other 

and with various theories and additional work was under way to determine selfabsorption effects and the detailed contributions from different parts of the spectrum. 

This information is 

The state of the thin layer of air adjacent to the surface of a supersonic body strongly 

affects the friction drag and heating of the body and is most important in the aerodynamic design of aircraft and spacecraft. 

more light on how this layer of air turns from a laminar into a turbulent state. 

A new theory was developed which sheds 

An 

26 
experiment validated the theory at Mach 4.5 and confirmed the existence of the two 

processes predicted by the theory. 

A theoretical program originated to predict molecular states through quantum mechanical analyses made it possible to predict and to detect experimentally the Nitrofluorine mcdecule, which had been searched for unsuccessfully in laboratories all 

over the world. 

tally as a result of the prediction of its stability and configuration by theoretical 

chemistry. 

This was the first time that a molecule was discovered experimenApplied Mathematics -- Research necessary for planning a Mars Orbiter was completed. 

orbits at heights between 150 and 5,000 km in three different possible atmosphere 

models ranged from about a week to 200 years. 

Using a new mathematical approach, investigators found that lifetimes for 

Electrophysics -- A laboratory investigation was instituted to determine whether 

electrostatic forces are important in the formation of tornadoes. 

the premise is that the tornado cloud derives its high angular momentum from an 

electrostatic motor type action, i. e. , two nearby cloud regions each containing 

oppositely charged water droplets with positively charged droplets moving 

to the negatively charged cloud and vice versa to produce a circulatory motion of 

water droplets. 

clouds were obtained on a small scale, and work was continuing to improve the 

laboratory equipment. This research may provide an understanding of the causes of 

tornadoes and may enable man to control them or to minimize their destructiveness. 

In this research, 

Moving charged droplets simulating the rotary motion of tornado 

Materials -- A very small solid state battery, about the size of a pea, was developed 

by researchers at the Jet Propulsion Laboratory. An aromatic hydro carbon mixed 

with a halogen and placed between magnesium and carbon electrodes was found to be 

capable of delivering useful electrical power. Such 2.5 volt solid state batteries, 

which have a short circuit current of 20 to 30 milliamps and can be encapsulated, 

are promising power sources since they should be insensitive to radiation, sterilizable, and capable of being made even smaller. 

After several years of development, NASA now has an operational large (240,000 

joules) ruby laser system, suitable for drilling, cutting, and welding of space components. With it, 1/8 inch aluminum has been welded and 1/4 inch aluminum has 

been penetrated. Work continued to improve the device and increase its useful operational life. 

A special laboratory fatigue machine was developed that will closely simulate the 

fatigue conditions (loads, temperatures, and corrosive environment) that a Mach 2. 7 

SST will experience in many flights over its full design-life. 

load, realistic gust-loads, normal maneuver loads, and thermal stresses will be applied to test specimens just as the actual airplane will encounter them from take-off 

to equilibrium cruise conditions. Simultaneously, the temperature of the specimens 

will be raised to correspond to the airframe temperature during climb while the corrosive environment of an ocean-side jetport is imposed. 

sequence of loads and temperature associated with let-down and landing will be 

applied. 

dependent effects will be revealed. 

The ground-to-air 

Then the corresponding 

The cycle will be applied in real time, so that any unexpected time27 
The facility can test sixty specimens at a time, permitting the accumulation of reliable data on the ability of the airframe to stand up under many years of use by the 

SST goes into service. This facility will support the SST program by verifying the 

design theory, by disclosing errors and unforeseen problems, and by contributin to 

the reliability and safety of the first SST. 

Columbium and tantalum base alloys which can hold boiling potassium metal for 

several thousand hours at temperatures above 2, OOOo F. were developed and evaluated. Data were collected on the effect small amounts of impurities have on the 

ability of these alloys to withstand such extreme conditions and on how to control impurities. This development is important in relation to the more advanced spacecraft 

concepts in which the electrical power for interplanetary missions would be derived 

from turbines driven by boiling metals and for potential commercial applications. 

Aeronautics 

Aircraft Aerodynamics -- A study was made of drastically modified airfoil shapes 

to determine and evaluate an aerodynamically and structurally near-ideal wing for 

flight close to the speed of sound (660 mph). 

which was mounted a swept-back wing with greater span and thicker sections than 

those of the current jets (supercritical airfoils), investigators found that this advanced configuration could be operated at about 10 percent higher speeds with appreciably less power than the most recent jet transports with conventional wings and 

fuselages. 

Using a specially shaped fuselage on 

Research is continuing to explore the potentialities of this concept. 

Structures -- Models embodying lightweight structural concepts which may be practical for a future hypersonic-cruise-aircraft fuselage were constructed and were 

being subjected to the load and temperature tests representative of hypersonic flight 

to obtain basic engineering information on structural behavior and characteristics 

and to identify specific fabrication and design problems. 

various possible designs of the hypersonic aircraft wing were made. 

tests of structural box beams representative of supersonic aircraft design indicated 

that crack propagation rates in fusion-welded beams were slightly higher than in spotwelded beams. 

Analytical studies of 

And fatigue 

Air Breathing Propulsion -- Research on propulsion systems for supersonic aircraft 

concentrated on advanced engine component concepts, such as application of advanced 

flow control technology to the design and operation of the individual compressor 

blades, which will increase performance and reduce system weight. In addition, 

competitive studies indicated the feasibility and high performance potential of a 

hypersonic research engine capable of operating with supersonic combustion to a 

Mach number of 8, and a contractor was selected to design and develop this engine. 

Aircraft Operating Problems -- In an investigation of cornering forces under heavy 

braking conditions with the aircraft yawed on the runway, tests conducted on the 

Langley Research Center Landing Loads Track indicated that maximum cornering 

forces can be developed only for non-skid conditions, that brakes should be released 

when a skid develops in order to retain directional control, and that one wheel on 

each landing gear truck might be left unbraked to develop cornering forces for control. 

A basic flight test handling qualities evaluation of the characteristics of seven general 

28 
aviation aircraft was completed by the Flight Research Center. The study showed 

that all aircraft tested were acceptable for good weather operations in the hands of 

alert, experienced pilots, but that there was a general deficiency in the aircraft 

characteristics necessary for safe instrument flight operations. 

The Naval Air Engineering Center, Philadelphia, under contract to NASA completed 

construction of spin test pits for studying the mechanism of compressor and turbine 

section failures and means of containing the fragments. 

sections up to the size of those proposed for the SST type engine. 

The pits can test turbine 

NASA continued basic research on the fundamentals of aircraft engine noise generation, and joining other Government agencies in an inter-agency aircraft noise abatement program, expanded its research to include studies of the noise generation 

characteristics and potential for noise reduction of full- scale engine components. 

The engines on the X-21 aircraft were converted to permit an inflight study of the 

effectiveness of inlet choking as a noise reduction system. 

X-15 Research Aircraft -- The three X-15 research airplanes continued in use as 

sources of basic information on manned maneuverable flight at hypersonic speeds, 

making a total of 20 flights. These flights were devoted to aeronautical and space 

flight experiments which use the unique speed, altitude, and recoverability capabilities of the x-15 aircraft. Research programs underway during the year included 

the University of Wisconsin stellar ultraviolet photography experiment, an aerodynamic base-drag study; an Air Force-sponsored high-altitude atmospheric density 

experiment, the Project APOLLO horizon scanner equipment development; a micrometeorite collection program for the Air Force; a horizontal-tail loads investigation; 

boundary-layer noise measurements; heat transfer measurements; the JPL solar 

spectrum experiment; the functional checkout of a new pilot's cockpit display panel, 

utilizing tapes instead of round dials; new inertial flight data system; and the alternate pitot static system required for future Mach 8 flights. 

aircraft were updated and modified for these various test-bed experiments. 

In addition, all three 

Two flights of the X-15-2 were made with the large external propellant tanks which 

will be required for the Mach 8 flights to be flown in support of the hypersonic ramjet research engine experiment. 

July 1. 

normal gross weight of 34,000 pounds. An error in the telemetry system led to an 

emergency landing at Mud Lake, Nev., an uprange dry-lake bed; the landing was 

without incident. The second full-external-tank flight, on November 18, was successful. Data were obtained on aircraft handling characteristics with full external 

tanks; tank jettison and separation characteristics; test of ablative materials being 

developed for programmed Mach 8 flights; and several test bed experiments. This 

flight resulted in the fastest speed to date in the X-15 program: 

6. 33. 

The first flight with full external tanks was on 

Launch weight for this flight was 52,000 pounds, in contrast with the X-15's 

4,233 mph; Mach 

Supersonic Transport - - NASA assigned technical personnel to the Federal Aviation 

Agency Source Selection Evalutation Group for evaluation of contractor proposals - 

for construction of the Phase 111 prototype supersonic transport. 

agency made wind tunnel tests of the contractors' designs to assist in the evaluation 

and provided other types of requested technical 

In addition, the 

29 
relatively minor changes in the shape of a large airplane like the SST can alleviate 

appreciably the sonic boom overpressure and impulse on the ground. It was also 

found that the same changes can be used in the design of a smaller, shorter-range 

SST to minimize sonic boom generation over domestic routes. 

V/STOL Aircraft -- The second NASA Conference on V/STOL aircraft, held at the 

Ames Research Center in April, was attended by about 500 engineers and scientists 

from industry, universities, and the Governmemt. 

progress of NASA research on vertical and short take-off and landing aircraft and 

on studies of the feasibility of using V/STOL concepts for improved short-haul comme r cia1 transport s. 

Reports were made on the 

A program was initiated to solve operational problems encountered in landing a jet 

fighter VTOL airplane in poor visibility weather conditions; contracts were awarded 

for studies of the possibility of modifying a conventional jet airplane to incorporate 

VTOL features desired for this research. 

ducted during the year, the rotating-cylinder flap and augmentor wing concepts for 

providing more efficient short take-off and landing capability, and the hingelessrotor and jet-flap rotor for improving or extending the flight capability of the helicopter seem.ed to have special potential value. 

In experimental research studies conNASA-USAF XB-70 Flight Research Program -- The initial phase of this program 

was almost completed by June 8, 1966, when one of the aircraft was destroyed following a midair collision with an F-104 chase airplane. 

two XB-70s had made 95 flights totaling 186 hours and 23 minutes of flight time. 

After the loss of the XB-70 Number 2, the entire program was replanned around the 

XB-70 Number 1, which had to be modified by installing additional research instrumentation and updating the airplane structure, landing gear , and several subsystems. 

This work was completed by early November, and the first flight in the joint NASAUSAF program was made on November 3. 

program include sonic boom (at least nine flights are scheduled in the first two 

months to obtain sonic boom data required for the national supersonic transport 

program); dynamic loads; stability, control and handling qualities; engine-inlet 

performance; and general aircraft performance. 

At the time of this loss, the 

Priority research areas for the XB-70 

Chemical ProDuls ion 

Liquid Propulsion Systems -- 

engine were tested during the phaseout of this development project. The main combustion chamber was tested successfully, yielding design specification performance 

values, other components were tested, and 62 reports on the project's technological 

advances were published. 

Components of the 1 , 500,000 pound thrust M-1 rocket 

In the advanced cryogenic rocket engine project, a jointly planned NASA-USAF effort 

to demonstrate two different advanced launch vehicle rocket engine concepts , work 

was started on toroidal combustion chamber dynamics and testing of high pressure 

cryogenic pumps. 

In spacecraft propulsion research, significant data were collected on the performance 

and cooling capabilities of the space-storable class of propellants. Good performance 

was obtained from the liquefied petroleum gases reacting with fluorine-oxygen mixtures and also from the oxygen difluoride-diborane propellant combination. 

30 
Design criteria were completed for small monopropellant hydrazine auxiliary rockets 

with thrust ranging from 1/2 to 50 pounds. 

long service life, simplify propellant storage, and are useful for a number of attitude 

control, extravehicular activity, and hot gas source applications. 

auxiliary propulsion system using high energy advanced cryogenic propellants was 

being defined, and several components were designed and tested. 

These single propellant engines have a 

A low-thrust 

Research on materials for liquid propulsion spacecraft engines stressed new manufacturing processes, with major advances in the pyroceramic and ablative rocket 

engine chamber fields. New methods were developed for processing pyroceramic 

materials such as pyrolytic graphite and compounds such as zirconium carbide and 

hafnium carbide, yielding noticeably superior products. Improved materials for 

ablative rocket engine chambers included a new synthesized resin that is easy to 

process, light in weight, resistant to salt water and many other chemicals, and has 

good compressive strength. 

heart valves, oceanographic and naval structures, and syntactic foams for flotation 

gear materials. 

It appears to be adaptable to such uses as surgical 

Solid Propulsion Technology - - Research in materials, propellants, combustion 

phenomena, environmental effects, test techniques and improved correlation of experimental data with theoretical predictions continues to provide the long- range 

basis for the NASA solid propulsion motor needs. During this year, significant results were achieved in identifying and understanding solid propellant combustion 

phenomena including the effects of metal particles in oxygen-containing propellants. 

The relation of various types of acoustic losses in a solid motor to other losses was 

clarified. 

stability for large solid motors than would otherwise be obtained in an experimental 

demonstration program. 

These efforts will provide better assurance in achieving combustion 

Large Solid Motor Program -- The large solid motor program progressed with the 

successful testing of the second 260" diameter solid rocket motor in February. 

This motor, identical to the first, developed a maximum thrust of over 3. 5 million 

pounds and burned for about 2 minutes; test results were exceptionally close to the 

pre-firing predictions. Based on the success of the two test firings a follow-on 

contract was negotiated for the firing in mid-1967 of a third motor with a thrust 

level of over 5 millioln pounds. Launch vehicle design analyses indicated that a 

260" diameter motor with a thrust of over 7 million pounds combined with the 

second stage of the SATURN IB can place about 100,000 pounds in orbit for an unusually low cost, and plans for a test of such a high thrust motor were initiated. 

Programs were underway to optimize the materials used in the fabrication of large 

motors, particularly the case and nozzle, and components, such as a failure warning system, devices for thrust termination, and motor steering systems, for a solid 

rocket motor vehicle stage were being analyzed and developed. Analyses indicated 

that the payload performance of small launch vehicles such as THOR and ATLAS can 

be improved significantly if high energy and controllable solid rocket motors are 

used as final stages, and planning was underway for demonstration tests of such 

motors. 

Biotechnology and Human Research 

Cardiovascular Research -- NASA-supported research on decreased oxygen in the 

31 
blood during prolonged high g conditions revealed that the decrease in brain performance during high g is due not only to a decreased blood supply to the brain, but 

also to the fact that the blood which is supplied has less oxygen. In other research, 

a device was developed for measuring vibrations of the heart (an indication of heart 

work) and relating them to the heart's electrical or conducting system. This device 

is new, and perhaps provides a more sensitive method for measuring changes in 

heart activity. A system incorporating several devices for measuring cardiovascular parameters was incorporated into a single chair, permitting an electrocardiogram, phonocardiogram, pulse rate, and respiration rate to be obtained from a fully 

clothed individual who simply sits in the chair. 

Respiratory Research -- NASA continued work on the problem of providing a suitable 

and safe atmospheric environment for astronauts. A summer study group on respiratory physiology sponsored by NASA, and conducted by the Space Science Board of 

the National Academy of Sciences, defined critical respiratory research needs for 

future extended manned space flights in 16 areas ranging from oxygen toxicity to the 

action of drugs and medication on the respiratory tract. 

Investigations of oxygen toxicity led to a discovery that may affect research on emphysema, a progressive and usually fatal lung disease whose exact cause is unknown 

and for which no curative treatment is known. Research on emphysema has been 

hampered because only people get the disease, and it could not be induced in laboratory animals. In NASA's studies of the toxic effects of pure oxygen on mammals, 

rats and larger animals breathing pure oxygen at 14.7 psi (sea level pressure) for 

extended periods developed lung lesions very similar to true emphysematous lesions. 

This finding may serve as the basis for research on the treatment and perhaps cure 

of human emphysema. 

Studies conducted with the Navy and the Air Force to determine the best diluent for 

oxygen when a two-gas spacecraft system becomes feasible showed helium to be safe 

for as long as 57 days. 

Noise -- Studies were underway on the effects of high-intensity sound in the 1-100 

cycles per second range on the inner ear sensory hair cells, and on three psychophysiological problems related to the sonic boom: 

booms upon sleeping persons, (2) the startling effect on people who are awake, and 

(3) the relation between the audibility of sonic booms and the physical characteristics of their acoustic waveforms. 

(1) the arousal effects of sonic 

Life Support Systems -- The advanced closed cycle system which requires resupply 

every 90 days while in orbit was tested at the Langley Research Center with limited 

manned runs. 

concepts were being developed. 

electrochemical carbon dioxide concentrator, of solid electrolyte techniques for reclaiming oxygen from carbon dioxide, and of expulsion techniques for subcritical 

cryogenic oxygen using electric fields to replace the gravity field. 

Concurrent with this system test program, new life support system 

Progress was made in the development of an 

Hard Suit Development -- Studies of the hard suit concept produced a radical arm 

and joint design, utilizing the principle of a constant volume joint applied to two 

conic or cone-like sections so that they interface to form a rotating seal. 

testing, the best features of the Ames Experiment hard suit and of the earlier series 

can be incorporated into an operational suit. 

After 

32 
Underwater Simulation - - Astronauts participated in studies of water immersion to simulate the effects of reduced gravity on human performance. 

Cernan simulated several of the EVA tasks which were involved in the GT-9 flight, 

and experienced problems indicating the need for redesign of footholds. Astronaut 

Aldrin received training on the complete sequence of the GT-12 EVA in the underwater simulation facility. Using a time chart for each activity, he rehearsed the 

EVA tasks underwater on three different occasions, resulting in some modifications 

to the EVA procedures, and late in October he went through a final complete EVA 

sequence. He returned to the underwater simulation facility on November 30, after 

his space flight, to compare its effects with the water immersion simulation of 

zero g. 

Astronaut 

Aerosol Particle Analyzer -- The instrument to measure dust particles in the cabin 

atmosphere was fabricated, qualified for flight, and assigned to the flight of the 

SATURN APOLLO 204 spacecraft. The finished hardware is a 3 1/2" x 4" x 5", 

self-contained, portable unit which replaces the standard one or two racks of heavy 

electronics normally required. 

Flight Experiments - - The Orbital Otolith experiment to provide basic physiological 

information on how the otolith made considerable progress. Flight hardware was designed, fabricated, and flight qualified, 

baseline data were obtained in the laboratory on the otolith response in the 1 g environment, and techniques to implant and support microelectrodes during the launch 

were perfected. 

205 vehicle, which was cancelled. 

scheduling on as early a flight as possible. 

functions in the zero g environment 

The experiment was scheduled for flight on the SATURN APOLLO 

The experiment was being considered for reFor the primate experiment, 35 companies were invited to submit proposals for a 

hardware definition study, the responses were evaluated, and recommendations were 

made for the contract award. 

the problems of diet, animal confinement, animal instrumentation, performance 

measurements, and experiment techniques. Problems uncovered, such as diet 

deficiencies, were being researched. 

Concurrently, laboratory research was conducted on 

Space Vehicle Systems 

Aerothermodynamics - - The reentry V Experiment returned highly significant data 

on the performance of a promising heat shield material. The second NASA liftingbody vehicle, the HL-10, was delivered and was being readied for initial flight tests. 

The first vehicle, the M-2, delivered last year, was flown in the subsonic flight 

regime and landed several times to determine pilot handling qualities and vehicle 

landing characteristics. 

deployment and performance characteristics of parachutes for use on the VOYAGER 

program. 

deployed so as to simulate flight in the very low density Martian atmosphere. 

such experiment with an 85-foot parachute was successfully completed. 

also continued on advanced lifting parachutes capable of landing APOLLO-type 

spacecraft on land and of being steered to chosen landing sites. 

Flight research was being conducted to determine the 

The parachutes are carried to high altitudes by balloons and rockets and 

One 

Research 

Structures -- Analytical studies demonstrated the feasibility of constructing and deploying in space a very large (about one mile in diameter), extremely lightweight 

radio telescope antenna to detect electromagnetic waves from'stellar sources in the 

33 
very low frequency range. 

wire or ribbon relatively insensitive to damage caused by meteoroid penetrations. 

Dynamic modeling technology for large boosters demonstrated its value through 

dynamic tests of models of the TITAN 111, which was developed and flown successfully with its structural dynamic qualities determined solely by modeling techniques 

without the full- scale ground tests characteristic of other large launch vehicles. 

The same economical technique was used to test models of the SATURN V. 

The antenna would be made of an open grid work of fine 

An analog computer program was developed to investigate the effects of rough terrain and low gravitational restoring force on a vehicle traversing the lunar surface. 

The same program, because of its generality, can also be used to predict the response characteristics of earth vehicles. 

Environmental Factors -- Analytical techniques which can be used to calculate the 

transmission of electrons through shield materials, the production of secondary 

radiations within the material and their subsequent penetration through the shield, 

were developed and checked experimentally. 

used to assess the radiation doses received by astronauts in manned space flights. 

Data from this program were being 

The three large PEGASUS spacecraft, launched in 1965 by uprated SATURN I vehicles 

to count meteoroid penetrations in metallic skins, continued to furnish significant 

data. These data, with those obtained by EXPLORER XXIII, resulted in revisions 

to the APOLLO meteoroid design criteria. Artificial meteor observations yielded 

data used in analyzing natural meteor observational data and in determining the 

meteoroid hazard to spacecraft. 

Data from the Lewis Research Center zero-gravity program were the basis for the 

design of the propellant management systems used in the CENTAUR and S-1VB 

stages. 

ballistic flight, and its adequacy was confirmed by successful flights of the CENTAUR 

and S-IVB stages. 

Feasibility of the system was demonstrated by a liquid-slosh experiment in 

Test procedures used to determine the degradation of thermal control coatings exposed to the space environment were improved by measuring degradation without exposure to the atmosphere. Results obtained in such tests resulted in modification of 

coatings on the LUNAR ORBITER spacecraft. 

Design Criteria -- The program to develop design criteria to insure the flightworthiness of NASA space vehicles was strengthened through the assignment of 

specific responsibility to NASA Centers: 

propulsion; Electronics Research Center for stability, guidance, and control; and 

Goddard for the Environment area. Contractual and in-house efforts were continued 

to formulate suitable criteria. 

Langley for structures; Lewis for chemical 

Electronics and Control 

Project Scanner -- This program was initiated to measure the radiance characteristics of the earth's horizon as a basis for the development of highly accurate navigation and attitude control sensors. 

produced more than 250 good horizon crossings and data which revealed close 

correlation between theoretical predictions and the experimental data. 

the experiment indicated that the 14-16 micron region is relatively free of cold cloud 

The first flight of a sub-orbital probe in August 

In addition, 

34 
effects which were major contributors to the failure of the OGO-I1 spacecraft. A 

second sub-orbital probe was launched on December 10 to acquire additional data 

under different seasonal conditions and further verify the theoretical calculations. 

Laser Gyro -- NASA began development of a three-axes ring laser gyro system for 

evaluation in a strapdown inertial platform, thereby eliminating complex and costly 

gimbal systems currently employed as reference platforms in spacecraft and aircraft. 

gyros in a strapped-down mode (0. lo per hour drift rate) by a factor of 10 and will 

also be simpler and less costly. 

Studies indicated that this system will exceed the performance of conventional 

Control Systems -- Results of research on new or advanced concepts for spacecraft 

and aircraft control included a manual control backup capability for the APOLLO 

SATURN V launch vehicle upper stages; a control moment gyro system applied in the 

APOLLO Telescope Mount project for precise pointing of a solar telescope by attitude control of an APOLLO vehicle; an aircraft autopilot using fluidics or fluid devices exclusively and offering potential low cost, high reliability, and long life; and 

indirect viewing optical devices to give pilots of lifting body reentry vehicles adequate visibility for landing. 

Optical Technology - - High resolution space telescopes for optical astronomy and 

communications may be developed by using segmented optics which could be assembled and aligned in space. 

out of alignment and to what extent and provides electrical signals to correction actuators located behind the mirror. 

model was tested to evaluate this technique with encouraging results. 

cept proves workable, it will mean significant advances in optical technology for 

space astronomy, communications, earth orbital geological surveys , mapping, and 

navigation. 

A mirror figure sensor determines which segments are 

A 24-inch diameter 3-segment mirror feasibility 

If this conVibrating Diaphragm Pressure Transducer - - An instrument was developed for 

measuring aerodynamic pressure on small models used in hypersonic tunnels and 

shock tubes. It is capable of operating from l/lO,OOO to 1,000 mm pressure with 

an accuracy of about 1 percent. 

damping of a vibrating metal diaphragm which is immersed in the gas whose pressure 

is to be measured; the higher the surrounding gas pressure, the larger is the damping 

effect on the membrane. 

of its simplicity. 

Angleometer -- Another device was designed to give very precise model alignment 

with gas flow direction required in testing with small models. 

lar inclination with a precision of plus or minus .02O over a range of 60°. 

vice, which weighs 4 ounces and is l 7/8" x l 3/32" x 5/8" in size. 

extremely linear and insensitive to temperature effects, and its critical sensing 

element is free from wear. 

Its operating principle is based on sensing the 

The device lends itself well to automatic operation because 

It can measure anguThe deThe sensor is 

Adaptive Telemetry -- In research on methods of increasing the efficiency of telemetered data from spacecraft, on-board ,adaptive telemetry techniques were developed which remove redundant information bits and reduce the volume of data transmitted to earth. The method conserves transmitting power and reduces ground processing. 

35 
NUCLEAR SYSTEMS AND SPACE POWER 

In the field of nuclear systems and space power, further research and development 

gains were achieved with nuclear power generation, solar and chemical power 

research, and electric thrustors. 

Nuclear Power Generation 

The SNAP-8 project is aimed at developing a 35 kilowatt power system capable of 

reliable space operation for 10,000 hours. 

system, in a breadboarded configuration, began operating, and a self- sustaining 

electrical output of 33 KWe was achieved. 

In 1966, the first power conversion 

Work on the SNAP-19 isotope generator continued. Ames Research Center and the 

AEC's Lawrence Radiation Laboratory, working together and using an isotopically 

fueled SNAP- 19 generator, mapped its radiation field to determine its suitability 

for other satellites that may carry extensive scientific equipment. 

The SNAP-27 generator begun last year under AEC sponsorship for the APOLLO 

Lunar Surface Experiment Package (ALSEP) entered the hardware delivery stage. 

Components and subassemblies of actual equiment were delivered and were undergoing tests. 

attacked and solved. 

come, and the contractor is expected to meet the completion schedule. 

Many of the problems encountered during design and manufacture were 

Difficulties in meeting the weight restrictions were being overThe advanced nuclear electric power program continued to give major emphasis to 

three energy conversion concepts: the Rankine and Brayton cycle turbogenerator 

systems and the thermionic direct conversion system. 

The alkali metal Rankine turbogenerator program attained major milestones in the 

technologies of the system materials and components. A 2100°F liquid sodium-toboiling potassium loop, with walls constructed of an advanced columbium alloy, 

and with sample stator blades of advanced molybdenum alloy in the circuit, completed 

a 5000-hour endurance test. The loop showed only negligible evidence of corrosion. 

A 200-kilowatt two-stage turbine, operating with slightly wet potassium vapor, 

successfully completed a 5000 -hour performance-and-endurance test. 

little or no evidence of erosion of the blades, and the turbine operated steadily and 

efficiently. 

There was 

Results of a design study indicated that a tenfold reduction in the weights of conventional electromagnetic pumps is attainable. 

require no lubrication and have zero leakage. 

reliability of dynamic space power systems. 

Such pumps have no moving parts, 

Their use substantially increases the 

The reactor powered thermionic direct conversion system program continued to 

make significant progress in providing new data on some of the problems involved 

in the design of a long-life lightweight system. The principal efforts included reactor fuel property research and out-of-reactor life-testing of high performance 

converters. The fuel investigations were still in progress at the end of the year. 

The (stable performance) operating life of the out-of-pile converters continued to 

improve, although the life achieved from converter-to-converter remains erratic. 

36 
Numerous re search programs relating to detailed thermionic component problem 

areas were also continued. 

upon the electrical properties of insulators. 

of the chemical compatibility of various insulator and braze materials with high 

temperature cesium vapor. 

stability of the crystal orientation of various emitter materials. 

involved with finding improved methods of protecting vapor depositing refractory 

elements and alloys. 

A typical one concerned the effects of reactor radiation 

Another was addressed to the matter 

A third was concerned with the high temperature 

And a fourth was 

The Brayton cycle power conversion work was focused on the 5 to lOKWe power 

range typical of the needs of early manned orbiting space station missions. 

high cycle efficiency of the Brayton system at these low power levels makes it 

attractive for use with a radioisotope heat source. "Cold" flow performance tests 

(efficiency, pressure ratios, etc. ) were substantially completed on the radial flow 

turbine and compressor components, and l'hotll flow tests on the gas bearing mounted 

turbocompressor package were in progress. Preliminary tests were encouraging. 

The gas bearings operated successfully at their design temperature and speed. However, facility limitations made it necessary to operate the turbocompressor package 

at less than its design temperature. Design point operation (about 1550°F turbine 

inlet temperature) is the prime objective of the test series that will begin shortly. 

The 

The performance achieved on the small research turbines and compressors led to a 

more compact single-shaft radial flow unit typical of a 5. 5KWe power system. 

unit, now in preliminary design, will combine the turbine, the alternator, and the 

compressor. 

This 

Solar and Chemical Power 

The extension of solar power system capabilities to multi-kilowatt levels was given 

increased emphasis during 1966, with the initiation of a technology program directed 

toward the test of a deployment model of a 12. 5 kilowatt solar panel assembly. Four 

such panel assemblies grouped around the spacecraft would be capable of providing 

a 50-kilowatt output, providing a 50-fold advancement in the power generating 

capacity of solar cell arrays with a 2 to 1 reduction in weight over present technology. 

Significant reduction in the solar cell's sensitivity to radiation hazards of the space 

environment is believed possible, based on 1966 research results. Short duration 

tests to date of lithium-doped silicon solar cells indicate a 50-to-100-fold increase 

in radiation tolerance over comparable solar cells made by the best conventional 

processes. 

these cells for use. 

Long duration tests are needed before determining the suitability of 

Developmental circuit techniques were demonstrated for the parallel operation and 

synchronization of low-input voltage converters. 

The low-input voltage conversion technology benefitted also through the development 

of experimental silicon power transistors having collector saturation resistance 

comparable to the best presently available germanium devices. 

also have advantages of reduced switching time and higher breakdown voltages. 

even more importance, the allowable junction temperature for silicon is about 

60 percent higher than for germanium, thus markedly reducing sensitivity to the 

operating environment. 

The silicon units 

Of 

37 
Electric Thrustors 

The attainment of thrustor components capable of achieving long life at high performance has long been a major goal of the NASA effort in electric rocket propulsion. 

Endurance tests of ion thrustors and their associated propellant feed systems during 

the past year, the most notable being a single engine test of over 8000 hours, provided confidence that this goal can be met. 

a second flight in the SERT (Space Electric Rocket Test) program. 

The results led to a decision to prepare 

The successful sub-orbital SERT I flight in July of 1964 demonstrated that ion 

engines can operate in the space environment. 

flight will be to verify long-term thrustor performance in space. 

to take place in the first half of 1969. 

such engine systems in combination with light weight solar arrays for prime or 

mid-cour se propulsion of planetary probes indicated that such an approach has 

potential merit. 

The primary objective of this second 

Launch is planned 

Initial studies evaluating the usefulness of 

Progress was also made in developing the small electric thrustor systems intended 

for spacecraft auxiliary propulsion. 

periment aboard the ATS-B satellite. Other systems were being prepared for flight 

on later spacecraft. Advanced research efforts were continued on ion, plasma, and 

e le c t r othe rmal system s . 

A resistojet system was installed as an exTHENUCLEARROCKETPROGRAM 

During 1966, the major emphasis in the joint NASA/AEC Nuclear Rocket Program 

was on the continued development of graphite reactor and engine system technology. 

As in previous years, work also continued at a low level of effort on the alternate 

solid core reactors, using tungsten instead of graphite as the primary structural 

material, and on various advanced cavity reactor concepts offerihg promise of 

greater performance. 

Technology work on an 1100 megawatt reactor and engine system was being performed 

under the NERVA project and is an outgrowth of the reactor technology developed by 

the Los Alamos Scientific Laboratory earlier in the program. In addition, work was 

also underway to develop a large NERVA engine with a thrust of 200,000 to 250,000 

pounds and a nominal reactor power of about 5000 megawatts. The technology for 

this effort is being provided through the PHOEBUS program. 

Advanced graphite reactor technology work is being carried out through the PHOEBUS 

effort. 

periments, were being tested to explore some of the operating characteristics and 

design features planned for a larger PHOEBUS 2 reactor of approximately 5000 

megawatts. 

KIWI-sized reactors, called PHOEBUS 1 and incorporating a variety of exNERVA Reactors and Systems 

Two major test series were conducted during the past year as part of the NERVA 

reactor and engine system technology effort. The first was designed to increase the 

existing knowledge and understanding of nuclear rocket engines which previously had 

been studied only under cold flow conditions. The test article used was a 55,000 pound 

38 
thrust "breadboard" engine called the NRX/EST (NERVA Reactor Experiment/Engine 

System Test). 

called the NRX-A5, was designed to provide further data on reactor operation under 

extended test durations. 

The second test, involving the use of a NERVA technology reactor 

The "breadboard" engine system test series was initiated in December of last year; 

power testing was initiated in February of this year and extended into March. The 

test series differed from reactor tests previously conducted in that it involved the 

use of several major components not previously operated with a reactor: a turbopump, a turbine power control valve, and a nozzle with a hot-bleed port located in 

its convergent section. 

reactor test car to provide the flow and pumping arrangement to be used in a flight 

system and, therefore, system characteristics representative of a flight engine. 

The NRX/EST was thus markedly different from a test system used when only a 

reactor is being tested. 

These components were functionally arranged on a modified 

The objectives in the "breadboard" engine test program were to demonstrate the 

hot bleed cycle nuclear rocket engine, to determine the ability of the engine to start 

up without any separate supply of starting energy (the so-called bootstrap start)', 

to provide data on steady state and transient operation of the engine, and to examine 

various control modes. All of these objectives were achieved. 

After cold flow tests on this engine, a series of power tests was conducted. 

there were ten startups to power. 

propellant dewar and the temperature of the reactor's reflector were varied to 

determine their effects on the bootstrap start characteristics. 

numerous closed loop and open loop control modes were investigated and numerous 

experiments were conducted to determine the response of a system to pressure, 

temperature, and power transients. A total of 110 minutes of power operation was 

accumulated, including more than 28 minutes at full power. 

In all 

During these startups, the pressure in the 

In the several tests, 

As a result of this test series, it was possible to conclude that the hot bleed system is 

stable over a very wide range. Such a conclusion means, in addition to its general 

significance, that the system can be throttled at full specific impulse, that several 

start techniques are feasible, and that any one of several control modes can be 

used. 

out the hardware prior to power operation. 

It was also found that cold flow tests can be used very effectively to check 

The NERVA NRX-A5 reactor was first successfully operated at full power for 15-1/2 

minutes and then restarted and operated for an additional 14-1/2 minutes on June 23, 

1966. 

the reactor under closely-controlled sustained operating conditions. 

The objective of the test program was to explore the corrosion behavior of 

With the completion of the NRX-A5 test program, more than one and three quarters 

hours of reactor operation at or near full power had been accumulated in the technology program. Particularly noteworthy was the fact that there had now been a string 

of seven successive reactor tests, including the breadboard engine system, without 

a reactor failure. This fact indicated that nuclear rockets have a potential for high 

reliability through a rea sonable development program. 

To complement the reactor and engine system technology efforts which continued 

throughout the year, work also continued on the design, construction, and/or 

39 
modification of the facilities required to carry out the next phase of work under the 

engine system technology effort -- the testing of ground experimental engines (XE). 

The testing of ground experimental engines, XES scheduled to begin in mid-1967, is 

to be carried out in Engine Test Stand 1 at the Nuclear Rocket Development Station. 

At year's end, this test stand was being activated. -Reactor testing will be conducted 

in Test Cell "C" which was being modified to accommodate the higher powered 

NERVA and PHOEBUS 1 technology reactors. 

The development testing of the large NERVA engine (200,000 to 250,000 pounds of 

thrust) will be accomplished in a new test facility called Engine/State Test Stands 2 

and 3, now in the preliminary design phase. 

PHOEBUS Reactors 

In the PHOEBUS reactor program, major activity during 1966 was in preparing for 

the upcoming PHOEBUS 1-B power reactor tests. 

the nonreactor components (exhaust nozzle and facility feed system) for conducting 

the PHOEBUS 2 power reactor experiments. 

Work also continued to develop 

The development of the exhaust nozzle for the PHOEBUS 2 was being accomplished 

under contract. The nozzle design is similar to the U-tube nozzle used for NRX 

reactor testing, except that Hastelloy X material is being used instead of stainless 

steel to accommodate the higher PHOEBUS 2 temperatures and heat fluxes. 

cation of the basic nozzle hardware and activation and demonstration of the nozzle 

test stand (using an uncooled nozzle) were completed during 1966. 

nozzle also was moved in the final stages of fabrication and is nearing completion. 

FabriThe first cooled 

Development of the feed system for the PHOEBUS 2 has been underway now for the 

past four years. 

developed for reactor testing in the Los Alamos KIWI program at NRDS. 

PHOEBUS 2 feed system, two of these pump-turbine units were being combined in a 

parallel arrangement to provide the higher flow rates required. 

Basically, this system is an outgrowth of the pump-turbine system 

In the 

In addition, the pumps were being developed to deliver fluid at higher pressures 

than were required for the KIWI tests. A single pump-turbine unit of this system 

was installed at Test Cell C; it is to be used for the PHOEBUS 1-B test scheduled 

to be conducted early in 1967. 

Tungsten Reactors 

Research on the tungsten systems has shown that tungsten reactors are feasible and 

that their performance in terms of specific impulse probably approaches that of the 

graphite system. This research also has shown that tungsten reactors can operate 

for long durations. 

do not require operating durations longer than appear to be attainable with graphite. 

Therefore, all work on tungsten nuclear reactors was discontinued at the end of 

FY 66. 

However, the missions currently envisioned for nuclear rockets 

Advanced ConceDts 

The advanced concept work conducted under the nuclear rocket program consists 

40 
primarily of basic studies on the liquid and gaseous fuel reactor concepts to explore 

some of the known problems that may be associated with establishing their feasibility 

and performance potential. The work includes basic research into the phenomena of 

co-axial and vortex gas flows involving two or more gaseous components, calculations of fluid properties at extremely high temperatures and pressures, analysis 

of radiation heat transfer processes, and research on the properties of molten 

metal-carbide mixtures. 

TRACKING AND DATA ACQUISITION 

The Tracking and Data Acquisition Program continued to play a highly successful 

part in support of NASA missions -- both manned andunmanned. 

operational support provided, basic network facilities and equipment were modified 

and augmented to meet the requirements of NASA's future programs. 

In addition to the 

Manned Space Flight Network 

The Manned Space Flight Network, an outgrowth of the original Mercury Network, 

successfully completed its support of the second phase of the Nation's Manned Space 

Flight Program -- GEMINI -- and is currently supporting the APOLLO Program. 

From the first GEMINI launch, in April 1964, through the final flight, in November 

1966, the Network repeatedly demonstrated its support capability and recorded 

many "firsts" in space accomplishments. In 1966, the Network supported the first 

dual launch and docking with an AGENA vehicle, GEMINI 8, and controlled the first 

docked vehicle maneuvers, GEMINI 10. The GEMINI 11 support was highlighted by 

the precision of the technical operations which enabled the spacecraft, during its 

first orbit of earth, to catch and dock with the AGENA vehicle after a chase of 

18,000 miles in space. 

future astronauts will require similar support during the APOLLO Program. 

Proof of such precision operations was necessary since 

Further proof of these precision operations was obtained during the GEMINI 12 

mission. From lift-off to splash-down, the Network constantly monitored the flight, 

relaying necessary information and commands to the astronauts. Precise orbit predictions and computer calculations enabled the spacecraft to rendezvous and dock 

with an AGENA target vehicle that had been fired aloft 99 minutes before the GEMINI 

launch. The accuracy of the "splash-down" was another example of the precision 

the Network has developed during the GEMINI Program. For the fourth straight 

time, a GEMINI spacecraft landed close enough to its recovery ship to permit television coverage of the descent and splash-down via the EARLY BIRD satellite to an 

estimated 50 million Americans. 

In addition to performing its primary function, support of NASA's Manned Space 

Flight Programs, the Network provides similar support for other NASA and Department of Defense programs on a noninterference basis to the manned program. Some 

of the programs so supported during 1966 were the ORBITING ASTRONOMICAL OBSERVATORY, the SURVEYOR, the TITAN I11 C, and the ORBITING GEOPHYSICAL 

OBSERVATORY. 

During calendar year 1966, existing GEMINI network systems supported the final 

GEMINI flights and early APOLLO/SATURN IB missions concurrently with major 

augmentation of the Network for support of the more complex missions of the later 

41 
APOLLO Program. This year five GEMINI support stations, three new land stations, 

and one of the five APOLLO Instrumentation Ships achieved operational capability 

for support of these later missions. 

stations required for APOLLO Program support, including eight APOLLO/Range 

Instrumentation Aircraft (A/RIA) , will achieve initial operational capability. 

During calendar year 1967, all remaining 

Effective September 1, 1966, management of the GLOTRAC Station at Gibbs Hill, 

Bermuda, was transferred to NASA from DOD. The DOD reimburses NASA for the 

operational costs of the GLOTRAC Station, and, in turn, NASA provides support for 

all programs requiring coverage by this station. 

with the NASA/DOD agreement concerning the operations of land-based tracking, data 

acquisition, and communications facilities. 

The transfer was in accordance 

The conclusion of the GEMINI Program eliminated NASA's requirement for its 

tracking station at Kano, Nigeria. 

support of Project MERCURY, and was continued for GEMINI. 

tion of the Network for APOLLO support, the Kano station is no longer needed. 

The station was established in October 1960, for 

With the recodiguraSatellite Network 

The Satellite Network supports NASA's unmanned scientific and applications satellites. 

The Network also supports space projects of other Government agencies (the Department of Defense and the Environmental Science Service s Administration) and industry 

(the Communications Satellite Corporation). 

through the electronic Space Tracking and Data Acquisition Network (STADAN) 

stations and the Smithsonian Astrophysical Observatory (SAO) optical tracking 

stat ions. 

The Network provides this support 

Two of the veteran STADAN stations -- East Grand Forks, Minnesota, and Blossom 

Point, Maryland -- were deactivated during the year. Although these stations were 

invaluable for support of early programs, the large unmanned satellites now being 

launched follow orbital paths which are better served by stations at other locations. 

Also, two consolidations of equipment and capabilities were accomplished, resulting 

in reduced operating costs. Equipment previously located at Woomera, Australia, 

was relocated and consolidated with the STADAN station at Canberra; and Minitrack 

and telemetry operations at College, Alaska, were consolidated with the STADAN 

facilities at Fairbanks. 

Support requirements for the Applications Technology Satellite (ATS) Program 

necessitated some additions to the Network. 

station at Toowoomba, Australia, and adding project-unique equipment at Rosman, 

North Carolina, and Goldstone, California, all of which were completed during 1966. 

These include locating a transportable 

Forty-foot parabolic antennas were installed at Tananarive, Madagascar, and Fair - 

banks, Alaska, to meet the increasing workload. 

primarily to the volume of data received from the large Observatory-type satellites. 

The increase in workload is due 

Another vital addition to the Network during 1966 was the Network Test and Training 

Facility, located at the Goddard Space Flight Center, Greenbelt, Maryland. This 

facility is used as an engineering test-bed for the checkout of new and standard 

equipment prior to installation at the operational stations. 

42 
Deep Space Network 

The Deep Space Network supports NASA's unmanned lunar and planetary space flight 

missions. During the year, three Network stations -- located in Australia, Spain, 

and California -- were being modified and equipped to provide joint support to the 

Manned Space Flight Network for the lunar phase of the APOLLO Program. These 

stations are approximately 120° apart in longitude, and allow continuous viewing of 

a lunar mission from at least one of the ground stations. 

During the year, the Network supported six major flight missions: PIONEER VI 

and VII, SURVEYOR I and 11, and LUNAR ORBITER I and II. The Network also 

provided limited support to the MARINER IV mission and to two ATLAS-CENTAUR 

vehicle development tests, AC-8 and AC-9. With the exception of PIONEER VI and 

MARINER IV, all the missions were launched in 1966. 

The support given the SURVEYOR I mission -- one of the most significant and 

successful lunar flights to date -- was outstanding. 

provided the first opportunity for the Network to demonstrate its capability to 

control a spacecraft from launch to lunar soft-landing and lunar based operations. 

The successful accomplishment of this feat required that over 100,000 commands be 

sent to the spacecraft, and resulted in the receipt of over 10,000 pictures from the 

lunar surface. 

The SURVEYOR I mission 

The Network again demonstrated its support capability during the LUNAR ORBITER I 

and I1 missions. 

marginally, the Network provided flawless support throughout the entire mission. 

The ORBITER I1 mission was also provided this level of support, and the pictures 

received at the Network stations were excellent. These high-quality pictures are 

vital in determining the APOLLO landing sites on the moon. 

Although the high resolution camera aboard ORBITER I functioned 

A significant addition to the Network in 1966 was the 210-foot diameter parabolic 

antenna at Goldstone, California. Dedicated in April 1966, the antenna is the 

United States' largest fully steerable antenna and the world's largest built for 

research by spacecraft. 

abut 16 million pounds -- provides an overall tenfold impravement in telecommunications support over that of the standard 85-foot diameter antenna. 

capability permitted solar corona experiments to be conducted with the MARINER IV 

spacecraft, and provided the first measurements of radio transmissions through the 

solar plasma. 

PIONEER VI and VI1 flight missions will extend the useful life of these missions a 

minimum of one year. 

This giant structure -- it stands 240 feet tall and weighs 

This increased 

It is estimated that using this antenna station to support the 

Network Communications 

The NASA Communications Network (NASCOM) is the interconnecting link between 

the network stations and control centers. The NASCOM was extremely successful 

in meeting the communications requirements of NASA and other agencies during the 

period. 

In addition to meeting the operational requirements the NASCOM was being prepared 

for the APOLLO Program. 

stringent communications requirements of any program to date. 

The APOLLO Program will impose by far the most 

Last year it became 

43 
evident -- from studies conducted with the National Communications System (NCS) -- 

that these requirements could not be met by conventional systems alone but could be 

met through the addition of a communications satellite system. 

Accordingly, NASA contracted for communications services via the INTELSAT ' 

communications satellites. The primary use of these circuits will be in support of 

the APOLLO Program to provide communications between remote instrumentation 

ships and stations and the United States. The stations using the satellite services 

are located at Carnarvon, Australia; the Canary Islands; and Ascension Island. The 

three APOLLO instrumentation ships, providing coverage for the insertion/injection 

phase and equipped with communications satellite terminals, will be stationed in the 

Atlantic, Indian, and Pacific Oceans. These satellite communications services will 

provide necessary communications with sufficient reliability and quality to allow 

real-time mission direction from the Mission Control Center, Houston, Texas. 

UNIVERSITY PROGRAMS 

The NASA Sustaining University Program has elements related to predoctoral trainining, special purpose multidisciplinary re search, and to construction of laboratory 

facilities. All elements contribute to broadening the base of university participation 

in the space program. 

One hundred and fifty-two colleges and universities, including at least one institution 

in each state, now hold training grants. 

students in the program rose to 3,681, as 1,335 new students began their training in 

space-related sciences and engineering. By September 1, 1966, 334 doctorates had 

been awarded at 75 universities in 34 states and the District of Columbia. 

are now participating in this program in every state. 

In September 1966, the total number of 

Students 

NASA- supported multidisciplinary re search and the encouragement of new research 

were provided through 57 research grants at 55 universities. 

Progress continued in expanding research facilities at universities. 

ties grants were made to universities, and eight facilities begun under previous 

grants were completed, providing an added capability of 283,000 square feet of 

university laboratory area for space related investigations. 

Two new faciliINTERNA TIONA L AFFAIRS 

NASA again extended its international cooperative space and atmospheric re search 

projects, as well as support activities, and laid the groundwork for new ones. 

Satellite Projects 

The successful Canadian satellites ALOUETTE I and ALOUETTE I1 (launched by 

NASA in 1962 and 1965, respectively) continued probing the ionosphere as the sun 

passed its quiet period. The two satellites are part of an eleven-year long, fivesatellite series to cover an entire solar activity cycle. 

are scheduled for launching by NASA in 1967, 1968 and 1969. 

The next three in the series 

The first satellite launched in cooperation with France (FR-1) passed its first year 

in space on December 6. Satellite instrumentation and telemetry have functioned 

44 
effectively, and at year's end U. S. and French scientists were reducing and analyzing 

the data received from the spacecraft. 

In May, NASA and the French National Center for Space Studies (CNES) concluded an 

agreement on a new experimental project. 

the scientific value and technical feasibility of collecting global weather data from 

constant-level instrumented balloons by means of an earth-orbiting satellite (EOLE/ 

This project is expected to demonstrate 

FR-2). 

In September, NASA and the German Ministry for Scientific Research agreed in principle that the second joint US/German satellite project will be an aeronomy research 

spacecraft. 

mum period, to study effects of solar radiation on the upper ionosphere. 

ment of the first German satellite, programmed for launching in 1968 to study the 

earth's radiation belts, progressed according to plan. 

third project, a joint U. S. /German space probe to the sun, was established. 

This spacecraft is to be placed in orbit in 1970,. during the solar maxiDevelopA basis for negotiating a 

Nearing launching readiness at year's end were the first ESRO (European Space 

Research Organization) spacecraft, the third British satellite (fir st to be constructed 

entirely in the U. K.) and Italy's SAN MARC0 II. All three are scheduled for launching on NASA Scout vehicles early in 1967, the first two from the U. S. Western Test 

Range and the latter to be the first orbital launching from an Italian Texas Towertype platform positioned off the east African coast near the equator. 

During 1966, the total of foreign experiments selected for flight on NASA satellites 

reached nineteen. These include experiments from the U. K., France, Italy, the 

Netherlands, and, for the first time, Israel. 

Of particular interest among the experiments suggested by the international scientific community are 69 proposals received from six countries for studies of samples 

of the lunar surface to be returned to earth by the APOLLO astronauts. These proposals are being evaluated by NASA along with those submitted by U. s. scientists. 

Sounding Rockets 

This year, for the first time, Spain and Greece entered into agreements with NASA 

for cooperative sounding rocket programs, bringing to 19 the total of countries 

having such arrangements with the United States. Rockets launched by NASA from 

Greece helped the world scientific community study the May 20 solar eclipse. On 

October 15, Spain launched the first of a series of meteorological rockets under one 

of two new cooperative projects with NASA. 

ects were negotiated with Argentina, Brazil, Germany, Japan, and the Netherlands. 

In addition, new sounding rocket projUnder agreements with Argentina and Brazil, twenty-seven sounding rocket launchings 

were conducted during the total solar eclipse of November 12. Agreement was reached with Germany and Brazil providing for the test flight in Brazil on a NASA rocket 

of German scientific instrumentation; this instrumentation is expected to be included 

in the cooperative U. S. /German radiation belt satellite. 

Science and Technology Agency agreed on coordinated test flights of Japanese and 

U. S. meteorological sounding rocket systems from Wallops Island, Virginia. 

Netherlands Laboratory for Space Research and NASA reached an agreement to 

include Dutch-built experiments as part of a solar physics package flown on a NASA 

NASA and the Japanese 

The 

45 
sounding rocket from White Sands, New Mexico. 

The Interamerican Experimental Meteorological Rocket Network (Exametnet) , established in 1965 by agreement with Brazil and Argentina, began active operations 

with fifty-three meteorological rocket launchings in 1966. Data was being exchanged 

through a central clearing house arrangement at NASA's Wallops Station. 

Other cooperative international sounding rocket projects continued under existing 

arrangements with Canada, Denmark, India, France, the Netherlands, Norway, 

Pakistan, Sweden, and the United Kingdom. 

Additional International Projects 

In the first arrangement of its kind, a Memorandum of Understanding was concluded 

between the European Space Research Organization (ESRO) and NASA, providing for 

purchase of launchings from the United States for ESRO spacecraft. 

The number of countries benefiting from the U. S. weather satellite program continued 

to grow. 

mission (APT) facilities which enable them to obtain directly, from a satellite overhead, cloud-cover pictures of local and adjacent areas. 

By the end of 1966, 31 countries had installed automatic picture transNASA continued to provide to the export control offices of the Departments of State 

and Commerce technical advice concerning the propriety of licensing the export of 

equipment and technology in the aerospace field. 

U. S. -Soviet Cooperation 

Experimental two-way transmissions of satellite weather data over a special sharedcost facsimile link between Suitland, Maryland, and Moscow began in September, when 

Soviet satellite data, including both cloud-cover photographs and nephanalyses, 

became available. In the meantime, reciprocal exchange of conventional meteorological data between the U. S. and the U. S. S. R. continued. 

Tracking Station Network 

Approvals were obtained from the United Kingdom for the establishment of tracking 

stations in Antigua and Grand Bahamas to support Project APOLLO, and negotiations for intergovernmental agreements covering the stations were in process. The 

agreement with the United Kingdom for operation of a tracking station at Winkfield, 

England, for support of scientific satellites was extended to December 31, 1967, as 

an interim measure pending completion of a new agreement. 

reached with Spain, continuing the existing NASA tracking station in the Canary 

Islands and expanding it to support Project APOLLO. 

Kano, Nigeria, was closed in December following completion of Project GEMINI, 

since it will not be required under the network reconfiguration for Project 

APOLLO. 

An agreement was 

The manned flight station at 

The ESRO/Alaska Station 

On November 28, an agreement was signed between the United States and ESRO for 

the establishment and operation of an ESRO telemetry/command station near Fair46 
banks, Alaska. 

The President had earlier (February 2, 1966) signed legislation making ESRO 

eligible to receive the benefits of the International Organizations1 Immunities Act in 

connection with its activities in the United States. 

The station is expected to be operational by the summer of 1967. 

The National Geodetic Satellite Program (NGSP) 

Denmark, Norway, Italy, Japan, Portugal, Iran, and the Netherlands agreed to the 

stationing of temporary geodetic satellite observation camera teams on their territory as part of the first phase of the National Geodetic Satellite Program. 

Personnel Exchanges 

One hundred fifteen scientists from 28 countries participated in postdoctoral theore - 

tical and experimental research programs at NASA centers. During academic year 

1965, 53 NASA international fellows were enrolled in U. S. universities. Sixteen of 

this group continued their studies into the September 1966 term; at that time, 29 

newly enrolled students began their studies. 

by their national or regional space committees. 

All were co-sponsored and supported 

NASA and national or regional space committees also co-sponsored 11 foreign 

students who attended summer institutes in the United States (The Summer Institute 

in Space Physics, Columbia University; The Environmental and Planetary Science 

Summer School, University of Miami; and The Bio-Space Technology Training 

Program, University of Virginia). 

Some 130 scientists, engineers, and technicians from six countries and ESRO were 

trained at NASA centers in payload engineering, telemetry, tracking, radar, 

meteorology, launch procedures, and range safety operations. During the year 

about 5000 foreign visitors -- representing scientific and technical organizations, 

government and overseas news media -- toured NASA Headquarters and the Agency's 

field in stallat ions. 

NASA- DOD CooDeration 

During the past year, the Aeronautics and Astronautics Coordinating Board (AACB) 

continued coordinating matters of mutual NASA-DOD interest. 

Interagency coordinating bodie s e stablished during the year include the Manned 

Space Flight Policy Committee, the Manned Space Flight Experiments Board, and the 

Space Applications Coordinating Committee for technical monitoring of NASA's 

Earth Resources Survey Program. 

New NASA-DOD 

The AACB coordinated FY 1967 facilities budgets for NASA and DOD after reviewing 

planned construction of new facilities and expansion of existing facilities for both 

agencies. 

were identified and eliminated. 

Areas of unwarranted duplication of aeronautical and space facilities 

The supporting Space Research and Technology Panel and the Launch Vehicle Panel 

of the AACB completed their reviews of advanced space propulsion systems. 

large liquid fuel engine program was reoriented to develop and demonstrate both 

NASA and DOD engine concepts at a common thrust level. 

capability in large solid motor technology, the two agencies are carrying on levelThe 

In order to preserve a 

47 
of -effort programs that supplement each other. 

space power systems was endor sed, with special emphasis on further development 

of the SNAP-8 system. 

The continuation of the long-life 

A study was completed on reusable launch vehicle technology. 

valuable guidance to both Agencies for future technology programs relating to reusable launch vehicle s and maneuvering re -entry spacecraft. 

provide more specific guidelines for developing the most meaningful technology will 

be made. 

This study provided 

Additional studies to 

Procedures were also established to provide for the efficient use of secondary payload space on the launch vehicles and spacecraft of both Agencies by cataloging and 

advertising available space. 

The Joint Navigation Satellite Committee Report, setting forth national requirements, 

future guidelines, relative costs, and technical merits of navigational satellite systems, was accepted by all member agencies (NASA, DOD, FAA, Commerce and 

Treasury). 

The Manned Space Flight Policy Committee considered policy matters related to the 

MANNED ORBITING LABORATORY, refurbishment of the GEMINI spacecraft, and 

cost-effectiveness comparisons of the TITAN IIIC and the SATURN I launch vehicles 

for future NASA missions. 

Arrangements were made for NASA to assist the Air Foree Systems Command in its 

study of Fundamental Space Principles, Applications, and Doctrine (Project SPAD). 

NASA is to provide this assistance by furnishing copies of ,reports on appropriate 

studies of future space systems and by providing informal consultative assistance to 

the AFSC Planning Group. 

Through NASA's Technology Utilization Program, steps were taken to make sure the 

Department of Defense would receive all applicable information or innovative ideas 

in all areas of space technology such as materials, propulsion, electronics, power 

sources fuels, etc., of potential value to DOD, are made available. 

NASA and the Department of the Air Force entered into an agreement wherein the 

Air Force will provide supply support for NASA's propellants and pressurants needs. 

Under the agreement, the Air Force Logistics Command will serve as single manager 

for propellants and pressurants where it is considered in the best interest of the 

Government. 

NASA and the Department of the Army completed arrangements for the Army Audit 

Agency to perform audits on that portion of NASA's Construction Program performed 

by the Corps of Engineers. Under this agreement the Army Audit Agency provides 

NASA with reports of its regularly scheduled cyclical audits and performs special 

audits as requested by NASA. 

NASA and the Defense Contract Administration Service (DCAS) developed a coordinated training course; through this course, DCAS instructors, trained by NASA, provided field training in NASA quality requirements to about 1,000 DOD quality assurance personnel who perform quality assurance functions on NASA contracts. 

48 
To promote the exchange of technical data resulting from ground tests and flight 

experiences, NASA has joined with the DOD services in support and management of 

the Interagency Data Exchange Program (IDEP). 

the Navy's Failure Rate Data Program (FARADA). 

NASA also took action to support 

NASA and the DOD continued their coordination in the X-15 and XB-70 Research 

Aircraft programs. The efforts were aimed at validating theory and wind tunnel 

data, and obtaining information on de sign, materials, and operational techniques 

applicable to future super sonic military and transport aircraft. 

The exchange of military and civilian personnel between NASA and the Department of 

Defense continued, with the major portion of the flow being to assist NASA. 

example, fifteen of the nineteen new NASA astronauts came from the military services. However, several NASA employees were detailed for tours of duty with the 

Air Force Systems Command in connection with the MOL and other programs and 

additional requests for the detail of NASA employees to the Air Force and the Navy 

were being processed. 

For 

Following the recent passage of the Marine Resources and Engineering Development 

Act, the Administrator of NASA was designated as an observer on the National 

Council on Marine Resources and Engineering Development. 

in the Council and in the activities of the Interagency Committee on Oceanography 

should advance the application of space technology to the National Oceanographic 

Program. 

NASA's participation 

Close cooperation between NASA and DOD in the field of aeronautical research 

continued. 

research and test-bed vehicles at NASA Research Centers. 

use of NASA wind tunnels during the year. 

Fourteen aircraft on loan from the Armed Forces were being used as 

The DOD increased its 

Other agreements entered into during the period with the Department of Defense or 

one of the individual Military Services included procedures for the funding and 

operating APOLLO Range Ships and Instrumentation Aircraft; detailing Navy and 

Marine Corps officers to NASA; loaning re search aircraft; extraterre stria1 mapping, 

charting, and geodesy support; and jointly investigating space program accidents. 

ORGANIZATIONAL IMPROVEMENTS 

NASA's Office of Space Science and Applications (OSSA) was reorganized to make 

better use of its developing manned flight capabilities: 

Office was redesignated the Manned Flight Experiments Office/OSSA. 

office serves as the principal interface between OSSA and NASA's Office of Manned 

Space Flight. An Advanced Mission Staff was established to improve coordination in 

advanced studies, supporting research and technology, and other efforts related to 

intermediate and long range planning. 

The Manned Space Science 

The new 

Also, the Communications and Navigation Programs Office and the Meteorological 

Program Office were consolidated into a new Space Applications Programs Office. 

The consolidation provides an improved focus for the growing number of relationships between NASA and other Government agencies in space applications programs. 

49 
Major organizational elements of the Kennedy Space Center were realigned to improve functional and program supervision. A second deputy position was e stablished to strengthen top management, and an Executive Staff was established to 

handle executive communication processes and management review. 

focal points were established for management systems and resources management; 

de sign engineering and development; technical support, and general housekeeping 

functions. 

Separate 

A Medical Re search and Operations Directorate was established at the Manned 

Spacecraft Center (MSC) to consolidate the diversified but interrelated medical 

activities. 

associated with manned space flight operations, and for directing the research to 

solve those problems. Also at MSC, a Science and Applications Directorate was 

established to handle the Manned Spacecraft Center's emerging science and applications-related responsibilities. 

This Directorate is responsible for identifying medical problems 

The Western Operations Office was closed and its functions were realigned under two 

component field activities reporting to the Headquarters Office of Industry Affairs. 

One of the components -- designated Western Support Office --provide administrative, technical, and related services to NASA programs and projects in Southern 

California and Nevada. 

overall NASA representation at North American Aviation, Inc., and support field 

installation projects at the contractor's site. 

The other component -- NASA Office, Downey -- will provide 

A NASA Resident Office at the Jet Pkopulsion Laboratory was formally organized 

and personnel of the former Western Operations Office's Contract Division were 

relocated at that Office. 

and responsibility for the procurement of the VOYAGER spacecraft and capsule 

systems. 

This realignment provides direct governmental capability 

INDUSTRY AFFAIRS 

NASA's policies, procedures, and practices involving the use of incentive contracts 

continue to mature in an orderly manner. The use of incentive contracting showed 

a three-fold increase during 1966, and NASA now has over 200 incentive contracts 

under administration, amounting to over $6 billion. 

NASA, incentive contract awards exceeded those made on a cost plus fixed fee 

basis. 

This year, for the first time in 

NASA further broadened its use of contract administration services available through 

DOD offices which are in the proximity of NASA contractors, or within the contractor's plant itself. By this arrangement, NASA contracts receive on-site attention by 

specialists intimately familiar with the contractor's operations. An agreement was 

reached with DOD, simplifying procedures to be used for reimbursing DOD for 

services performed. 

NASA and DOD have entered into an agreement whereby DOD will conduct contractor 

compliance reviews and complaint investigations for NASA under the Equal Employment Opportunity Program. 

After a trial perod, full implementation of the Contractor Performance Evaluation 

(CPE) System in NASA was approved by NASA management. A CPE Review Group 

50 
was established, and NASA contracts were being screened by the group for recommended inclusion in the system. 

During 1966, NASA continued to improve its government quality assurance activities. 

At contractor's plants, quality assurance functions are normally carried out for 

NASA by DOD field personnel. 

guidance for its field installations on improved management of these functions. 

NASA published a Handbook providing direction and 

The Headquarters Reliability and Quality Assurance Office began a formal program 

to evaluate the reliability and quality assurance activities of its field installations 

relative to procurement. 

The NASA internal cost reduction program resulted in savings of $200 million. 

Agency's major contractors, voluntarily participating in the contractor cost reduction program, reported savings of $280 million during 1966 for a total savings of 

$480 million. 

The 

NASA experienced a notable decrease in labor disputes leading to work stoppages 

during the year. 

ticularly at the John F. Kennedy Space Center, have resulted in reduction of work 

stoppages. While time lost during calendar year 1965 was 67,815 man days, this 

figure was reduced during 1966 to 31,423 man days. 

labor-management cooperation to ease the transition from construction projects to 

predominantly "industrial"-t-*e labor relations. 

veloping into the latter phase and the change appears to be developing as planned. 

Increased efforts in preventive labor relations management, parThe Agency is actively seeking 

Most NASA facilities are now de - 

TECHNO LOGY UTILIZATION 

NASA continued expanding dissemination of knowledge gained from aerospace work 

and to experiment with new approaches to transfer aerospace technology. 

year, the Agency entered into joint programs with the Office of State Technical 

Services of the Department of Commerce, the Atomic Energy Commission, the Vocational Rehabilitation Administration, the Office of Law Enforcement Assistance in 

the Justice Department, and the Small Business Administration. Preliminary stages 

of exploration toward joint efforts were reached with the Bureau of Mines. 

In the past 

The Department of Commerce's Office of State Technical Services (OSTS) has 

launched an effort to bring to all states, through state-designated agencies, scientific and technological information to fill the needs of business, commerce, and industry. 

sored Regional Dissemination Centers (RDCs), the OSTS recommended to all the designated state agencies "increased cooperation" with the RDCs based upon "the early 

and consistent success of the NASA/RDC program. " 

After thoroughly reviewing the capabilities of the established NASA-sponTo increase the store of scientific and technological information available for dissemination, the Atomic Energy Commission entered a cooperative program with 

NASA. Through this program, the Argonne National Laboratory (and, eventually, 

other AEC laboratories) will report innovations deriving from their research endeavors. 

Tech Briefs. This activity is modeled after NASA's Tech Brief program, established 

in 1964, which has reached a volume in published Briefs of over 1,300 -- a 100 percent increase in this year's effort compared to that of two previous years. 

Such reports will be published and disseminated in the form of AEC-NASA 

51 
NASA's Technology Utilization program also assisted in medical advancement through 

two new programs. 

exchange between NASA and the biomedical community by direct communication of 

new concepts to biomedical researchers. Additionally, these Teams and NASA information dissemination personnel began work with the Vocational Rehabilitation Administration under a formal agreement to apply space technology to the rehabilitation 

needs of disabled persons. 

Biomedical Application Teams were established to improve the 

The NASA Office of Technology Utilization and the Small Business Administration 

jointly began seeking a means of bringing aerospace knowledge to small industrial 

businesses to assist them in keeping abreast of technological changes. 

In an effort to bring NASA-generated scientific discoveries to the educational field, 

the Office of Technology Utilization in cooperation with the Oklahoma State University launched an experimental pilot program. The aim is to review, select, and 

prepare significant technical material stemming from NASA's R&D activity for 

incorporation in graduate engineering and physical sciences courses. In addition, a 

computer programs dissemination service was started at the University of Georgia. 

This service will make NASA computer programs more quickly available to the 

non-aero space community. 

52 
DEPARTMENT OF DEFENSE 

INTRODUCTION 

CHAPTER 

IV 

Three major actions and events highlighted the Department of Defense space and 

aeronautical activity during 1966. 

seven communications satellite repeaters and one experimental satellite into equatorial, near-synchronous orbit. 

of the space segment of a defense satellite communications system designed to meet 

unique and vital communications needs in support of national objectives. (2) A 

second TITAN IIIC was used to launch eleven DOD experiments and a modified 

GEMINI spacecraft. 

of the MOL program, the communications program, and the Aerospace Research 

Support Program. 

the C-5A, continued on schedule. 

(1) A single TITAN IIIC successfully placed 

This is the initial step toward orbital establishment 

The experiments and spacecraft provided test data in support 

(3) Development of the world's largest military cargo aircraft, 

SPACE DEVELOPMENT ACTIVITIES 

MANNED ORBITING LABORATORY (MOL) 

The MANNED ORBITING LABORATORY (MOL) is being developed to meet the 

following program objectives: 

a. Learn more about what man is able to do in space and how that 

ability can be used for defense purposes. 

b. Develop technology and equipment which will help advance manned 

and unmanned space flight. 

c. Experiment with this technology and equipment. 

Management of the MOL Program is being conducted under streamlined organizational 

structure in which the Director, MOL, reports directly to the Secretary of the Air 

Force. 

The past year has been devoted to the Contract Definition Phase in which sufficient 

technical data and costing information have been developed to specify in detail the 

optimum program. 

ration has been established, the development and flight schedule has been refined, 

procurement of developmental hardware has been initiated, and the program is 

moving progressively toward meeting the established objectives. 

Engineering definition has been completed, the baseline configuTwelve aerospace research pilots have been assigned to the MOL Program. 

addition to preparation for their flight duties, they are each assigned special areas 

on systems engineering and test operations as members of the MOL development team. 

In 

53 
In one of the series of TITAN I11 development flights from the Eastern Test Range, 

test data useful to MOL was obtained on the TITAN structure integrity and control 

capability, and on a modified GEMINI spacecraft. 

DOD and NASA will continue to coordinate fully their manned space flight efforts. 

Where feasible the Air Force will accommodate, on a minimum interference basis, 

such NASA experiments of a general scientific and technological interest as may be 

economically and effectively conducted. 

TITAN 111 Program 

The TITAN IIIC flight test program involved three flights in 1966. The mission of 

the first of these was to place seven Defense Communication Satellites and one 

Gravity Gradient Experiment in a near-synchronous orbit of 18, 200 nautical miles. 

It was one of the most complex earth orbital flights ever attempted. The eight 

satellites were placed in the exact orbit desired and are operating satisfactorily. 

The second flight plan was identical to the first. 

of eight Defense Communication Satellites. 

performance in flight, the payload fairing suddenly failed, leading to subsequent 

self destruction of the vehicle. 

could not be absolutely determined, it is believed that the payload fairing experienced 

structural failure. 

honeycomb fairing will be used for the next Defense Communication Satellite mission 

and all subsequent TITAN IIIC flights. 

In this case the payload consisted 

After some 79 seconds of flawless 

Although the exact reasons for this lack of success 

As a result, a metal fairing in lieu of the original fiberglass 

One objective of the third flight of the year was the test of a modified GEMINI heat 

shield. In addition, a series of scientific experiments was carried. The test was 

successful in every respect. The definition phase of the modified TITAN 111, known 

as the TITAN IIIM, was completed and long lead time procurement was initiated for 

the development phase. This configuration of the TITAN I11 will be used to boost the 

MANNED ORBITING LAB OR AT ORY (MO L) . 

Also during'this year the TITAN IIIB development program was completed on 

schedule in July 1966 by the successful R&D launch of the first vehicle from Vandenberg AFB. The TITAN IIIB vehicle, which consists of the first two liquid stages of 

the basic TITAN 111 plus an AGENA upper stage, was developed to meet polar orbit 

mission requirements. 

DOD Satellite Communications Activities 

To provide the prompt, reliable, secure, and flexible communications vital to the 

United States in support of its global responsibilities, to command its forces, and to 

control its weapons, the DOD has continued its efforts to exploit the demonstrated 

ability of orbiting satellite radiowave repeaters together with appropriately de signed 

surface terminals to provide such communications. 

Defense Communications Satellite Program (DCSP) 

The objectives of the Defense Communications Satellite Program are to conduct 

necessary satellite communications re search and development, and to establish an 

operational long haul point-to-point satel€ite communications system in a timely 

54 
manner. The DCSP is carried out by the three Military Departments with the Defense 

Communications Agency providing management and operational direction to coordinate 

the Departmental efforts. 

To accomplish these objectives, the DCSP is divided into three broad efforts as 

follow s: 

a. SYNCOM 

b. Initial Defense Communications Satellite Project (IDCSP) 

c. The Operational Defense Satellite Communications System (DSCS) 

SYNCOM I1 and SYNCOM 111, developed and orbited by the National Aeronautics and 

Space Administration, were used with various DOD terminals in 1966 for experimental 

system test activities and for passing operational communications. 

system was converted to operational status in July 1966 and is currently being employed 

as an alternate to cable and high frequency radio circuits between land terminals in 

Hawaii, Philippines, and Southeast Asia; a shipboard terminal installed on the 

USS ANNAPOLIS is also being used in this system. 

used for the remaining life of the satellites -- currently estimated to be about two 

years for SYNCOM II and five years for SYNCOM 111. 

The SYNCOM 

The SYNCOM system will be 

Initial Defense Communications Satellite Project (IDCSP) 

This project is designed both to provide an in-being research and development 

satellite communications system to demonstrate system feasibility on a world-wide 

network basis and to provide an early, though limited, operational capability to 

supplement the essential command and control communications system of the DOD. 

The first spacecraft-repeaters were successfully launched in June 1966. A single 

development model TITAN IIIC performed in near-perfect fashion to inject seven 

satellites and one gravity gradient stabilized test satellite into circular, equatorial 

orbit at a near-synchronous altitude of approximately 18,000 nautical miles. 

satellites were sequentially injected into orbit and each was given a small increase in 

velocity with respect to the preceding satellite to cause a "randomu dispersion of the 

satellites around the orbit. 

DOD is examining possible reasons for the failure, including the protective fairing 

surrounding the satellites. 

The 

A second launch attempted in August 1966 failed and the 

The IDCSP surface subsystem consists of newly developed ground and shipboard 

terminals. 

cation -- on the east and west coasts of the United States, and in Germany, Hawaii, 

and the Philippines. 

PROVIDENCE, flagship of the First. Fleet, in October 1966. 

end, terminals were being installed and checked out in Southeast Asia to support 

operations in that area. 

portable in a single aircraft, continued throughout 1966 with system testing beginning 

in November 1966. 

During 1966 ground terminals were established for world-wide communiThe first shipboard terminal-was tested aboard the USS 

As the year came to an 

Development of a smaller, lighter ground terminal, trans55 
The Operational Defense Satellite Communications System (DSCS) 

During 1966 the DOD continued planning and preparation for acquiring a truly 

operational satellite communications system which will take full advantage of our 

experience with the SYNCOM and IDCSP circuits and of advances in communications, 

spacecraft and rocket technology. System definition studies were completed and 

implementing direction was prepared. 

Tactical Satellite Communications (TacSatCom) Program 

Operational advances in such areas as strategic and tactical weaponry, transportation, and combat surveillance -- both in our forces and those of potential enemies -- 

place a related demand on improving our means for commanding the operating forces, 

providing them promptly with adequate intelligence and controlling their weapon 

systems. 

potential of their fire power and maneuver capabilities because of limitations on the 

means provided for command, control and communications. Recent Military Department studies have confirmed that important tactical communications requirement s 

could be met by sensibly designed satellite communication equipments and networks. 

Also, rapid national progress in the development of economical space boosters and 

sophisticated spacecraft in recent years suggest that properly de signed orbiting 

repeaters, used in concert with appropriate surface and near surface equipments, 

could go far toward meeting military tactical communication needs. 

Often, tactical combat forces are re strained from exploiting the full 

The program is directed toward meeting the needs of the highly mobile, lower 

echelon land, sea and air forces using very small, lightweight and relatively less 

costly tactical equipment in networks characterized by great flexibility and minimum 

control. During 1966, the Military Departments formed a Tri-Service Executive 

Steering Group (TSEG) to manage a joint research and development program with the 

following objectives: (a) to develop and test experimental space and surface satellite 

communications hardware, (b) to develop operational concepts for the confident 

military use in large scale communication networks, and (c) to demonstrate and test 

those concepts in an operational environment. 

The Army has the primary responsibility for the development of the experimental 

ground equipments; the Navy, the seaborne terminals; and the Air Force, the airborne terminals. 

launching the spacecraft/repeaters which the Services agree will meet their needs. 

Joint development projects ensure that only a minimum number of surface equipment 

types will be developed. 

The Air Force also has the responsibility for developing and 

A joint test program will be devised and implemented. 

Initial experiments are keyed to the launch of an Air Force-MIT UHF repeater by a 

developmental TITAN IIIC booster early in 1967. During 1966, the Military Departments developed, fabricated and installed suitable terminals in combat vehicle s, 

ships and aircraft in line with the joint test program to be implemented during 1967. 

Contractual action was also initiated in 1966 for a second satellite, one specifically 

designed to meet the goals of this program, for launch in 1968 using a developmental 

TITAN IIIC booster. By then, suitably designed surface terminals will be installed 

in a sufficient number of tactical vehicles, operational aircraft and Navy combat 

surface ships and submarines to permit adequate technical and operational testing 

in simulated and real tactical environments. 

tactical satellite communication system will depend on the results of the 1967-1968 

expe r im e ntal pro gram. 

The development of an actual operational 

56 
Experimental Communications Satellites 

Two experimental satellites, de signed and built by the MIT-Lincoln Laboratory under 

DOD sponsorship, were placed in orbit in December 1965 by a TITAN IIIC. 

Satellites, LES-3 and LES-4, were placed into a elliptical orbit rather than the 

planned circular, near- synchronous orbit; however, planned experiments were 

successfully conducted during 1966. 

to make accurate measurements of UHF propagation phenomena. 

at SHF, demonstrated the feasibility of using sensors to select, from a number of 

antennas, the one antenna pointing most directly toward earth so that the energy 

radiated by the satellites is directed to the earth. 

on electron density throughout the orbital path. 

and fabrication of LES-5, a larger UHF satellite to be launched in 1967. 

These 

LES-3 included a UHF transmitter and was used 

LES-4 operating 

LES-4 also yielded valuable data 

The Laboratory continued the de sign 

International Satellite Communications Discussions 

During 1966 the DOD held a number of discussions with friendly nations to acquaint 

them with the DCSP; initial reaction indicates considerable interest in the potential 

of satellite communications for military purposes. A Memorandum of Understanding was concluded with the United Kingdom for their participation in the research and 

development phase of the IDCSP. Arrangements were also made for Canadian participation in IDCSP research and development. 

The United States Ambassador to the North Atlantic Treaty Organization proposed a 

cooperative program to provide the NATO an early operational satellite communications capability. 

Spaceborne Nuclear Detection (VELA) 

Development of a satellite based nuclear detection capability for events occurring on 

the earth's surface to the outer reaches of deep space has been the design of the 

VELA Satellite Program. 

Advanced Research Projects Agency, it is conducted jointly by the USAF and AEC. 

Originally a research and development program of the 

There are six VELA satellites presently in orbit. 

pairs in 1963, 1964 and 1965. 

environment in space and on the operation of nuclear detection sensors in space. 

VELA program is providing an interim monitoring capability for detecting nuclear 

explosions occurring in the region from the earth's surface to deep space. Future 

launche s are planned to maintain the present system, in addition to continued re search 

on advanced space detection techniques. 

The satellites were launched in 

All six are still providing valuable data on the radiation 

The 

VELA satellites are launched from Cape Kennedy into near-circular orbits about 

60,000 nautical miles from earth. 

valuable contributions in techniques of solar storm forecasting. 

also provided a real-time radiation cover to the GEMINI manned space flights. 

The radiation background data has and is making 

The VELA program 

VELA satellites will continue to provide this important radiation detection service 

for future manned spacecraft flights. 

57 
Space Object Identification 

The Air Force and Advanced Research Projects Agency are cooperating on a continuing research program to determine the best means by which the physical characteristics of uncooperating objects in earth orbit can be obtained through observations 

by ground-based radar. The advanced techniques will be of value in obtaining diagnostic information on our own satellites in orbit and will serve as a prime source of 

technology for improving the capabilities of the Space Surveillance and Detection 

Tracking System (SPADATS). 

efforts in this area to Air Force management. 

Plans are being made for transfer of the ARPA research 

Geodetic Satellite 

The Department of Defense continued its active participation in the National Geodetic 

Satellite Program during 1966. The NASA's EXPLORER XXIX satellite (GEOS A), 

launched November 6, 1965, is being observed on a world-wide basis by DOD as well 

as other participating Government agencies. 

SECOR transponder, a NASA Range-Range Rate transponder and LASER reflector, 

an Air Force optical beacon, and a Navy Doppler beacon. 

EXPLORER XXIX carries an Army 

The NASA's PAGEOS A satellite launched in a 2000 nautical mile orbit in June 1966 

is currently being observed by DOD and the Coast and Geodetic Survey for establishing a world-wide Geometric net of 43 stations. 

sphere observed simultaneously against a star background from at least two ground 

stations. 

PAGEOS is a reflective 100' inflatable 

These projects will continue to provide more precise information about the earth's 

size, shape, mass and variations in gravity and precise determinations of locations 

for accurate mapping, charting, and geodesy. 

The Army Corps of Engineers has extended a continuous geodetic network from Japan 

to Hawaii using the SECOR (Sequential Collation of Range) satellite system. Three 

SECOR satellites, VI, VII, and VIII, with a newly develapedl hi@ zltitude performance 

capability, were successfully orbited in 1966. 

in VI1 is functioning favorably, and it is anticipated greater distances between stations 

will soon be possible. 

circling network designed to link all major geodetic datums, provide a new determination of the earth's equatorial radius, and provide scale to the PAGEOS satellite 

triangulation network. 

Of the three, the SECOR transponder 

Operations will begin in the near future on a 30-station globeDuring 1966, the Navy determined from Doppler observations, the positions of 21 

world-wide stations to an accuracy of t 25 meters with respect to the earth's center 

of mass. 

coefficients of the earth's gravitational potential. 

order have been published. 

NASA's Beacon B, Beacon C and GEOS A are being used for gathering the Doppler 

data. 

Additiowlly, the Doppler data was used to determine the harmonic 

Coefficients through the eighth 

The Doppler beacons in the Navy Navigation Satellites, 

In 1966, the Air Force completed two programs using the PC-1000 geodetic stellar 

cameras. 

Test Range with an accuracy of 10 meters (lo-). 

were used to provide comparative data with the SECOR and Doppler systems. 

Trinidad has been related geodetically to Cape Kennedy for the Eastern 

The 

In the U. S., the PC-1000 cameras 

58 
three systems, in turn, were checked against the Coast and Geodetic Survey's super 

accurate base line. Favorable results were obtained. Currently, the Air Force is 

engaged in establishing eighteen stations world-wide for defining the GEOS orbits 

more precisely and to assist in verifying major datums of the world. 

Navy Navigation Satellite System 

The Navy Navigation Satellite System has been in operation since 1964. 

are installed in all Fleet Ballistic Missile submarines and all attack carriers deployed 

to Southeast Asia to up-date the ships' inertial navigators and to insert data into the 

inertial navigators of aircraft prior to launch from the carriers. 

Receivers 

During 1966 the use of the Navigation Satellite System for up-dating an aircraft's 

inertial system was found feasible. Flight tests were performed using shipboard 

equipments with an existing inertial navigator and an interconnection system that was 

considerably less than optimum. Now that the feasibility of the technique has been 

shown, a receiver designed specifically for the aircraft application will be developed 

and tested to determine the potentials of its operational use in military aircraft. 

Also during 1966 the accuracy of the system was improved by the use of more detailed 

and accurate knowledge of the earth's gravity field with a consequent improvement in 

predictability of a satellite's position. The system is also now being used by oceanographic and range instrumentation ships as a primary source of accurate, all-weather 

PO sition data. 

To give artillery units the capabilities of locating themselves accurately in relation 

to one another, a 50 lb. navigation satellite receiver suitable for carrying as a backpack was developed. 

obtained by one satellite pass without the necessity for laborious, time-consuming and 

sometimes dangerous conventional 4th order survey techniques. Further development 

work will be done to make this receiver suitable to actual field conditions. 

Marine Corps and Army plan to exploit the technique if it proves operationally 

feasible. 

Accuracies equivalent to those obtained by surveying can be 

Both the 

Met e o r ol o g i c a1 S y s t e'm s 

The first NASA TIROS Operational System satellite with a direct readout capability 

was launched in 1966. 

Asia were provided with equipment for utilizing this technique. Thereby, for the 

first time the task force commander or captain of a ship was able to determine in 

real time the actual cloud conditions in the Task Force area of operations with a 

single overhead pass of the satellite. 

Concurrently Navy attack carriers deploying to Southeast 

SPACE GROUND SUPPORT 

DOD National Ranees 

The realignment of the National Range complex continues as program support requires 

change. On the Eastern Test Range, the San Salvador Station was deactivated and both 

Advanced Range Instrumentation Ships were moved to the Pacific Ocean. 

Western Test Range, Vandenberg Air Force Base was expanded with the acquisition of 

Sudden Ranch. Several older launch complexes at Vandenberg AFB are being modified 

On the 

59 
to accommodate the newer versions of THOR and TITAN space boosters. 

Instrumentation improvements on the Department of Defense Range s were limited 

by available funding. 

ing radar accuracies and converting the telemetry systems from the Very High Frequency (VHF) spectrum to the Ultra High Frequency (UHF) band. 

directed action to relieve some of the congestion in the 200 to 400 megacycle spectrum. 

Instrumentation improvements for re -entry and terminal measurements have been 

initiated and must continue next year to meet the needs of ballistic missile systems 

which will be flying on the Eastern and Western Test Ranges. 

The major modifications now underway are directed at improvThis latter is a 

The instrumentation system for the first APOLLO ship (the VANGUARD) has been 

completed and this ship is now undergoing engineering tests. The second of these 

five range ships (the REDSTONE) is nearing completion and will be delivered about 

February 1967 for testing and operational shake-down. The first two of eight APOLLO 

range instrumentation aircraft were delivered in November 1966. 

Conversion of the Satellite Control Facility to the Ultra High Frequency spectrum 

passed a significant milestone on 13 October 1966 with the successful flight test of 

the Space Ground Link Subsystem. 

type hardware to support this and subsequent flight tests. 

to equip the entire network with this system which permits transmission of more than 

a million bits of data per second between space vehicles and ground terminals. 

new UHF antenna is now being installed at the Hawaiian Tracking Station and work has 

been initiated to install a similar high gain antenna at the Guam Tracking Station. 

Two tracking stations were equipped with protoProduction is now underway 

A 

TITAN I11 Facilities at WTR - MOL Launch Complex 

Site preparation for the TITAN 111 launch facility at WTR was completed in August 

1966. This work included land grading and installation of access roads and utilities. 

The next phase of facility construction, including items specifically associated with 

MOL, has been approved, and construction will commence in the early part of 1967. 

Space Detection and Tracking System (SPADATS) 

SPADATS operation is under the control of the North American Air Defense Command 

(NORAD). 

Force (SPACETRACK) and the Navy (SPASUR). 

detection and tracking of all foreign and friendly earth orbiting objects. 

Service and NASA space programs such as GEMINI, APOLLO and the MANNED 

ORBITAL LABORATORY (MOL) is also a function of SPADATS. The SPADATS 

capabilities are constantly being evaluated for possible improvements in operation 

and for required equipment modifications and additions. Advances have been made 

in the capability to provide more precise predictions of satellite orbital positions 

and determine space object decay times and locations. 

enabling the U.S. to advance our knowledge of the earth's atmosphere, shape and of 

various extra terrestrial effects upon orbital flights. 

It consists of detection and tracking radar systems assigned to the Air 

SPADATS is responsible for the 

Support of 

Such improvements are 

60 
AERONAUTICS DEVELOPMENT ACTIVITY 

C-5A Heavv Logistics TransDort Aircraft 

The airframe/system integrating contractor began on schedule, in August, the manufacture of what will be the world's largest military cargo aircraft. Final assembly of 

the first aircraft will begin in November 1967. Roll-out is scheduled to occur in 

February 1968. Some major technological 

advances in design are: high by-pass ratio turbofan engines (TF-39) featuring very 

low specific fuel consumption; an in-flight electronic "trouble shooter" for flight 

safety and reduction in ground time; a straight-through loading feature, made possible 

by large cargo doors in both nose and tail, for fast ground turn-around time; and a 

landing gear with high flotation to permit the massive aircraft to tread softly over 

relatively unprepared fields and with a Itkneeling" feature to facilitate cargo loading. 

First flight is planned in June 1968. 

A B-52E will serve as the flight test bed for the TF-39 turbofan engines and was made 

available to the engine contractor in October. 

planned in April 1967. 

installed dimensions (with cowling) will be 8. 5 feet in diameter and 26.0 feet in 

length. 

First flight with the test engine is 

The TF-39 engine is in the 41,000 pound thrust class and the 

Working with the airframe / system integrating contractor is a team of subcontractors 

spread across the United States, who will produce 60 percent of the C-5A by aircraft 

weight. 

The Air Force began designing some new facilities to support testing of the C-5A. In 

order to ensure sufficient cold air for accomplishing the cold weather tests of the 

high bypass engine, the Climatic Laboratory at Eglin AFB, Florida, will be modified 

to increase the amount of cold air so as to permit a cold soak period and engine run 

up at -65OF. 

tests, a large hangar and engineering office is being designed. 

C-5A requires a new hangar and modification to several other smaller facilities in 

order to support the test program. 

At Edwards AFB, California, where the aircraft will undergo flight 

The large size of the 

F-111 

The F-111 System Program was marked by satisfactory progress as well as a significant increase in program activity during the past year. 

the F- 11 1A flight envelope was extended to its maximum speed and altitude and a 

total of six separate versions of the F- 11 1 aircraft were under development. 

By the end of the period, 

As of 4 October 1966, thirteen F-111A aircraft and four F-ll1B aircraft had been 

delivered to the flight test program. Contractor Category I testing was in progress 

at Fort Worth, Texas, Eglin AFB, Florida, and Peconic River, Long Island, New 

York Air Force Category I1 Testing was also initiated at Edwards AFB, California, 

during the year. Over 992 flights and 1,634 flight test hours were accumulated by 

the end of the reported period. Of these, 359 flights were supersonic and 95 flights 

were in excess of Mach 2.0. 

To take full advantage of advancements in avionic system development since the 

F- 11 1A was initially conceived, an improved avionics system package has been 

selected for production installation in the F- 11 1A aircraft. This Mark I1 Avionics 

61 
equipment is designed to provide increased reliability and increased air-to-ground 

and increased air-to-air weapon delivery capability through use of improved navigation and radar equipment. 

Development of a RF-111A reconnaissance version of the F-111A was approved on 

28 October 1965. 

commonality with the basic F- 11 1A. Reconnaissance sensors will be located in the 

weapons bay on a removable pallet type structure. Photographic, radar, thermal, 

and electronic sensors will be carried. 

The configuration of the RF-11 1A will be based on maximum 

Congressional approval was obtained and development of a Strategic Bomber version 

of the F-111 was initiated in February 1966. The FB-111 utilizes the basic F-111A 

design but has improved avionics and structural improvements for long range, high 

payload missions. The FB-111 will be capable of delivering nuclear weapons, short 

range attack missiles (SRAM) or conventional bombs over long ranges with great 

accuracy. 

The F-111 Cooperative Logistics Arrangement between the U. S. and the U. K. 

dated 5 April 1965 was implemented by a sales order for 50 F-111 aircraft on 

12 March 1966. The U. K. F-111 Program is being managed in the Air Force by 

the F- 11 1 System Program Office (SPO) in the same manner as the Air Force F- 11 1 

Program. RAF personnel are assigned to the SPO to assist the System Program 

Director and provide the necessary technical management interface between the two 

countries. The U. K. F-111 configuration will have design features of both the 

F-ll1A and the FB- 11 1 aircraft, and include British furnished equipment as well. 

Royal Australian Air Force (RAAF) liaison activities relative to their order for 

F- 11 1A aircraft continued to increase during the year. 

Advanced Tactical Fighter 

The Air Force is studying an advanced tactical fighter (FX) for introduction into the 

Tactical Air Command. 

Based on the results of contractor studies and additional DOD examination, the Air 

Force will recommend acquisition of this new fighter. 

Aircraft will have performance superior to the projected threat. 

The weapon system is to replace F-I04 aircraft and the F-4. 

As presently envisioned, the 

The Navy has indicated a requirement for a multi-mission carrier based fighter-attack 

aircraft (VFAX). The requirements of the Navy and Air Force for this new aircraft 

are in many respects similar, and the Services are studying the possibility of meeting their joint requirement s with a common aircraft. 

A-7 Light Attack Aircraft 

The Navy A-7A is a turbo-fan powered, single place, visual attack aircraft. 

placing the A-4 light attack plane, the A-7A has a more versatile ordnance carrying 

capacity, an improved weapons delivery accuracy capability and an increase range. 

De sign and engineering concepts have emphasized simplicity of systems to maximize 

reliability, maintainability and operability at minimum cost. The first operational 

A-7A's were delivered to Navy Fleet Training Squadron VA-174 at Cecil Field on 13 

October 1966. 

Re62 
The program for the Air Force A-7D version of the Navy A-7A is progressing on 

schedule. 

development and will be in production by early 1968. 

The aircraft will be equipped with the Allison TF-41 engine which is under 

XB -70 

A total of two XB-70 aircraft were built. 

occurred on September 21, 1964, and the first flight of Number 2 occurred on 

July 17, 1965. 

The first flight of the Number 1 airplane 

The Number 2 airplane was more sophisticated than the Number 1 airplane. 

equipped with more test instrumentation than was provided in the Number 1 airplane, 

and it contained some improved systems components. 

It was 

Both airplanes were used in a Flight Test Program from the first flight of the first 

airplane until the Number 2 airplane was lost in an accident on June 8, 1966. Objective s of that program were to establish airworthine ss of the airplanes, inve sigate 

the de sign feasibility, determine handling qualities, and demonstrate Mach 3 flight 

for 30 minutes. 

pr o g r am. 

Those objectives were met. A total of 186 hours were flown in the 

The second phase of the XB-70 program consists of a joint AF/NASA program 

directed toward some 23 flight test objectives and 76 flights, top priority being on 

sonic boom test. 

was delayed, however, pending an investigation of the June 8 accident and modification to the remaining XB-70. 

The joint program was to have begun on 16 June 1966. The project 

On 3 November the Number 1 aircraft resumed its flights. 

flights will be made during an 18 month period in order to meet the flight test objectives. If all the flights are not made, however, it appears that a sufficient number 

can be made to meet a high percent of the test objectives. 

It is planned that 75 more 

COIN Aircraft 

The first flight of a COIN OV-1OA aircraft was on July 16, 1965. 

lems affecting aircraft performance have delayed some aspects of the development; 

however, the production delivery date for USAF and Marine Corps aircraft is not 

expected to slip more than a month or two. 

Engineering probThe Navy conducted early evaluation testing of the OV-1OA. 

Navy Preliminary Evaluation (NPE) program was completed on 21 March 1966. 

Several deficiencies were discovered and the Navy/Contractor team immediately 

initiated a vigorous "get well" effort. The corrective action was successful and a 

contract for 185 production aircraft (109 USAF and 70 USMC) was released on 15 

October 1966. 

increase in wing span and up-rating of the turboprop engines. 

The first phase of the 

The most significant changes to the aircraft configuration included an 

The OV-10A is a twin engine turboprop 

performance from unimproved fields, roads and aircraft carriers without using 

arresting gear. 

for light logistic duty carrying five paratroopers or 3000 pounds of cargo. 

aircraft wish short takeoff and landing 

In addition to weapon delivery missions, the aircraft may be used 

Variants 

63 
of the OV-10 are presently under study for USAF strike reconnaissance and light 

transport missions. 

This aircraft may replace USAF 0-l's, T-28's, and A-1E's. Marines plan to use 

the OV-1OA in the helicopter escort and reconnaissance role. 

Heliconter 

The Department of Defense is developing helicopters which will have significantly 

improved operating characteristics and effectiveness over those now in operation. 

This need has been accentuated by the Army's recently adopted airmobile concept 

which places almost complete reliance on helicopters for battlefield mobility. 

Engineering development of the AH-56A (Advanced Aerial Fire Support System) was 

initiated by the Army. 

avionics and fire control subsystems into a weapons platform capable of effectively 

employing various combinations of point and area fire weapons in support of ground 

combat operations. The Army has contracted for ten prototype AH-56A helicopters. 

The design of this helicopter will integrate armament, 

Pending availability of the optimized AH-56A, and in response to an urgent operational 

requirement for an interim improved armed helicopter in Vietnam, the Army is procuring the AH-1G (COBRA) helicopter. 

the UH- 1 helicopter. The AH- 1G armament includes a flexible chin turret and wingmounted pods which are capable of employing machine guns, rockets and grenade 

launchers. First flight of the Army AH-10 prototype was made on 15 October 1966. 

Flight test reports are highly favorable. Production deliveries of the AH-1G will 

begin in the spring of 1967. 

This helicopter is a streamlined version of 

During 1966 the Air Force used the HH-3E helicopter as its primary Combat Aircrew 

Recovery Vehicle. 

refuelable HH-53B's. 

hover ceiling and speed over the HH-3E now in use. 

bility to recover downed airmen from enemy territory, the Air Force is conducting a 

continuing evaluation programof various VTOL and advanced helicopter de signs that 

are capable of quick reaction and increased performance in hover and range. 

Reprogramming approval was obtained to procure eight air 

These helicopters will provide a substantial improvement in 

To improve further its capaV/STOL Development 

The Army XV-5A (Fan-in- Wing) research program was completed in September 1966. 

The two test aircraft accumulated over 150 hours flying time in approximately 350 

flights. 

the other completed the Army program and was undergoing a follow-on Navy and Air 

Force sea air rescue evaluation when it crashed during rescue simulation in October 

1966 -- the cause not yet determined. 

are therefor e indefinite . 

One aircraft crashed on 21 April 1965 as a result of a control malfunction; 

Plans for developing a fan-in-wing aircraft 

During CY 66 the three Services successfully conducted individual operational evaluations of the XV-6A (P. 1127) aircraft to perform missions relatedto their specific 

areas of interest. The XB-6A diverted thrust aircraft completed the tripartite 

(US, UK, FRG) V/STOL operational concept evaluation in England during 1965. 

U.S. National Trials of the six research aircraft -- all built in England -- were 

conducted by the U. S. Army, Navy and Air Force from April through July 1966. 

64 
Major objectives of the overall program, involving 1, 196 flights, were to evaluate 

flight operating procedures, transition techniques, V/STOL aircraft suitability to 

operating environments, logistic implications, and the various modes of take -off and 

landing. 

the Air Force. 

assigned to the Air Force at Edwards Air Force Base. 

unilateral tests to study further the flight characteristics and handling qualities of 

the XV-6A. 

experience in V/STOL aircraft for future development programs. 

Additional follow-on flights and studies are being conducted by NASA and 

Two aircraft are on loan to NASA for technological studies and four 

The Air Force will conduct 

The aircraft will also be used to check out additional pilots to build up 

Members of the XC-142A Tri-Service Test Force at Edwards Air Force Base have 

operated this tilt-wing V/STOL transport aircraft from unprepared terrain (barren 

desert), semi-prepared surfaces (sod, gravel, sand, plastic membrane, metal pads) 

and normal runways. 

Take-Off and Landing) and hover modes to ascertain operational suitability. 

18 May 1966 an XC-142A investigated initial aircraft carrier compatibility when 41 

take-offs and landings were made on the USS BENNINGTON off the coast of California. 

ing of which was the dropping of 4100 pound load while hovering ten feet above the 

ground. 

hoisting of a man from a life raft into the XC-142A which was hovering 100 feet overhead. 

XC-142A's ability to operate from an Army field environment. 

tion is scheduled for April-August 1967. 

of the C-142 tilt-wing turbo prop aircraft were completed in September by the USAF. 

A decision on the purchase of additional C-142's is pending. 

Take-offs and landings were accomplished in the STOL (Short 

On 

Several methods of cargo air drop have also been demonstrated, the most demandThe rescue potential of the XC-142A was investigated and culminated in the 

The Army is preparing an operational plan to conduct an evaluation of the 

The operational evaluaConfiguration studies for a follow-on version 

The X-22 rotating ducted-propeller aircraft program suffered a serious setback in 

August 1966 when one of the two test aircraft experienced hydraulic systems failures 

and crashed at Buffalo, New York. 

systems controlling ducted-propeller orientation will correct this particular problem 

on the remaining aircraft, the program is being re-evaluated to determine the readjustments necessary to complete this program. 

While minor design changes in the hydraulic 

Contract definition of the V/STOL Assault Transport (previously referred to as the 

CX-6) was deferred pending the results of several on-going studies which should 

determine the requirements for a transport of this size. The program originally 

envisioned an aircraft with a 17. 5 ton payload to replace the C-130 in the mid 1970's. 

Design studies had configured the aircraft as a fan-in-wing type V/STOL vehicle. 

X-15 Research Aircraft Program 

The three X-15 aircraft are being used primarily as test beds to carry a series of 

experimental payloads in support of environmental studies, the development of 

improved components for future aerospace vehicles, and basic aerothermodynamic 

research. 

The X-15's were designed to achieve speeds of up to Mach 6. Following an accident 

in November 1962, X-15 Number 2 was rebuilt and modified to achieve Mach 8. Development (primarily of ablative material) leading to expansion of the flight envelope 

from Mach 6 to Mach 8 is continuing. 

65 
Highest speed attained to date is Mach 6. 1 and highest altitude 67 miles. 

speed and altitude capabilities, along with the high degree of reliability attained, make 

the X-15 ideally suited for its missions. 

These high 

The USAF sponsored X-15 experiments are scheduled to be completed in December 

1967. 

a scramjet engine, high temperature structures, and a delta wing. 

The experiments planned by the NASA in the CY 1968 - 73 time period include 

SUPPORTING RESEARCH AND TECHNOLOGY 

Over-the -Horizon Radar 

The Department of Defense developed OTH radars, using the ionospheric reflection 

of radar energy technique, have demonstrated a capability to detect missiles and 

aircraft beyond the radar or line-of-sight horizon. Instead of being limited to detection ranges of several hundreds of miles, the OTH technique provide ranges of several thousands of miles. 

objectives of improving our missile early warning capabilities and operational aircraft movement observations and for possible application to air traffic control 

operations. 

Laboratory and field evaluations are continuing with the 

Spacecraft Technology and Advanced Re-entry Tests (START) 

The START program consists of four hardware oriented projects: 

ASSET. 

consisted of six THOR boosted flights from the Eastern Test Range. 

last of these radiatively cooled vehicles was flown in 1965. 

(Aerothermoelastic Structural Systems Environmental Tests) 

The 

PRIME. 

four flights of a small unmanned ablatively cooled lifting body from the 

Western Test Range. These vehicles, which can be maneuvered by means 

of aerodynamic controls, will test the speed range from hypersonic reentry to approximately Mach 2.0 where they will be recovered by parachute. 

(Precision Recovery Including Maneuvering Entry) encompasses 

PILOT. 

Base by a joint AF/NASA test force. 

launched from B-52 aircraft to investigate the trisonic velocity spectrum 

from Mach 2.0 to horizontal landing. 

(PIloted LOW-speed Tests) will be flown at Edwards Air Force 

This single piloted vehicle will be 

RMS. (Re-usable Multipurpose Spacecraft) is in the early stages of study. 

In-house Air Force studies have been completed and follow-on contractor studies 

are underway. 

will insure a least cost approach to Air Force requirements. 

These studies will serve as a basis for vehicle selection and 

The four PRIME flights will be flown in the period from December 1966 through 

June 1967. 

continue into 1970. 

Flight testing of the PILOT vehicle will start in October 1967 and 

66 
Space Power Equipment 

The DOD continued to develop various concepts for meeting anticipated electrical 

power requirements of future satellites. The accomplishments of 1966 include further 

development of fuel cells for unmanned satellites and fabrication of a prototype window 

shade solar cell array. 

The fuel cell is an electrochemical device which converts hydrogen and oxygen to useful electricity, heat and water. 

batteries. Successful completion of this program will increase power and life over 

current missions, increase payload weight through power supply weight reduction and, 

in general, allow missions which are presently impossible. 

Present unmanned short life vehicles use primary 

Solar cells in conjunction with rechargeable batteries have been used to provide 

electricity in the majority of long duration space vehicles to date. 

cell arrays presently under development have great potential for weight and volume 

reduction combined with simple reliable deployment and retraction. 

advancement will reduce vulnerability and increase maneuverability of space vehicles. 

Arrays are stored in a rolled up window shade configuration; arrays are deployed and 

retracted with the aid of extendable rods. 

Flexible solar 

The latter 

Rocket Propul sion Te chnology 

The three Military Departments maintain exploratory and supporting re search and 

technology programs in rocket and missile propulsion which are designed to provide 

the technological base for advanced rocket-propelled weapon systems for tactical, 

defensive, strategic, and space missions. The technical content of these programs 

is coordinated among the three Services and with NASA to give priority tb the missions 

of greatest interest to each agency and to avoid redundant effort, except by design. 

These exploratory development programs initiate, evaluate, and selectively develop 

new propellants, novel propulsion concepts, and advanced componentry. They in turn 

generate advanced development programs which consolidate selected exploratory 

development advances and demonstrate them in the form of integrated prototype 

engines for specified missions. 

Thus, the exploratory development program of the Air Force us currently supporting 

five advanced development programs. 

liquid engine of sufficiently improved performance to make possible a one-stage intercontinental ballistic missile. 

employing the hydrogen-oxygen propellant system for high-energy booster stages. 

This program which will demonstrate a 250,000 pound thrust modular engine for a 

variety of space applications is being closely coordinated with NASA by a Subpanel of 

the Aeronautics and Astronautics Coordinating Board on Advanced Cryogenic Rocket 

Engines. 

fluorine engine with deep throttling and multiple re start capabilities for satellite 

inspection and intercept missions requiring great versatility and the maximum in 

velocity increment. This engine demonstration will bring to fruition 20 years of 

exploratory development in the technology of hydrogen-fluorine rocket engines. 

the tactical field, the Air Force is mounting an advanced development program in airlaunched rocket propulsion. This program is designed ta develop and demonstrate three 

desired attributes of air-to-air and air-to-ground propulsion system: great ruggedness 

and resistance to environmental extremes; command-controlled thrust magnitude 

One of these is a modular storable high-pressure 

Another program is developing two competing concepts 

A newly started advanced development program will demonstrate a hydrogenIn 

67 
variation for choice of trajectory and end-game maneuvering; and use of air-augmentation for extended range in volume-limited systems. Closely related to the air-augmentation programs is an advanced development effort in the area of supersonic comSustion 

ramjet propulsion. This program is of interest in connection with the ultimate development of a composite scramjet rocket engine capable of operating efficiently at sea level, 

in the upper atmosphere and in space. 

reusable spacecraft and reusable launch vehicles. 

It represents a potential propulsion system for 

The Army in cooperation with the Advanced Re search Projects Agency is developing 

the technology of high-acceleration solid rockets for advanced missile interceptors, 

requiring extremely short reaction times and the ability to perform high-G and 

high-Q maneuvers. This has involved the development of high-burning rate propellants 

and novel means of achieving thrust vector control through external burning. 

Army is also sponsoring the development of smokeless propellants for tactical field 

missiles. 

The 

The Navy is pur suing an advanced development program to realistically demonstrate 

the performance gains that can be realized by employing ram air to augment the 

thrust of solid rocket motors for both tactical and strategic weapon applications. 

This program will culminate in flight demonstrations of five prototype missiles, and 

these data will serve the thrust augmentation interests of all three Services. The Navy 

is also developing the technology of advanced throttleable prepackaged liquid rocket 

motors, which may operate interchangeably in a ramjet mode by command control. 

Gravitv Gradient Stabilization for Satellites 

A two-axis gravity gradient stabilized satellite was placed in equatorial, near- synchronous orbit in June 1966 as a part of the first launch of the Defense Communications 

Satellite Program. While not entirely successful, this experiment did demonstrate 

that gravitational forces at an altitude of about 18,000 nautical miles are useful in 

stabilizing a satellite to point toward the earth. 

Following several experimental gravity gradient satellites launched over the past few 

years the Navy utilizes Z-axis gravity gradient stabilization on all navigation satellites. 

The Department of Defense Gravity Gradient Experiment (DODGE) will attempt to use 

simple extendable booms and magnetic damping techniques to stabilize a satellite in 

3 axe s at near - synchronous altitude. 

In addition, a multi-purpose Gravity Gradient Experiment (DODGE-M) will be capable 

of carrying a number of technology experiments to synchronous altitude. 

Despun Satellite Antenna (DATS) 

An experimental electronically de spun communications antenna was fabricated during 

1966 and was undergoing tests at the end of the year prior to being launched on an 

experimental satellite early in 1967. The despun antenna will improve the efficiency 

of satellite communications repeaters by directing radiated energy toward the earth 

rather than dissipating a large portion of this energy into space, and by offering a 

larger absorption cross section for transmissions directed toward it from the earth. 

68 
Pro i e ct HARP 

The joint U. S. -Canada high altitude research program (Project HARP) continued to 

develop techniques for >robing the upper atmosphere with gun-launched sensors. 

preliminary research launcher is a modified, smoothbore, 16-inch gun with a 119- 

foot barrel, installed on Barbados in the West Indies. Fiberglass plastic rocket 

bodies have been successfully developed and tested. Rocket grains, rocket components and hardened telemetry components have withstood the 10,000 g acceleration 

associated with a gun launch. An improved powder ignition system has produced 

higher muzzle velocities. 

The 

During 1966 an extended 16-inch modified gun was installed at the Highwater Test 

Facility in Canada for horizontal test firings of rocket and guidance control systems. 

Another extended 16-inch gun has been installed at the Yuma Proving Grounds in 

Arizona to vertically fire recoverable rocket guidance components and to collect 

upper atmospheric wind information over this desert testing range. 

During 1966 there were approximately 50 vertical firings with the 16-inch gun to 

gather upper air wind and electron density measurements and to test the engineering 

design. The vertical soundings, taken to a maximum height of 475,000 feet, revealed 

upper atmospheric winds in excess of 200 knots. 

showed very marked wind changes in speed and direction over short time intervals. 

This phenomena had hitherto been undetected. 

The hourly measurements made 

Solar Radiation Monitoring Program 

SOLRAD VIII was launched on a NASA Scout in November 1965 continuing a series of 

solar X-ray monitors begun by the Naval Research Laboratory in 1960. 

tions during 1966 suggest that the coming solar maximum, 1968-69, will equal or 

exceed the level of activity reached at the previous maximum, 1957-58. 

evidence indicates that an increase in background solar X-ray emission can be 

interpreted as a precursor of flare activity and the subsequent disruption of radio 

communications and may provide early warning of energetic particle fluxes hazardous 

to manned operations in space. 

The observaAccumulated 

X-ray astronomy is the most rapidly developing category of space astronomy. 

shows all the ingredients of a fundamental new discovery that has characterized radio 

astronomy for the past quarter century. 

the energy production mechanisms of the most powerful cosmic sources. 

It 

Further observations are planned to reveal 

Turbojet Engines 

This area of research and development effort has made considerable progress during 

the year. Four new aircraft engines are in the initial stages of development. 

C-5A Engine, 

class and is scheduled for completion of qualification tests in September 1968. 

This engine has entered the development stage. It is in the 41,000 lb. 

Vertical Take-Off Aircraft Lift Engine, 

U. S. /U. K. development program. Government to Government and contractor to 

contractor agreements have been signed. 

mid 1966. 

This engine is being developed as a joint 

The development program started in 

69 
Vertical Take-Off Aircraft Lift-Cruise Engine. 

vectoring device so that the thrust may be used for either lift or cruise. 

tractors are in competition for this program. 

and system development will begin about July 1967. 

This advanced engine will have a 

Three conA single contractor will be selected 

Advanced Strategic Aircraft Engine. 

gram to do the initial development of an engine which could be used for strategic 

The Air Force presently is conducting a proaircraft in the future. 

efficiently over a wider range of speeds and altitudes than has been possible previously. 

This engine is unique in that it is designed to operate more 

The demonstration phase is planned to be completed in July 1967. 

Instrument for Mass Measurement Under Weightless Conditions 

During 1965, the Air Force undertook a development effort to devise a method for 

accurately making mass measurements in a weightless flight environment. 

Aerospace Medical Division has produced such a device which is considered to be a 

major accomplishment in support of manned space flight. 

The 

The present configuration consists of a 6" x 8" x 9l' package which weighs approximately 15 pounds. 

from 25 grams (0.1 pound) to 500 grams. 

same package can be used for items from one-half to 100 plus kilograms. 

present accuracy ranges from .03 of 1% at lower masses to .01 of 1% at masses in 

excess of one pound. 

device is more accurate in the weightless environment as has been demonstrated in 

"zero-g" aircraft flight trajectories. 

It has the capability to determine accurately the masses of items 

By merely changing the platform, the 

The 

Using the principle of the linear spring/mass pendulum, the 

The necessity to measure weight changes during space flight and to be able to assess 

as a function of elapsed time the body fluid changes which occur have been considered 

as a major requirement of the U. S. space flight program by the Medical and BioSciences community. The ability for accurate determination of input and output from 

astronauts in space flight in order to determine body fluid balance and body weight 

changes is now possible. 

Airborne Warning and Control System 

The Airborne Warning and Control System (AWACS) is being considered for overland 

operation in support of the Air Defense Command and Tactical Air Forces deployed 

world-wide. 

completed by different contractors and reviewed by the Air Force. The studies had 

been initiated to determine if an effective AWACS was within the state-of-the-art. 

Each of the three study contractors concluded that an effective AWACS could be built 

and delivered in the early 1970's. 

studies, DDR&E directed the Air Force to proceed with the development of a prototype system (two aircraft for flight test) in a timely and orderly manner. 

In December of last year three separate configuration studies were 

Also in December, and as a result of these 

The Air Force has responded during the past year by organizing a system program 

office to manage the development, planning a sound development program and engaging a number of contractors to carry out the first phase of the program. This 

first phase, called concept formulation, will be completed by May of next year and 

will ensure, through studies and preliminary de signs, that we continue development 

of a system that can be built and can do the job that we want it ta do. 

70 
The study contracts let this year fall into three general groupings. 

four radar contractors making preliminary design studies of radars that will have the 

ability to detect and track aircraft against a background of ground returns. Second, 

two contractor teams are examining the command, control and communications 

problems entailed in providing communications, data processing and displays. Significantly, these studies are defining what must be done to make AWACS compatible 

with the other services and our allies. 

reviewing the above mentioned studies and other factors which affect the proposed 

aircraft. The result of the system studies will be a cost-effectiveness trade-off 

analysis which will be used to validate the concept formulation and to support the 

contract definition phase. 

First, there are 

Finally, two aircraft system contractors are 

COOPERATION WITH OTHER GOVERNMENT AGENCIES 

Coordination and cooperation with other governmental activitie 8, particularly NASA, 

continues at a high level. 

levels of the respective agencies, scheduled meetings of formal coordinating panels 

and boards, and direct support o NASA. 

These include very frequent informal discussions at all 

Aeronautic s -Astronautic s Coordinatinv Board 

The Board held five meetings during CY 1966. 

reusable launch vehicle studie 8, coordination of planning of new facilities, examination of advanced large liquid fuel engine, and use of navigation satellites. 

Examples of its activities are: 

Manned Space Flight Policy Committee 

DOD and NASA, by agreement of January 1966, established a "Manned Space Flight 

Policy Committee" as a means of expediting coordination at a policy level the manned 

space flight programs of the two agencies. Three meetings of the Committee were 

held during 1966. 

DOD Participation in the GEMINI Program 

This program, consisting of fifteen separate experiments, has been directed towards 

enhancing the DOD manned space flight experience level by conducting and evaluating 

techniques and equipment on the NASA GEMINI missions. 

During 1966, eleven DOD experiments were flown on four GEMINI missions. 

early termination of the GEMINI 8 mission and Extra Vehicular Activity (EVA) 

curtailment due to some astronaut and operational difficulties on GEMINI missions 9, 

10 and 11 precluded totally successful completion of all DOD experiments. However, 

rescheduling some of the early experiments that were not conducted to later missions 

permitted a substantial accomplishment of experiment objectives. 

The 

With the successful completion of the D- 15 Night Image Intensification Experiment on 

GEMINI XI, the Navy concluded its series of experiments in the GEMINI program. 

The Navy's experiments included D-15, D- 14 UHF/VHF Polarization Measurement 

and D- 15 Astronaut Visibility; all experiments were successfully accomplished. 

71 
DOD Support of NASA 

There are over 400 separately identifiable activities of DOD support of NASA, representing in magnitude a total value of effort over $500 million per year. Among 

the major items of support are the operation of the ranges for manned and unmanned 

spacecraft launches and host base support by the Air Force, major construction by 

the Army and operation of the recovery fleet by the Navy. 

many other activities of lesser magnitude. 

In addition, there are 

Selected examples are cited below: 

Army 

Conetruction Support. The Corps of Engineers supported NASA by providing real 

e state acquisition services, and de sign and construction of facilities at various 

locations, including the John F. Kennedy Space Center, Mississippi Test Facility, 

the Manned Spacecraft Center and the Electronics Research Center. 

of this support exceeded $80 million. 

The magnitude 

Lunar Activities. 

techniques and lunar control networks. 

using various source data, including RANGER, SURVEYOR and LUNAR ORBITER 

photographs. 

The Army Map Service assisted NASA by developing lunar mapping 

Maps are being produced at several scales 

The Corps of Engineers and the Army Materiel Command made a study of the feasibility of modifying an Army vehicle for use in exploration missions on the surface of 

the moon. The Army Materiel Command is conducting mobility tests on two versions 

of prototype lunar vehicles, designated as Mobility Test Articles. 

Engineers is assisting NASA in evaluating engineering models of lunar drills. 

The Corps of 

Supporting Technolou. 

field commands, carried out a variety of research and development projects for 

NASA. These included: (1) Development of freeze-dried foods for space use and 

de sign of clothing for extended space missions -- Natick Laboratories; (2) Inve stigation of spacecraft contamination and sterilization -- Fort Dietrick; (3) R&D of 

post-operational destruction system for NERVA engine -- Picatinny Arsenal; 

(4) 

development of fluid logic techniques -- Harry Diamond Laboratories. 

The Army Materiel Command, through its laboratories and 

Development of safety and ignition device for spacecraft apogee motor and 

Navy 

GEMINI. 

involved in each operation. 

of 1000 hours. 

Operation of the recovery fleet for GEMINI flights. About 14 ships are 

In addition to the ships, the Navy flew aircraft in excess 

Medical Projects . with GEMINI V and VII flights and similar test program is planned for APOLLO 

AS-204 and AS-205. 

Tests of vestibular function have been conducted in conjunction 

Construction Projects. 

facilities de sign and construction together with inspection and contract administration. 

Work performed for NASA under this category covers 

Types of facilities that have been constructed run from fabrication of facilities for 

space vehicles, and space tracking and data acquisition facilities to foundations for 

antenna structures and associated site and utility work. 

72 
Air Force 

Range Support. 

and unmanned programs. 

support, and range ship support. 

The National Range Division provides support o NASA for manned 

This support included range support services, base 

Launch Vehicles. 

average of approximately: (1) one booster delivery per month to the combined NASA 

The Medium Launch Vehicles Program Office has provided an 

AGENA and NASA DELTA programs over the past four years; and has provided 

launch services management of between two and three boosters per year for NASA 

AGENA. 

The GEMINI Target Vehicle Program Office acts as the NASA contractor for six 

AGENA Target Vehicles used in the GEMINI rendezvous and docking experiments. 

This includes procurement of the basic AGENA D vehicle; development, test and 

procurement of the program peculiar equipment necessary to convert the AGENA D 

to a GEMINI Target Vehicle; development and procurement of Aerospace Ground 

Equipment; procurement of the ATLAS (SLV-3) boosters; and launch of both vehicles. 

The SLV-3 Directorate is responsible for the management of the SLV-3 vehicle 

program. This responsibility includes technical direction, configuration magement, 

procurement and production of SLV-3 vehicles and supporting Aerospace ground 

equipment. For example, LUNAR ORBITER, from its inception as a requirement 

to its recent launch required 24 months of management, 6 months contractual leadtime and 18 months production time, during which close surveillance was required 

to insure its successful launch. 

APOLLO Services Provided for Manned SDacecraft Center 

a. 

b. 

C. 

d. 

e. 

LEM Ascent Engine Environmental Development. Thirty-eight firings 

were made in the period 14 January - 10 February 1966 to evaluate 

the effects of altitude and thermal environment on engine performance 

and structure and to investigate altitude start transients. 

LEM Descent Engine Environmental Test. 

duration mission duty cycle tests at simulated altitude of about 350,000 

feet. 

Objective was to conduct long 

Service Module Propulsion Test. 

the operating characteristics of the engine and determine whether it meets 

performance specifications in a simulated space environment. 

A continuing test program to establish 

Command Module. Von Karman Gas Dynamics Facility. Testing on 

models of the Command Module was accomplished to investigate flow interference problems encountered in previous tests. 

Miscellaneous. 

Flight Center at Von Karman Gas Dynamics Facility Impact Ranges. 

is a continuing test program to determine effects of hypervelocity projectile 

impacts into lined and unlined pressure vessels containing air or oxygen 

at various pressures. 

Meteoroid impact test conducted by the Marshall Space 

This 

73 
Aerospace Rescue and Recovery prepositioned operating and support personnel to world-wide locations to support GEMINI 8 through 12 to recover 

astronauts and spacecraft and to recover the APOLLO SATURN 201 unmanned suborbital spacecraft near Ascension Island. 

T-2 testing which evaluated the SURVEYOR lunar soft-landing vehicle was accomplished. This testing required over three years to complete. 

74 
ATOMIC ENERGY COMMISSION 

INTRODUCTION 

In the Atomic Energy Commission's space nuclear 

CHAPTER 

V 

power program, 1966 was the 

year in which the joint NASA/AEC nuclear-rocket program progressed from a 

graphite reactor engine system technology program into a combined technology and 

engine system development program, and the space electric power program moved 

from the developmental to the applications stage. 

experimental data was accumulated on the high -performance capabilities of nuclear - 

rocket systems. Nuclear-rocket reactors were started, stopped, and restarted 

without difficulty and operated over a wide range of conditions. 

nuclear -rocket engine was successfully tested in a "breadboard" configuration 

(flight-type components in a nonflight arrangement). Work also proceeded on the 

next phase of the engine system technology program -- to build and test ground 

experimental rocket engines which are more closely configured to a flight engine 

than the "breadboard" engine tested early this year. 

During the year, additional 

The nation's first 

The development of nuclear energy systems to provide the source of electrical 

energy in long-life space applications also progressed during 1966. A reactorpowered electric generating system completed one full year of continuous operation 

on the ground in a vacuum tank, and a growing list of requirements has developed 

for radioisotope electric generating systems. 

NUCLEAR ROCKET PROPULSION 

In the program to develop nuclear rocket propulsion systems, an altitude specific 

impulse of more than 7~50 seconds was experimentally demonstrated (assuming a 

nozzle area ratio of 40 to 1) for approximately 30 minutes at design power (1,100 

megawatts) in each of two reactors. 

run them back to full power, and throttle them at full specific impulse was demonstrated. 

850-900 seconds were potentially attainable. 

that extended operating duration was also attainable. 

nuclear rockets will permit large gains in payload for the variety of space missions 

now being considered. 

In addition, the ability to restart these systems, 

Laboratory experiments further indicated higher specific impulses of 

Laboratory experiments also indicated 

The work done indicates that 

NERVA Reactors and Engine Systems 

Significant advancements were made during 1966 in the development of the NERVA 

(Nuclear Engine for Rocket Vehicle Application) graphite engine reactor system 

capable of operating at full power of 1 , 100 thermal megawatts for approximately 

60 minutes. 

nuclear -rocket engine, a "breadboard" engine called NRX/EST (NERVA Reactor 

Experimental Engine System Test), and in tests of the NRX-A5 reactor. 

These advancements were demonstrated in tests of the nation's first 

75 
The NRX/EST consisted of a flight-type reactor (the NRX-A4) mounted on a test car in 

anupside-down firing position and connected for the first time to an engine turbopump 

located on the test car, the turbine of which was driven by hot hydrogen bled from the 

reactor exhaust through a port in the nozzle wall (a hot-bleed port). The main differences between this system and that of an actual flight engine system were that the 

pump was not in its flight engine location (it was located on the test car), the engine 

fired upward rather than downward, and the exhaust gases discharged into the atmosphere rather than into an altitude simulation (vacuum) duct. The engine operating 

information obtained from tests of such a system, however, was indicative of and 

applicable to the design of a flight engine. 

of testing over a period of seven weeks and accumulated a total of 110 minutes of 

power operation, including about 29 minutes at full power. 

as yet incomplete, but it has been established that the hot-bleed nuclear-rocket 

engine system is stable over a wide range of operating conditions, and is capable of 

withstanding multiple starts, stops, and restarts, and of being controlled by several 

means. 

the test program, and it was replaced early in the test series with an improved model 

which functioned well for the remainder of the test program. 

The NRX/EST was subjected to five days 

Analyses of test data are 

Only one of the engine components, a valve actuator, caused difficulty in 

On June 8, the NRX-A5 reactor was successfully test operated at full power for 15.5 

minutes. On June 23 the same reactor was restarted without difficulty and run for 

an additional 14.5 minutes to gain a further understanding of its operation and life. 

In addition to the NRX/EST and NRX-A5 tests, work also continued throughout the 

year on developing those components and facilities required to assemble and test 

ground-based experimental engines (XE's) -- the next phase of the engine system 

technology program. 

first systems to be tested in a down-firing position, at conditions partially simulating operation in space. The first XE is scheduled to begin power testing in 1967 

to provide further data on engine startup, system interactions, and various control 

modes. 

of the complex engine-test facility system. 

The XE's will resemble actual flight engines and will be the 

This test program will also provide important needed data on the operation 

PHOEBUS Reactors 

The principal activity during 1966 in the PHOEBUS reactor program -- the designation given to the program to advance the KIWI/NERVA graphite reactor technology 

toward higher power and temperatures -- was the preparation for and conduct of the 

PHOEBUS-1B power reactor test program. The PHOEBUS-1 reactors are the same 

size as the KIWI/NERVA reactors and incorporate a variety of experiments to 

explore some of the operating characteristics and design features planned for the 

larger -diameter, higher -powered (5,000 thermal megawatts) PHOEBUS-2. 

The development and fabrication of improved fuel elements, high-temperature 

materials, large hardware, and complex facilities which will allow testing of the 

PHOEBUS-2 reactor also continued throughout 1966. 

The nuclear -rocket propulsion program has, to date, proven the feasibility of nuclear 

rockets and their high-performance capabilities. In addition, the program is well on 

the way toward establishing the technology base on which it will be possible to design 

and develop the specific flight hardware required for future missions. 

76 
SPACE ELECTRIC POWER 

Space Radioisotope Power Systems 

To supplement present technical management of the rapidly expanding space radioisotope power systems programs, the AEC in February 1966 selected its Sandia 

Laboratory and Albuquerque Operations Office, Albuquerque, N. Mex. , to support 

the Space Nuclear Systems Division in the conduct of these programs. 

The first fueling of a SNAP-11 thermoelectric generator with curium-242 was accomplished in July 1966 at the Oak Ridge National Laboratory in Tennessee. 

1966, this fueled unit successfully completed a 90-day test under simulated lunar 

conditions. 

Manned Spacecraft Center, Houston, Tex. and the Jet Propulsion Laboratory, 

Pasadena, Calif. late in the year. Testing of these generators will complete the 

planned SNAP- 11 work. 

In October 

Electrically-heated SNAP-1 1 generators were delivered to NASA's 

Two prototype SNAP-19 generators, designed to provide approximately 50 watts of 

electrical power to the experiments on board the NIMBUS-B weather satellite while 

200 watts electrical will be provided by the satellite's large solar cell paddles, were 

thermally tested on board a NIMBUS-B mockup in June 1966. An electrically heated 

system was delivered to NASA's spacecraft integration contractor in July 1966 for 

electrical compatibility testing with the spacecraft. Late in 1966 two prototype 

radioisotope-fueled generators were tested to flight system qualification levels. 

The final design was completed, and hardware procurement and manufacturing 

initiated, for the 50 watt electrical SNAP-27 radioisotope thermoelectric generator. 

This plutonium-fueled generator, which is to be placed on the moon by an astronaut 

during an early APOLLO mission, will provide power for up to one year for experimental packages left there by the astronauts. 

system -- including the generator, fuel capsule, and lunar excursion module shipping 

cask -- were delivered to NASA in January 1966 for system compatibility studies. 

The fir st electrically-heated engineering generators were placed on test in October 

1966. 

mockups, and in December 1966 a prototype electrically-heated system was delivered 

to NASA's Manned Spacecraft Center for system compatibility testing with the APOLLC 

Lunar Surface Experiments Packages hardware. 

Models of the complete SNAP-27 

In November 1966, delivery was made of the thermal test generator system 

The detailed design and subcomponents development phase of the SNAP-29 program 

was initiated in 1966. SNAP-29 is to be designed for fueling with polonium-210 and 

is to provide nominal power of 500 watts electrical for 150 days with a total system 

weight of about 500 pounds suitable for both manned and unmanned space applications. 

Parallel six-month studies were also initiated in 1966 by three industrial contractors 

to determine the feasibility of designing radioisotope thermoelectric generators - - 

fueled with either plutonium-238 or, possibly, strontium-90 - - which would be 

capable of controlled re-entry into the earth's atmosphere from orbit in an intact 

condition. These studies will be used as the basis for possible follow-on work should 

the Department of Defense or NASA require long-lived radioisotope -powered generators for satellite operation in the few hundred watt power range. 

77 
Space Reactor Power Systems 

SNAP-1OA Ground Tests. A SNAP-1OA flight-type system -- identical to the 500- 

watt SNAP-1OA system which operated successfully in space for 43 days in 1965 

before a faulty command within the spacecraft shut it down -- completed a recordmaking 10,000 hours (about 417 days) of continuous operation on the ground in a 

vacuum tank, simulating the space environment, and was then shut down. The unit 

has been disassembled and is now being examined to determine its status after 

operation. 

SNAP-8. Funds to continue the development of the SNAP-8 reactor power conversion 

system (PCS) were re-instated, and the PCS has been assembled and is undergoing 

extended testing at NASA. The experimental version of the SNAP-8 reactor -- designated the SNAP-8 Experimental Reactor -- which was ground-tested for a total of 

8,300 hours at thermal powers of 400 to 600 kilowatts before being shut down, was 

disassembled and found to have cladding cracks in most of the fuel elements. This 

problem, which is attributed to the combined effect of fuel swelling and fuel-clad 

embrittlement, is being evaluated and will be corrected before the fuel elements for 

the next reactor in the SNAP-8 series -- the SNAP-8 Developmental Reactor -- are 

fabric ate d . 

SPACE-DIRE CTED ADVANCED TECHNOLOGY DEVELOPMENT 

Advanced Space Reactor Concepts 

In order to meet future space power needs for very long-lived systems having electrical outputs in the hundreds and thousands of kilowatts, the AEC continues to 

support three basic advanced reactor concepts: (a) the liquid metal-cooled reactor, 

(b) the in-core thermionic reactor, and (c) the high-temperature advanced gas-cooled 

reactor. Further work on a fourth concept, the Medium Power Reactor Experiment 

(MPRE), was eliminated in 1966. 

Major attention during the year on the liquid metal-cooled reactor concept was given 

to defining the reactor requirements, and by the end of the year the experimental 

portion of this program was evolving from exploratory materials research into a 

technology effort supporting the reference reactor designs. 

Activities conducted on the thermionic reactor concept during 1966 consisted primar - 

ily of the in-pile (in-reactor) testing of fueled thermionic diodes to determine their 

capability of operating at temperatures above 3, OOO°F. In view of the encouraging 

results obtained from these in-pile tests, the scope of the thermionic effort is being 

broadened to investigate overall reactor problems such as stability, control, and 

reliability . 

Emphasis in 1966 in the development of high-temperature gas -cooled reactor technology was placed on dynamically testing full-size fuel elements at temperatures up 

to 3, OOO°F, in-pile fuel testing, and on refining the reactor design. 

reassessment of space program priorities, the development program is being reoriented from one which would involve the testing of a reactor core to one which will be 

limited for the time being to the development of fuel element technology. 

Because of 

78 
Further work on the boiling potassium reactor (the MPRE) was eliminated during 

1966 in order that effort and resources might be concentrated on the other three 

advanced reactor concepts. 

Space Power Conversion Technology 

To supplement prototype radioisotopic generator developments and studies, the AEC 

is supporting several industrial contractor organizations that are conducting programs 

to provide higher temperature, more efficient and/or lighter weight thermoelectric 

systems, and to demonstrate the capabilities of radioisotope -fueled thermionic power 

systems, to meet long-term requirements for future space applications. 

programs are the Compact Thermoelectric Module Development program which looks 

toward the development of a compact space thermoelectric power converter of modular form which would use either radioisotopes or reactors as the heat source to 

produce one to 20 electrical kilowatts; the ISOTEC program which employs thermal 

radiation coupling between an isotope heat source and its surrounding flat-plate 

thermoelectric panels; and the Direct Radiating Thermoelectric program which has 

the purpose of upgrading the thermoelectric technology used in SNAP-1OA SO that 

higher efficiencies can be achieved with the SNAP-8 space reactor or with radioisotopes. Each of these programs progressed during 1966 through tests of thermoelectric elements in their operating environment. In addition, the design phase of a 

100 watt thermionic module for use with radioisotope heat sources was initiated in 

1966. 

Among these 

SPACE NUCLEAR SAFETY ACTIVITIES 

On January 11, 1966 a modified SNAP-1OA type reactor was deliberately destroyed 

in order to improve the predictive capability to determine the consequences that would 

follow an accidental excursion of a SNAP reactor system. 

Additionally, safety studies were conducted on radioisotope fuel capsule impact and 

burial phenomena, system responses to propellant fires and explosions, re-entry 

phenomena, atmospheric dispersion of particles, and terrestrial contamination 

problems associated with radioisotope fuels. 

SATELLITE-BASED DETECTION OF NUCLEAR EXPLOSIVES IN SPACE 

The six AEC-instrumented VELA nuclear test detection satellites developed for the 

Department of Defense continued to perform their test ban monitoring functions in 

1966. 

solar wind and its interaction with the earth's magnetosphere, including the earth's 

magnetospheric tail which is dragged out to distances of many earth radii on the dark 

side of the earth by the action of the solar wind. 

orbit two at a time using ATLAS-AGENA booster systems, with the launches taking 

place in October 1963, July 1964, and July 1965. 

on a near circular orbit with coverage radius of about 60,000 nautical miles. 

In addition, they relayed back to earth much new scientific information on the 

The six satellites were placed in 

They are in widely space positions 

A fourth launch of two VELAs is planned for early 1967 and two more satellites are 

scheduled for a 1968 launch. 

system, and will place in orbit a new generation of twin spacecraft with increased 

nuclear test detection capabilities. 

oriented at all times, and will include new instrumentation for observing the optical 

The future launches will use a TITAN III-C booster 

The new satellites will have one axis earth 

79 
and electromagnetic radiations from nuclear weapons tested in the atmosphere, in 

addition to improved versions of neutron, gamma-ray and X-ray detection systems 

for space surveillance. 

80 
DEPARTMENT OF STATE 

INT RODU CTION 

The President's decision to seek increased cooperation with other technically 

advanced nations in advanced space exploration projects was greeted in Europe 

with great interest. 

governments on the President's offer of cooperation. 

ment of State team visited the major European capitals and space science centers to 

discuss the offer in detail. 

for additional discussions. 

exploration has stimulated interest in bilateral and multilateral cooperative projects 

and in the role of space programs in solving the problems of the technological gap. 

United States embassies in Europe carefully briefed their host 

In February a NASA/DepartSenior officials also made a visit to Europe in September 

This initiative toward increased cooperation in space 

A review of policy on the export of space technology has enabled the Department to 

inform European governments of U. S. willingness to increase its assistance to 

multinational development of a space launch capability. 

The United Nations took several important decisions relating to outer space. 

most significant was the agreement reached on the "Treaty on Principles Governing 

the Activities of States in the Exploration and Use of Outer Space, including the 

Moon and Other Celestial Bodies. I' 

important arms control development since the limited test ban treaty of 1963. I' The 

treaty forbids the placing of weapons of mass destruction in outer space or on 

celestial bodies, restricts military activities on celestial bodies, bars claims of 

sovereignty and national appropriation, and contributes in a number of other ways 

to the establishment of a legal regime in outer space. 

The 

The President has called this treaty "the most 

The General Assembly also approved recommendations of the Outer Space Committee for a United Nations conference on outer space to be held in Vienna in 

September 1967. 

of space programs, with special reference to the needs of developing countries, and 

opportunities available for international cooperation in space programs. The U. N. 

Assembly also endorsed recommendations resulting from the work of the Scientific 

and Technical Subcommittee including one to establish a working group to consider 

the development of an international navigation-services satellite system. 

The conference will focus on two basic subjects: practical benefits 

The Department was pleased to forward through its science attaches and scientific 

affairs officers at missions overseas SURVEYOR I and LUNAR ORBITER I photographs for appraisal by foreign scientists. Our ambassadors were also provided 

with selected copies for presentation purposes. 

The Department stimulated interest of foreign governments in the Automatic Picture 

Transmission (APT) system for receiving cloud-cover photographs from U. s. 

81 
weather satellites by having U. S. missions present information on the benefits and 

low cost of the system. 

encouraging. 

purchase commercial equipment by the ingenuity shown in building APT receiving 

sets from locally available materials. 

The appreciation shown for the APT system has been 

A number of countries have made up for their lack of funds to 

The Department has continued to support the national space program by negotiating 

station agreements, assisting in contingency arrangements for astronaut recovery, 

and obtaining foreign cooperation and support for various aspects of the program. 

It has also taken an active part in encouraging broad participation in the development of a commercial global satellite communications system. 

ACTIVITIES WITHIN THE UNITED NATIONS 

A Working Group of the Committee on the Peaceful Uses of Outer Space met in 

New York January 18-25, and again September 6-9, to consider a proposal for a 

United Nations conference on Outer Space. It recommended a conference focused 

on two basic subjects: 

to the needs of developing countries, and opportunities available for international 

cooperation in space programs. A detailed agenda covering all aspects of these 

subjects was developed. 

which will not be empowered to make recommendations or decisions, be held in 

Vienna in September 1967. 

practical benefits of space programs, with special reference 

The Working Group also recommended that the conference, 

The Scientific and Technical Subcommittee of the Outer Space Committee met 

April 18-27 at the European U. N. Headquarters in Geneva. 

agreed on a number of recommendations, of which the most significant were: 

The Subcommittee 

a. five guidelines for evaluating requests for international support of 

training programs in the specialized field of space science. 

b. a Space-Committee Working Group to consider the need, feasibility, and 

implementation of a navigation-services satellite system. 

c. means to improve the usefulness and distribution of U. N. publications 

in the field of outer space. 

The Space Committee's Legal Subcommittee met twice in 1966 -- July 12-August 4 

and September 12-16 -- and its members conducted nearly continuous informal 

negotiations. On December 8, they announced agreement on a "Treaty on Principles 

Governing the Activities of States in the Exploration and Use of Outer Space, including the Moon and Other Celestial Bodies. 'I Work had begun shortly after May 7, 

when the President suggested a number of elements for such a treaty and asked the 

U.S. Ambassador to the United Nations to seek early discussions in the United 

Nations. 

The Treaty forbids the placing of weapons of mass destruction in outer space or on 

celestial bodies - - thus incorporating the "no-bombs -in-orbit" U. N. resolution of 

1963 -- and placed restrictions on military activities on the moon and other 

celestial bodies. 

is guaranteed. The Treaty also contains a number of principles designed to 

To allow verification, open access to all areas on celestial bodies 

82 
establish a legal regime in outer space. 

following: 

Among the most important are the 

a. 

, b. 

C. 

d. 

e. 

f. 

g. 

freedom of exploration and use of outer space and celestial bodies for 

all States on a basis of equality. 

activities in outer space and on celestial bodies are subject to international law, including the United Nations Charter. 

claims of sovereignty and national appropriation are barred. 

an unconditional obligation exists to help and to return astronauts promptly 

and safely if they land elsewhere than planned, and to exchange information 

relating to astronaut safety. 

activities in outer space and other celestial bodies are to be reported to 

the Secretary-General of the United Nations to the greatest extent feasible 

and practicable. 

provision is made for the avoidance of harmful contamination and for 

international consultation in connection with potentially harmful space 

experiments. 

a launching state shall be internationally liable for damages caused by its 

space vehicles. 

The Outer Space Committee endorsed the recommendations of the Scientific and 

Technical Subcommittee with little debate and noted the partial report of the Legal 

Subcommittee. The U. S. Ambassador to the United Nations drew attention to the 

broad opportunities for international cooperation available in our national space 

program. 

On December 19, the U. N. General Assembly adopted by acclamation a resolution 

endorsing the draft treaty and asking the Outer Space Committee to begin study of 

related legal topics. 

endorsed the recommendations of the Scientific and Technical Subcommittee; the 

other approved the holding of the U. N. space conference in 1967. 

Space Committee's major lines of action in 1966 thus culminated in General Assembly endorsement and approval. 

The Assembly also adopted two other resolutions: one 

All three of the 

TRACKlNG NETWORKS 

NASA Facilities 

Government-to-Government agreements by exchange of notes are in existence with 

the following countries covering the foreign portion of NASA's global tracking network: Australia, Canada, Chile, Ecuador, Malagasy Republic, Mexico, Nigeria, 

Peru, South Africa, Spain, and the United Kingdom. These facilities consist of 

stations supporting the manned space flight program, a tracking and telemetry 

network for scientific satellites, and deep-space antennae at four locations around 

the world. 

facilities which are also used by NASA. 

These are in addition to the U.S. Air Force's Eastern Test Range 

83 
During the past year the United States, through its embassies abroad, negotiated 

extensions and modifications of its agreements with Spain and the United Kingdom 

in preparation both for Project APOLLO and for new or expanding scientific satellite programs. After a NASA review of its tracking requirements determined that 

the facilities in Nigeria would no longer be required, negotiations were begun to 

close the station in Kano. 

Cooperation with ESRO 

Negotiations were completed with the European Space Research Organization (ESRO) 

November 28, on the agreement providing for establishment and operation of an 

ESRO satellite telemetry and command station near Fairbanks, Alaska. 

which forms part of a network which ESRO is building to support its scientific 

satellites, will be the first foreign space-tracking station on U. S. soil. The station 

will be manned primarily by U.S. contractor personnel but will also have a complement of ESRO technical personnel. The station whould be in operation by the end of 

I966 and be available for the launchings of two ESRO satellites which are scheduled 

for 1967 under the terms of a cooperative agreement between ESRO and NASA. 

The station, 

CONTINGENCY RECOVERY OF ASTRONAUTS 

The Department of State and its overseas posts maintained a state of alert throughout each of the manned GEMINI flights. A GEMINI Task Force was briefed and 

prepared to support DOD and NASA in case of an emergency recovery requiring 

such support. 

principal purpose of the Task Force is to enable the Department, on a moment's 

notice in event of a premature landing or other emergency, to call upon the appropri 

Similar arrangements will be made for APOLLO flights. The 

ate posts abroad to arrange through the respective host governments for such 

assistance as is indicated by the nature of the emergency. 

is to assist in the maintenance of clear communications channels between the spacecraft and ground stations by alerting posts whenever interference on GEMINI or 

APOLLO frequencies is reported in any part of the world. When necessary, posts 

can be instructed to request through their host governments the silencing of potentially harmful interference. 

ference harmful to a GEMINI mission, thanks to excellent cooperation of governments in all areas of the world. 

Another important task 

To date there has been no instance of radio interSimilarly, each principal Foreign Service post between 32 degrees north and 32 

degrees south latitudes has an officer whose duty it is to keep abreast of space 

flight planning for every manned mission as it evolves. 

Prior to each manned spaceflight mission the Department through embassies 

abroad facilitates the positioning of Air Force SAR (Search and Rescue) Units at 

strategic locations around the globe. 

clearances are obtained in advance from countries through which SAR Units might 

have to fly in event of emergency. 

To the maximum extent possible overflight 

ASTRONAUT TRAVEL ABROAD 

Now that the U.S. has passed through the early, critical stages of its manned space 

flight program, the President has decided to make use of our astronauts from time 

to time to carry abroad the message of the peaceful character of the U. S. space 

84 
program. 

Africa in 1965 was repeated in 1966 in visits to the Far East and Latin America. 

The success of the astronaut visits to France and the Near East and 

WEST GERMAN CHANCELLOR VISITS CAPE KENNEDY 

On September 22, the Chancellor of the Federal Republic of Germany visited Cape 

Kennedy as a guest of the President and toured NASA facilities there. 

which the President made to the group gathered in the Vehicle Assembly Building 

to greet the Chancellor included a statement of U. S. willingness to join with the 

countries of Europe in space efforts of mutual benefit. 

of launch vehicles and other types of assistance, as appropriate. 

The remarks 

The offer included provision 

ASSISTANCE TO ELDO 

In the interest of encouraging multilateral cooperation in the .building of launch 

vehicles for non-military space purposes, as opposed to national programs which 

might be militarily oriented, the U. S. reviewed its policy on the export of booster 

technology. 

of the European Launcher Development Organization (ELDO) by offering technical 

advice and assistance in the proposed reconfiguration of the ELDO-A launch vehicle 

and long-range assistance in development of follow-up ELDO projects using highenergy, cryogenic upper stages. In addition, the U. s. offered to supplement 

ELDO-A launch services by sale of certain U. S. launch vehicles or launch services 

for scientific or applications satellite projects. In addition to promoting expanded 

cooperation without enhancing foreign ballistic missile capability this initiative to 

ELDO provides another approach toward reducing the technological gap. 

A decision was reached to encourage the continued existence and work 

COOPERATION WITH DEPARTMENT OF DEFENSE 

The Department of State continued to work closely with the Department of Defense 

during 1966 on international aspects of the Initial Defense Communications Satellite 

Program (IDCSP) and the Manned Orbiting Laboratory (MOL) Project. 

COMMUNI CAT IONS VIA SAT E LLIT E 

The International Telecommunications Satellite Consortium (INTELSAT) continued 

development of a commercial global communications system. 

(EARLY BIRD) continued to operate successfully with 79 of its voice channels 

leased on a full-time basis. The launch of the first of the second-generation 

INTELSAT -11 satellites took place on October 23, 1966. The vehicle failed to 

achieve synchronous orbit on its planned position over the Pacific. 

tion of the cause of the failure, caused a delay in the succeeding INTELSAT-I1 

launches. 

and one over the Pacific in 1967. 

satellites which are designed to provide approximately 1200 voice circuits over a 

five year operating life. 

INTELSAT -I 

The investigaOne INTELSAT-I1 satellite is planned to be positioned over the Atlantic 

Construction was authorized for six INTELSAT-I11 

Six countries joined INTELSAT in 1966 bringing the total membership to 54. 

Department of State and the Communications Satellite Corporation maintained a 

vigorous program of encouraging other countries to join the consortium. All 

member countries have signed the Supplementary Agreement on Arbitration to the 

Special Agreement on Technical and Financial Arrangements thus placing the 

The 

85 
Agreement in force. 

As a contribution to the International Telecommunication Union (ITU) technical 

assistance program the U. S. sponsored a Seminar on Communication Satellite 

Earth Station Technology held in Washington in May. 

international organizations were represented at the Seminar, which was designed 

to acquaint officials of interested countries with the fundamentals, current developments, and technical details of communication satellite earth stations. Edited 

copies of pertinent technical materials presented at the Seminar have been distributed to participating countries and to the ITU. 

Forty-five countries and six 

The U.S. actively participated in meetings of the technical organs of the ITU, the 

International Radio Consultative Committee (CCIR) and the International Telegraph 

and Telephone Consultative Committee (CCITT) and contributed to their growing 

interest in space activities. 

awareness of the technical problems in utilizing a radio spectrum shared by space 

and terrestrial radio services. 

Both of these organizations have shown an increased 

The Second Session of the Extraordinary Administrative Radio Conference for the 

Aeronautical Mobile Service adopted a resolution proposed by the United States 

which asked member countries to consider space radio communication techniques 

as a means of filling the communication needs on the major world air routes. 

At a meeting of the Communications /Operations Division of the International Civil 

Aviation Organization (ICAO) the U. S. proposed ICAO endorsement of a plan to 

test a VHF aeronautical voice communications satellite system in the North Atlantic. 

This proposal was supported by other members of the Organization. 

86 
NATIONAL SCIENCE FOUNDATION CHAPTER 

VI1 

INTRODUCTION 

This year as in the past, the contributions made by the National Science Foundation 

to the Nation's space effort consisted for the most part of support given to basic 

research projects at colleges, universities, national programs, and national research centers throughout the country. 

scientific balloon capabilities are also provided by NSF for scientific research that 

is related to outer space. 

Facilities such as radio telescopes and 

National Radio Astronomy Observatory (West Virginia; Virginia) 

During the past year major computer facilities and staff headquarters have been established in Charlottesville, Va., to serve the National Radio Astronomy Observatory at Green Bank, W. Va. The 140-foot precision radio telescope was in very 

active use during the entire year. Areas of research pursued included measurements of the OH spectrum lines in various regions, lunar occultations of extragalactic sources, and hydrogen line observations. The instrument was heavily 

scheduled by both visitors and members of the staff. 

Modifications and improvements in the 300-foot radio telescope have been carried 

out during this year and it is now a better and more rigid structure. 

ferometer using the two 85-foot telescopes has operated very successfully and has 

also been heavily scheduled. 

The interInstrumentation has been under construction for implementing an extremely widebase line interferometey using the 140-foot antenna at Green Bank and the 1000-foot 

reflector at Arecibo in Puerto Rico. 

operate at millimeter wavelengths has been completed and installed at its site at the 

Kitt Peak National Observatory in Arizona. 

The 36-foot radio telescope designed to 

The Kitt Peak National Observatorv (Arizona) 

A second 36-incb reflecting telescope was put into service late in the year. 

cations to the first 36-inch during the summer included a new mirror and tube with 

provision for a wider angle of view and rapid exchange of the secondary mirrors. 

These two "workhouse telescopes'' will come closer to fulfilling the demand by U. S. 

astronomers for observing time at the National Observatory. A wide variety of research programs ranged from visual measurement of double stars and photoelectric 

photometry of stars to spectra of various types of stars, nebulae, galaxies, and of 

quasi-stellar objects (using image tubes). 

ModifiNew auxiliary equipment on the great McMath solar telescope permits recording the 

magnetic field of the sun in great detail. Many spectographic researches were 

87 
carried out during the year. 

Ce r ro Tololo Inter -Arne rican Ob se rvatorv (Chile) 

A second 16-inch reflecting telescope was put in operation and both instruments used 

by U. S. and South American astronomers in several photometric research programs 

by staff and visitors. 

University of Michigan has added a third telescope expected to come into operation at 

the same time as the 36-inch and 60-inch reflectors shortly after the year ends. 

large field of view of the Schmidt telescope complements the other instruments and 

they present a powerful battery for exploration of the lesser known southern skies 

from this superb astronomical site. 

The loan of a 24-inch aperture Schmidt telescope by the 

The 

The E. 0. Hulburt Center for Space Research at the Naval Research Laboratory 

(Washington, D. C. ) 

The NSF continued the support of several university staff members, who proposed 

astronomical research programs using rockets and satellites, to work with the fine 

staff and facilities of the Center. 

National Center for Atmospheric Research (Colorado) 

The research programs of the National Center for Atmospheric Research are 

centered in the High Altitude Observatory and the Laboratory of Atmospheric 

Sciences. The High Altitude Observatory program is concerned with the sun, 

solar atmosphere, and the region between the sun and the earth. 

Accomplishments during FY 1966 include: 

a. 

b. 

C. 

the 

analysis of the combined results of three sets of solar measurements 

made by: 

May 30, 1965; (2) the HA0 balloon-borne Coronascope I1 on flights 

made June 3 and July 1, 1965; and (3) the HA0 K-coronameter in daily 

observations in Hawaii. This analysis has enabled HA0 to define the 

shape of a coronal streamer from the sun and to determine the velocity 

and distribution of electrons in the streamer. Thus, it isnow possible 

to determine the distance from the sun to which the solar magnetic field 

governs streamer shape and the point at which the electrons break free 

of the sun's magnetic field. 

(1) a NASA aircraft over the Pacific during the eclipse of 

a survey of the magnetic fields in 50 solar prominences, using the new 

magnetograph at Climax, Colo. As a result, the range of fields that can 

occur in prominences has been determined, as well as the manner in 

which the geometry of the field relates to the geometry of the prominence. 

detailed analysis of the earth's magnetic field variations which showed 

that ionospheric currents change in phase with the solar cycle. 

the currents were larger than could be accounted for solely on the basis 

of increased solar activity as reflected in increased conductivity of the 

ionosphere. The hypothesis that solar activity also affects the winds of 

the ionosphere is being subjected to continuing investigation. 

However, 

88 
At the Laboratory of Atmospheric Sciences, studies on radio emission by droplets 

colliding in an electric field have led to a quantitative estimate of the radio emission 

spectrum under a given set of conditions in a cloud. This work has implications for 

the use of radio techniques for studying terrestrial cloud processes and may inspire 

a new examination of the microwave emission from cloud-covered Venus. 

Proj ect Polaris cope 

This is a new field of research dealing with the composition and structure of the atmosphere of celestial bodies which made notable advances in FY 1966. A study is 

being made of the brightness and polarization of light from stars and planets with 

telescopes on the ground near Tucson, Ariz., and with telescopes carried on highaltitude balloons ("Project Polariscope"). Changes in the brightness, in the color, 

and in the polarization occur upon reflection or scattering by particles and molecules 

in space or in planetary atmospheres. Most of the scattering phenomena increase in 

importance in the far ultraviolet. 

Preparations for observations from balloon gondolas and, later, from space probes 

and satellites required the solution of difficult technical problems such as in farultraviolet polarimetry made to unusually high precision, in the operation of highvoltage photo-multipliers and power supplies in a vacuum at low temperatures and in 

the development of a telescope platform stabilized to within a minute of arc. 

December 3, 1965 a small polarimeter obtained the first far-ultraviolet measurements from above the ozone layers in the earth's atmosphere. 

Phoenix, Ariz., it obtained measurements on the earth's atmosphere and on the 

surface of the moon from an altitude of 34 kilometers. On May 27, 1966 from 35 

kilometers, a 28-inch telescope obtained precise measurements in the far ultraviolet wavelengths (2200 and 2820 angstroms) on the earth and the moon and on interstellar particles by observations of a star. 

On 

Launched from 

International Years of the Quiet Sun (IQSY) 

The IQSY, which covered the period from January 1964 to December 1965, was an 

international program for cooperative observations of the sun and its effects upon the 

earth during the low activity period of the solar storm cycle. It supplemented the 

observations made during the International Geophysical Year (IGY) from July 1957 to 

December 1958 -- a period of high activity in the sun's 11-year cycle. 

Since the conclusion of the observational period of IQSY on December 31, 1965, 

efforts have been devoted to reducing and analyzing the large amount of data collected 

around the world by individual investigators and made available to all through the 

World Data Centers. 

processes and their relationship to the solar and terrestrial atmospheres, and into 

the interaction between these two atmospheres. 

From these studies should come new insights into solar 

Solar EcliDse in South America, November 12, 1966 

The United States solar eclipse expeditions to South America, coordinated by the 

National Science Foundation, included approximately 40 different American agencies, 

spending some $10 million transporting 300 scientists and a half-million pounds of 

equipment (valued at $8 million) to eclipse sites. 

89 
In an eclipse, the diameter of the moon just covers the diameter of the sun -- an 

accident of size and distance that permits scientists to observe solar features otherwise masked by the brilliance of the sun and by the brightness of the sky. 

November 12, 1966 eclipse began at sunrise west of the Galapagos Islands, continued 

in a southeasterly direction across Peru, Bolivia, Argentina, and Brazil, moved 

across the South Atlantic Ocean and ended at sunset off the coast of Africa. The path 

of totality was never more than 55 miles wide and the duration of totality at its maximum was about two minutes. 

The 

Observations by the U. S. scientific team were made from land-based sites located 

along the solar eclipse path from the coast of Peru to the extreme southeastern 

corner of Brazil. In addition, five jet aircraft were used to race along with the 

moving shadow as it moved across the South Atlantic Ocean. 

scientists to conduct their experiments for about three minutes, compared to the less 

than two minutes available to the ground-based researchers. 

aimed at investigating the changes in the earth's ionosphere and stratosphere brought 

about by the eclipse, and balloon-borne instruments, used to monitor ozone concentration and its change with solar illumination, provided U. S. scientists with valuable 

additional data. 

This enables airborne 

Rocket programs, 

The American studies were part of an overall plan to develop a "history" of a complete solar cycle and the effects of solar events on the earth's atmosphere. Teams 

of scientists from Argentina, Bolivia, Brazil, France, Italy, Japan, The Netherlands, 

Peru, and other countries also observed the eclipse complementing the extensive 

U. S. observations. Thus, from the standpoint of scientific data collection, the 

great variety and number of observations and experiments made this one of the most 

completely observed solar eclipses on record. 

U. S. Antarctic Research Program 

The U. S. space effort has several ties with Antarctica: Data on the ionosphere and 

magnetosphere obtainable only in the high latitudes owing to the configuration of the 

earth's magnetic field, result from investigations using a 21 -mile-long antenna, 

satellite readout stations, and cosmic rays apparatus. Satellites are also monitored 

for the space programs of several agencies to help determine the shape of the geoid, 

refine orbital paths, acquire gravity data, and establish geodetic ties. 

Antarctic environmental factors provide useful parallels to those hypothesized for 

extraterrestrial bodie s. The National Aeronautics and Space Administration, with 

the cooperation of Foundation grantees performing research in the ice-free areas, 

tests hardware and techniques being developed for space exploration, such as lifedetecting samplers and lunar drills. 

program in a remote and hostile environment have led to a close study of the U. S. 

programs in Antarctica by several NASA groups. 

Logistical aspects of the conduct of a research 

90 
DEPARTMENT OF COMMERCE CHAPTER 

VI11 

INTRODUCTION 

A significant number of the activities of the Department of Commerce contribute to 

the Nation's space program. The major organizational components which contribute 

directly are three science and technology bureaus, the National Bureau of Standards, 

the Environmental Science Services Administration, and the Office of State Technical 

Services. The fourth science and technology bureau, the United States Patent Office, 

contributes indirectly through the issuance of patents on inventions with space applications. 

Advisory Board, which consists of 18 non-Government leaders in science, education, 

industrial research, business, and labor. 

In addition, the Department has the benefit of the Commerce Technical 

ENVIRONMENTAL SCIENCE SERVICES ADMINISTRATION 

The Environmental Science Services Administration is engaged in fulfilling the 

Department's responsibility to describe, understand, and predict the state of the 

atmosphere, the oceans, the space environment, and the size and shape of the earth. 

HIGHLIGHTS OF 1966 

With the successful launches of the Environmental Survey Satellites, ESSA 1 and 2 

in February, the Administration established the world's first operational weather 

satellite system. These satellites with ESSA 3, launched on October 2, 1966, 

provide regular and reliable daily weather observations of the entire globe for 

central analysis, and local area photographs for more than 180 ground stations 

scattered around the world. 

ESSA assumed control of a meteorological space system on March 15, 1966, when its 

National Environmental Satellite Center took over the operation of the ESSA 2 

satellite. The National Environmental Satellite Center assumed control of ESSA 1 

and TIROS IX on June 21. 

The Institute for Telecommunication Sciences and Aeronomy designed a solar proton 

counter which will be flown on the TIROS M satellite late in 1968 and on subsequent 

operational ESSA satellites. 

solar disturbances which can affect the operation of manned and unmanned satellites 

and supersonic aircraft flying at high altitude s . 

This instrument will provide data to detect and forecast 

The quick response of the Weather Bureau's Space Operations Support Division in 

providing a forecast for an alternate splashdown area for the GEMINI 8 flight, 

enabled smooth recovery operations when this manned flight had to be terminated 

early because of an emergency situation. ESSA satellite data contributed significantly to preparation of this emergency forecast. 

91 
In September 1966, after a delay of more than two years, an exchange of weather 

satellite data took place over the Washington-Moscow data link. 

established in 1963 pursuant to a bilateral agreement between the United States and 

the USSR for the exchange of satellite data. 

position to furnish satellite photographs, analyses, and infrared data acquired from 

their COSMOS 122 experimental satellite which was launched on June 25, 1966. 

This link was 

The Soviet Union was finally in a 

The Coast and Geodetic Survey and the Institute for Earth Sciences effected a direct 

geodetic connection between North America and Europe by geometric satellite 

triangulation. 

common world geodetic reference datum. 

This connection is the first step toward the establishment of a 

Meteorological Satellites 

The daily, worldwide coverage capability desired for the weather system was made 

possible by redesigning the TIROS satellite so that its cameras look out of the side 

of the spacecraft instead of its base, and by orienting the satellite in its orbit so the 

spacecraft rolls along in its orbit like a wheel. As the satellite rolls along its path, 

each camera looks directly down at the earth once during each revolution of the 

spacecraft, so the cameras can photograph the earth from any part of the orbit. 

The special configuration of spacecraft and orbit necessary to establish the TOS 

system was tested successfully in 1965 with the TIROS IX satellite, launched by the 

National Aeronautics and Space Administration on January 22. 

this satellite were used to provide worldwide analyses of clouds for daily operational 

use. 

Photographs from 

ESSA 1 and 2 

The Environmental Survey Satellite, ESSA 1, was launched February 3, 1966 from 

the Cape Kennedy launch facility. The launch was carried out for ESSA by the 

National Aeronautics and Space Administration. This satellite, although identical 

in configuration to TIROS IX, became the first operational satellite of the TOS 

system. 

satellite for later transmission to ESSA Command and Data Acquisition (CDA) 

stations at Gilmore Creek (near Fairbanks), Alaska, and Wallops Station, Virginia. 

The signals from ESSA 1 were transmitted via high speed data links from the CDA 

stations to the National Environmental Satellite Center at Suitland, Maryland. The 

signals were then reconstituted into pictures. Latitude -longitude grids and coastal 

outlines generated by a high speed computer were electronically merged with the 

pictures processed in NESC. 

handling and analysis time. 

The pictures taken by ESSA 1 were stored on tape recorders aboard the 

This procedure resulted in a marked decrease in 

During the time ESSA 1 was fully operational, an experiment in computer rectification of cloud pictures was carried out. 

3OoW to 15OoW was digitized and the picture elements spread out onto a Mercator 

map of the area. The computer put the digitized map on a magnetic tape which was 

then fed into a converter, and the cloud mosaic was transmitted via facsimile to the 

Tropical Analysis Center at Miami. 

period ending July 25, the date on which one of the cameras on ESSA 1 failed. 

The area between 300N and 300s from 

These maps were sent during the three-week 

92 
The loss of one of the two cameras of ESSA 1 reduced its capability for global coverage by about forty percent. 

October 2, the day ESSA 3 was launched, was obtained by using the combined capabilities of ESSA 1, 2, TIROS IX, and NIMBUS u. While this patchwork operation was 

relatively successful, complete global coverage was not obtained. 

difficulties inherent in using data from these different systems resulted in a large 

increase in the time needed for the preparation of analyses, and hence, delays in 

dissemination of the data. 

The cloud photography needed between July 25 and 

In addition, the 

ESSA 2 was launched for ESSA by the NASA on February 28, 1966. Some 35 foreign 

nations had installed the special equipment needed to receive pictures directly from 

this satellite. ESSA 2 is equipped with Automatic Picture Transmission (APT) 

cameras that take pictures of the area beneath the satellite and telecommunications 

equipment to broadcast the pictures to simply equipped ground stations within a 

2000 mile range of the satellite. 

reliably. 

been unqualified enthusiasm. 

have been established by both foreign and domestic interests at a rate of about seven 

stations per month, for a current total of over 180 stations in 45 countries. 

To date the ESSA 2 satellite has been operating 

The response to the direct transmission of these satellite pictures has 

Since the start of ESSA 2 operations, new stations 

ESSA 3 

The ESSA 3 satellite was launched October 2, 1966 into its near-polar orbit at an 

average altitude of 774 nautical miles. 

114.5 minutes. 

side of the earth. 

processed as were the ESSA 1 photographs. 

The satellite orbits the earth once every 

It takes and stores 12 photographs on each pass across the daylight 

The picture signals are telemetered to the ground and are 

ESSA 3 is equipped with two Advanced Vidicon Camera System (AVCS) units, each 

capable of maintaining global cloud cover surveillance without use of the other 

camera. 

This configuration is designed to double the useful lifetime of the satellite. 

area covered by each picture is 4 million square miles. 

the number of pictures required for global coverage from the 450 per day taken by 

ESSA 1 to 144 per day. The decrease in total number of pictures has the effect of 

decreasing the amount of time needed for processing and analyzing the data. In 

addition, the number of television lines per picture has been increased from 460 

lines to 830 lines, which results in a corresponding increase in the information 

contained in the photographs. 

The second camera is held in reserve in the event the first camera fails. 

The 

This area coverage reduces 

TIROS VII-X 

Each of the last four satellites of the TIROS series has one camera usable. TIROS 

VII and VIII have been in orbit for three and one-halfand three years respectively. 

TIROS IX and X have been in orbit for 23 months and 18 months. While none of these 

satellites is used routinely, specific camera capability is used occasionally to obtain 

photographs for special purposes. During the period between July 25 and October 3, 

when only one camera of ESSA 1 was operational, TIROS IX and occasionally 

TIROS VII and X were used to complete the coverage necessary for operational 

purposes. 

93 
NIMBUS I1 

NASA's NIMBUS 11 satellite, launched May 15, 1966, carried an experimental Medium 

Resolution Infrared Radiometer (MRIR) system which provided data of great interest 

to research meteorologists. 

pictorial representations of the radiation flux from five separate spectral regions. 

The data contained information related to the horizontal distribution of water vapor 

and carbon dioxide over the earth, measurements of surface and cloud top temperatures, outgoing terrestrial radiation, and the earth's albedo, or reflectivity. 

data on water vapor distribution are particularly useful in studies of hurricanes, and 

other large scale weather systems. The other sensors on NIMBUS II were television 

cameras for both stored and direct readout, and a High Resolution Infrared Radiometer (HRIR) system. Pictorial representations from the HRIR system were used in 

place of picture data during the time between the failure of one camera on ESSA 2 and 

the launch of ESSA 3. The cameras for stored pictures failed on September 1, the 

HRIR system failed November 15, and the MRIR system failed July 28. 

System remained in operation through the end of the year. 

The data from this system were provided in the form of 

The 

the APT 

Advanced Technolonv Satellite - ATS I 

NASA ATS I, launched December 6, 1966, carried two experiments in which ESSA 

participated: 

Ocean area from Australia to the West Coast of the United States between 50°N and 

5OoS, and the WEFAX experiment which uses a satellite to relay weather data and 

cloud charts from central points of the United States to APT stations within range of 

the ATS satellite. 

The Spin-Scan Cloud Camera which takes pictures of the entire Pacific 

Both experiments are working well. 

Centralization of Satellite Operations 

Operational control of the operational weather satellites is now maintained by the 

National Environmental Satellite Center of ESSA. 

of the NESC assumes control of ESSA satellites after the NASA has launched and completed inflight engineering checkout of the satellites. 

March 15, 1966, when the NASA passed control of ESSA 2 to this Center. 

The TIROS Operations Center (TOC) 

The TOC went into operation on 

The TOC prepares and sends commands for operation of the satellites to the Command 

and Data Acquisition stations at Gilmore Creek (near Fairbanks), Alaska, and Wallops 

Station, Virginia, where contact is made with the satellites and command signals are 

telemetered to the spacecraft. The Center monitors the engineering operation of the 

system. 

Digitized Cloud Mosaics 

Digitized cloud mosaics of the Tropical Atlantic, Caribbean, Gulf of Mexico and the 

eastern Pacific were transmitted experimentally via facsimile from NESC at Suitland, 

Md., to the Weather Bureau's Tropical Analysis Center at Miami during the early 

part of July. This successful experiment was discontinued when the number 2 camera 

system of ESSA 1 failed on July 25, and resumed in October following the launch of 

ESSA 3. 

The digitized cloud mosaics are prepared by means of a high speed digital computer 

program. In this process, the signals comprising the cloud pictures are assigned 

94 
numerical values to indicate the relative brightness of each element. These numerical values are then assigned positions on a standard map projection, and a magnetic 

tape is prepared. This magnetic tape is then used as the input signal to transmit the 

mapped data over a standard facsimile data channel to weather stations. 

puter processing results in a product containing at least 100 percent more information 

than the manually prepared nephanalyses (cloud maps) now in regular use. 

plans are to use computer prepared digitized cloud maps to replace manually prepared 

nephanalyses within the coming year. 

This comCurrent 

Re search and Development Programs of the National Environmental Satellite Center 

The Office of Research of NESC is charged with conducting investigations (1) to extract 

from satellite data the maximum possible amount of weather and environmental information, and (2) to devise new or improved ways to obtain from satellite platforms 

environmental information which will contribute toward improvement of the various 

services provided by ESSA. 

Experiment Laboratory of NESC's Office of Research carry out analytical studies, 

research investigations, and experimental programs to achieve these goals. 

The Meteorological Satellite Laboratory and the Satellite 

During 1966 work continued on the interpretation and analysis of cloud pictures and 

infrared data received from the satellites. 

pheric motion, the heat balance of the atmosphere, and the structure and development 

of storms. 

standing of the atmosphere, and improved methods for weather analysis and forecasting. Among these are 

several of particular interest: 

These data are used in studies of atmosThe results of these investigations are resulting in an increased underMore than 60 individual investigations are under way. 

a. 

b. 

C. 

d. 

the flight model of the Sztellite Infrared Spectrometer (SIRS), an 

instrument designed to measure the vertical temperature structure 

of the atmosphere from satellite altitude, was completed during 

1966. 

launch in 1967. 

This instrument will be tested on NIMBUS B scheduled for 

a method developed and tested in 1964 and 1965 for estimating maximum wind speeds in hurricanes using satellite photographs as the 

sole source of data was used operationally throughout 1966 with 

excellent results. 

of a method for using high resolution infrared data, such as that from 

NIMBUS IC, to estimate hurricane intensities and stages of development. 

In 1966 research was started on the development 

methods for improving numerical weather prediction models by the 

use of satellite data will be advanced by the results of studies started 

in 1966. 

and thermal properties of cloud systems seen in satellite photographs 

and infrared data. 

This research is concerned with determining the dynamics 

studies of cloud photographs obtained during the GEMINI flights have 

shown that areas which have had rainfall within the past 24 hours can 

be identified in the satellite pictures. 

fallen recently show as dark streaks, particularly over desert or 

The areas where rain has 

95 
drought areas. 

satellites showed that rainfall areas also can be seen in these lower 

resolution photographs. 

A re-examination of photographs from the weather 

e. the successful test aboard GEMINI 5 of a special spectrograph designed 

to measure cloud heights from satellites has led to the design of a Cloudtop Altitude Radiometer (CAR) which will be developed and ready for 

testing on NIMBUS D in 1969. 

f. Public Law 480 counterpart funds are being used to continue support 

for a joint research project of the Hebrew University of Jerusalem 

and the Israel Meteorological Service. 

of their studies is that the location of the jet stream over North Africa 

and the Middle East can be detected by the presence of cirrus cloudiness 

in the satellite pictures. The daily position and strength of this important weather feature could only be crudely estimated prior to the availability of weather satellite photography. 

An interesting result of one 

Washington-Moscow Data Exchange 

On August 18, 1966 the Hydrometeorological Service of the U. S. S.R. started transmitting to Washington nephanalyses (cloud maps) based on data from the COSMOS 122 

satellite over the Washington-Moscow data link. This line was established in 1963 

pursuant to a bilateral agreement between the United States and the U.S.S.R. for the 

exchange of meteorological data from satellites. On September 6 the United States 

reciprocated by sending analyses and cloud pictures from the ESSA 1 satellite over 

the line. 

The U.S.S.R. sent its first pictures from COSMOS 122 on September 11. In addition 

to cloud photographs, the Soviets have sent pictorial representations of infrared data 

observed over the night side of the earth. Although the United States operational 

weather satellites do not have this capability, two infrared systems tested on the 

NIMBUS I1 satellite has furnished infrared information. By the end of September 

receipt of pictures over the line from Moscow became sporadic for about ten days, 

after which transmissions resumed at the usual rate until October 20, when it became 

sporadic again. The last transmissions from COSMOS were received by the U. S. 

National Environmental Satellite Center on October 26, 1966, and COSMOS has been 

presumed inoperative since then. 

International Cooper ation 

Prior to the launch of ESSA 2 on February 28, the United States furnished to all interested nations detailed information on the ground equipment needed to receive pictures 

from the Automatic Picture Transmission (APT) system of this satellite. At the time 

of launch, approximately 35 nations were prepared to receive the pictures; by the end 

of 1966, over 150 ground stations in 45 countries were in operation and reporting 

receipt of the pictures. 

Early in 1966 a manual, the "APT Users Guide" was prepared and distributed internationally. This manual contains instructions for tracking the satellite, and for 

receiving and geographically gridding the pictures. The manual also includes a 

comprehensive section on the interpretation of cloud pictures from weather satellites. 

96 
TO further aid the world meteorological community in the use of satellite data, meteorologists of the National Environmental Satellite Center wrote a technical note on 

"The Use of Satellite Pictures in Weather Analysis and Forecasting,'' which was 

published by the World Meteorological Organization of the United Nations. 

At the request of the World Meteorological Organization, personnel of ESSA's 

National Environmental Satellite Center prepared material and provided instruction 

for a workshop on satellite data interpretation at the European regional meeting of 

WMO held in Moscow during October 1966. 

During 1966 the National Environmental Satellite Center also provided study facilities 

for WMO and AID Fellows from Argentina, Hungary, India, Japan, Pakistan, and 

Poland for periods ranging from three months to one year. 

by scientists from Afghanistan, Australia, Cameroun, China, England, Germany, 

Hong Kong, Japan, Korea, Laos, Sweden, and Saudi Arabia for one to five days of 

general briefings and short study periods. 

The NESC also was visited 

COAST AND GEODETIC SURVEY OPERATIONS 

The Coast and Geodetic Survey is engaged directly in the space program, using satellites to support its work in geodesy and nivigation, and indirectly through its seismic 

and geomagnetic support to space facilities and activities. The aeronautics and space 

activities of the Coast and Geodetic Survey during 1966 were partly in support of NASA 

space operaticns, and partly in support of the C&GS primary missions. 

Navigational Satellites 

The Coast and Geodetic Survey furnished a report to NASA evaluating the Navy Satellite Navigation System. It was concluded that the system is the best available operational system for navigational control of oceanographic survey work. 

The Navy Satellite Navigation System is currently being used operationally aboard the 

Coast and Geodetic Survey Ship OCEANOGRAPHER. 

fully used to control gravimetric, magnetic, and bathymetric surveys in the North 

Pacific. 

The system has been successGeometric Triangulation by Satellite 

Extensive theoretical studies were performed by the Coast and Geodetic Survey and 

the Institute for Earth Sciences in the field of geometric satellite trangulation as part 

of the continuing effort to improve and refine data acquisition and reduction methods. 

Full advantage was taken of advanced electronic computing and data handling technology for reducing, in a statistically significant manner, increasingly large amounts 

of raw data using mathematical models which account for the higher order effects of 

certain physical parameters. 

detic reference data with accuracies approaching one part in a million. 

The goal of these studies is to obtain worldwide geoEfforts in the satellite triangulation program are concentrated on establishing a 

common world geodetic reference datum, providing connections to the independent 

triangulation datums within a continent, and improving the internal consistency of 

geodetic control within a datum. 

97 
Cooperative agreements between the United States and Canada, the Departments of 

Defense and Commerce, and between the United States and Denmark (Greenland), 

Iceland, Norway and the United Kingdom have made possible an extension of a densification network of satellite triangulation thus effecting a direct connection between 

the North American and European continents. 

of the ECHO I and I1 satellites. 

This network was based on observations 

Cooperative agrezments between the Department of Defense, National Aeronautics and 

Space Administration, and the Depzrtment of Commerce concerning the worldwide 

geodetic satellite program resulted in the launch of PAGEOS in June 1966, and the 

establishing of eight Coast and Geodetic Survey and four Army Map Service camera 

parties on 12 of the 42 stations comprising the worldwide network. 

are presently concentrated in the northern portion of the worldwide network. 

These 12 stations 

The results have proven the superiority of geometric satellite triangulation over 

classic or other geodetic triangulation methods. 

metric satellite triangulation provides both accuracy and economy. 

advantages are not limited solely to the acquisition of new information, but are also 

related to the usefulness of classic geodetic data collected during the past decades. 

These data can now be re-evaluated in light of the more accurate frame obtained by 

satellite triangulation. Thus, the considerable expenditures for field operations in 

the past can be fully exploited in the future. 

The approach developed for geoIts economic 

In connection with NASA’s Earth Resources Survey and Lunar and Planetary Programs, 

the significance of geodetic-cartographic subprograms has been receiving increased 

recognition. In pursuit of these problems and in close cooperation with various NASA 

organizations and the cartographic activity of the U. S. Geological Survey, sensor and 

system oriented studies have been performed to match present space technology with 

problem requirements . 

Progress has been made in the use of precision airborne photogrammetric techniques 

for geometric control purposes. The capabilities of precision aerial photogrammetry 

have been enhanced to such an extent that the method could, for economic reasons, 

and in certain instances, be considered as a substitute”for classic geodetic procedures. 

Operations of the Institute for Telecommunications Sciences and Aeronomy 

This Institute is using space techniques for basic research on the properties of the 

very high atmosphere, and the effect of solar activity on communications and manned 

and unmanned space exploration. Techniques are being developed for monitoring and 

forecasting upper atmosphere and space disturbances. The activities of the Institute 

are described in the next four sections. 

Space Environment Monitoring and Forecasting Activities 

In July 1966, a Space Disturbance Forecast Center located at ESSA’s Institute for 

Telecommunication Sciences and Aeronomy in Boulder, Colo. went into a 24-hour 

per day operation on a trial basis. 

mental Committee for Atmospheric Sciences (ICAS), this Center is being developed to 

meet the common national needs for space environment monitoring and forecasting 

services. Emphasis is being placed on the early development of several key monitoring systems, including a worldwide solar flare patrol and a ground-based solar proton 

Implementing recommendations of the Interdepart98 
detection system. 

under study. 

provided to NASA in support of various unmanned scientific space activities as well 

as to the manned spaceflight program. 

Also, improved techniques for space disturbance forecasting are 

During 1966, a growing number of space environmental services were 

The needs for satellite monitoring of the space environment for the early detection 

and forecasting of space disturbances have been clarified and defined. Short range 

plans include an instrument for monitoring solar proton flux, which will be included 

on the TLROS-M and subsequent improved TOS satellites of the operational environmental satellite system. This instrument will measure protons in the energy range 

from about 1 to 100 MeV. 

eration for inclusion in these spacecraft. 

Solar X-ray and ultraviolet sensors are also under considExospheric Electron Content 

For studies of exospheric electron content, beacon transmitters were launched on the 

NASA Orbiting Geophysical Observatory satellites, OGO 1 and OGO 3. 

mitter on OGO 1, which was launched September 4, 1964, is still returning data which 

are being recorded and analyzed at Boulder, Colo. Owing to failure of the orientation 

system, the attitude of this spacecraft is unfavorable for optimum transmission, hence 

the data are of relatively poor quality. 

The transThe OGO 3 was launched June 7, 1966. 

cause interference in the command receiver and was subsequently shut down to avoid 

blocking the other experiments on board. Recently, an alternative method for overcoming the effect of the interference has been used successfully. 

that the radio beacon experiment may be turned on at least for selected periods in the 

future. 

After launch, the radio beacon was found to 

Hence, it is possible 

Ionospheric Satellites 

The Institute for Telecommunication Sciences and Aeronomy continues its participation 

in the ISIS (International Satellites for Ionospheric Studies) program, studying data 

received from the Topside Sounder satellites ALOUETTE I, ALOUETTE 11, and 

EXPLORER XX. 

The topside sounders have demonstrated the existence of ionospheric irregularities 

which extend continuously along magnetic field lines. 

high frequency radio waves for great distances. 

guided radio waves have bounced back and forth several times between the northern 

and southern hemispheres. These irregularities, called conjugate ducts, were first 

discovered with ALOUETTE I and have been studied in detail with EXPLORER XX; 

their size, distribution, latitudinal and diurnal occurrence pattern, and other features 

have been partially determined. 

These irregularities can guide 

Examples have been found where the 

The topside sounders have proven especially useful at high latitudes where the horizontal variations in electron density are too small to be resolved by any reasonable 

network of ground-based radar sounders. 

resonance observed by EXPLORER XX has led to a much better understanding of this 

phenomenon and has led to its use in studying the ionospheric structure. 

detailed determinations of electron density along the satellite orbit have been obtained 

from the resonances and related phenomena. 

The study of the occurrence of plasma 

For example, 

Through studies of these curves, 

99 
latitudinal variations in gradients of electron density were discovered in the polar 

regions. An understanding of the resonance phenomenon also has led to the development of a new technique for the measurement of local electron density. 

has been used successfully to measure electron densities in the terrestrial inosphere 

and could be used for that purpose in interplanetary space. 

proved to be useful for the study of the ionosphere at lower latitudes, especially 

throughout the equatorial region where ion composition was inferred from field-aligned 

electron density data deduced from ALOUETTE I soundings. 

Ionospheric Rocket Probe 

This technique 

These sounders also have 

A number of instruments for the exploration of the lower ionospheric regions have 

been developed and installed on a NIKE CAJUN rocket (NASA 10.181 AI). For electron density studies, these instruments include a Gerdian condenser to measure 

positive and negative ions, a VLF receiver at 20 Kc/s to obtain the electron density 

profile by means of phase and amplitude measurements of signals from the NBS radio 

station WWVL, beacon transmitters at 2.23 Mc/s and 3.23 Mc/s for Faraday rotation 

measurements of electron densities, and a radio frequency probe utilizing reactance 

measurements of cylindrical sensors to determine electron density, electron temper - 

ature, and negative ion concentration. Photoelectric devices are included: one in the 

infrared region to measure a prominent, excited oxygen line at 1.27 microns; the 

other is in the untraviolet region, to measure the hydrogen (Lyman alpha) line at 

1216 angstrom units. 

same ionospheric parameters by different methods, will yield comprehensive results 

pertaining to the D and E layers of the ionosphere, and will provide data to evaluate 

the alternate sensors. 

The combination of instruments, some of which measure the 

This rocket, which can reach a height of 140 km, is scheduled for launch shortly after 

the launch of a larger rocket, which is instrumented by other groups for dust and 

micrometeoroid concentration measurements. This combination should yield valuable 

new information on the relative effects of these influences on the ionosphere. 

Support for NASA Space Operations 

Telecommunications and Aeronomy Support. ITSA scientists, acting as consultants 

to the NASA, assist in the planning of experiments to be carried out on manned satellites, including the briefing and debriefing of the astronauts. 

cern the airglow layers in the high atmosphere, the twilight bands, a solar eclipse, 

and the zodiacal light due to sunlight scattered by interplanetary dust. 

The experiments conServices to the space program include special advance predictions of radio frequencies 

for communication among the ground control stations of the GEMINI program. These 

are supplemented by special and up-to-the -minute forecasts of propagation conditions 

and distrubances during the course of each mission. 

casts are also provided. 

satellite launching sites contribute both to operations and research. 

national arrangement with COSPAR, the radio and geophysical forecast center 

operated by ITSA assigns the international designations to all satellites and space 

probes launched, and serves as the Western Hemisphere center for notifying the 

scientific community of launchings and relevant orbital information. 

Experimental solar flare foreUnder an interIonospheric sounding observatories at several rocket and 

100 
Seismic Support 

The Seismology Division of the Coast and Geodetic Survey conducted a seismic monitoring program for the National Aeronautics and Space Administration at the Kennedy 

Space Center. It was found that vibrations from industrial machinery produced Calibration inaccuracies in testing laboratories at the Center. The seismic data obtained 

in this program will be used as a factor in the design of a new laboratory in which 

instruments used for calibrating space equipment will be isolated from the existing 

vibration environment. 

Acoustic and seismic coupling of energy from the SATURN 201 launch was monitored 

to determine the magnitude of induced ground vibrations. 

An intentional detonation of 75,000 pounds of solid propellant with a donor charge of 

25,000 pounds of TNT was recorded on seismic instruments at the Rocket Propulsion 

Laboratory, Edwards Air Force Base, Calif. The objective was to define the potential hazards associated with a possible launch failure. 

Vibration measurements taken around various installations of the NASA Goddard 

Space Flight Center showed that the vibrations were of sufficient magnitude to affect 

several test procedures adversely. An accurate knowledge of the seismic history of 

the area was found to be useful in evaluating space system calibrations. 

Geomagnetism 

The Coast and Geodetic Survey made available to the National Aeronautics and Space 

Administration the facilities of ESSA's Fredericksburg Geomagnetic Center. The 

Center provides facilities in which geomagnetic fields for any point on the earth's 

surface or in space can be simulated. 

the design, development, and testing of magnetic instruments employed in the nation's 

space effort. 

This facility has proved an invaluable asset to 

A joint project was conducted by scientists of this Center and of NASA to obtain 

correlations between geomagnetic field measurements obtained on the earth's surface 

and those made by instruments aboard satellites and space probes. 

data from 50 magnetic observatories around the world were collected and correlated 

with the satellite and space probe data. 

correlations. 

Nearly current 

Computer techniques were used to do the 

ESSA's Fredericksburg Geomagnetic Center continued to provide calibration and test 

facilities for the Navy's Project MAGNET instrumentation. 

magnetic data at flight altitudes from oceanic areas still inadequately surveyed for 

magnetic charting purposes. 

Project MAGNET gathers 

Meteor 010 gical Support 

The Space Operations Support Division of the Weather Bureau continued to furnish 

meteorological services to the National Aeronautics and Space Administration in 

support of the manned spaceflight programs. 

program, the next phase of the manned spaceflight program designed to accomplish a 

manned lunar landing, began with the APOLLO 201 flight early in the year. 

the GEMINI flights, the high state of readiness of the flight control program was 

Operational forecasting for the APOLLO 

During 

10 1 
demonstrated when the early termination of the GEMINI 8 mission necessitated a 

quick change of the spacecraft recovery area. The Space Operations Support Division 

forecast favorable weather conditions for the western Pacific, and the GEMINI 8 landing and retrieval were made there. In addition to directly supporting the APOLLO and 

GEMINI flight operations, Weather Bureau units served in a staff capacity at both the 

Manned Spacecraft Center and the Kennedy Space Center. Staff support consisted of 

providing environmental studies and meteorological advice pertinent to the APOLLO 

systems design and development program, and operational planning and facilities 

development. Forecast services were also furnished for systems and component 

tests and evaluation. 

The Weather Bureau also continued to provide meteorological support under contract 

to various National Aeronautics and Space Administration and Department of Defense 

facilities supporting the United States space exploration and research effort. These 

services included forecasting, atmospheric measurements, and technical support for 

launch, test, and performance evaluation of rocket vehicles and payloads. Specialized 

forecasting of meteorological ,parameters are required to assure acquisition of desired 

scientific data from rocket-launched experiments. 

NATIONAL BUREAU OF STANDARDS 

Basic information on atomic and nuclear processes and interactions developed by NBS 

are essential to interpreting data gathered by space explorations from the ground as 

well as by manned and unmanned satellites. 

as negative ions of oxygen and hydrogen, rare earth elements, and frosts of water and 

carbon dioxide. 

phere, outer space, the stars, and other planets. 

neighbor, the moon, NBS developed a special X-ray spectrometer designed to function 

in that inhospitable environment. 

NBS measured the spectra of such species 

The results will be useful to scientists' investigations of the atmosFor exploration of our nearest 

Improvements in the Bureau's atomic clock bring its accuracy to the equivalent of one 

second in 6,000 years. 

sub -nuclear events. 

Improvements are needed for tracking satellites and timing 

Closer to the ground, the Bureau developed a way of predicting failures in transistors, 

made a study of the amount of smoke produced by typical combustible airplane materials when they burn, and developed a new method for marking airplane propellers to 

keep ground crew and other passersby from walking into them. NBS investigations of 

the properties of chemically-strengthened glass will enable engineers to make better 

use of this new material in such applications as aircraft windshields. And a study of 

the nuclear magnetic resonance of liquid hydrogen could lead to a new method for 

metering the flow of this rocket fuel. 

The programs of the National Bureau of Standards in measurement, materials 

research and engineering standards, are important to the national effort in space and 

aeronautics. The host of experimental measurements made by space probes depend 

for meaning and interpretation on the standards of measurement maintained by NBS. 

These same standards, along with engineering standards developed by the Bureau, 

enable the Government to specify their needs in hardware and systems, and enable 

industry to bid intelligently on contracts and sub-contracts to supply the hardware and 

systems. 

materials for demanding space applications, but facilitate such jobs as routine maintenance of conventional aircraft. 

NBS materials research not only enables the space engineer to select 

102 
BASIC MEASUREMENTS AND STANDARDS 

Interpreting Space Data 

All investigations on radiation from the sun, atmospheric reactions and exotic rocket 

propulsion systems depend upon fundamental atomic and molecular data such as atomic 

energy levels, transition probabilities for atomic energy states and energy release or 

absorption when atoms and molecules interact with radiation. 

seek to provide these necessary data over wider ranges and to a higher degree of 

accuracy: 

Many NBS programs 

a. 

b. 

C. 

d. 

e. 

certain two photon processes play an important role in energy transfer 

in the upper atmosphere. 

a method to study these processes in the laboratory for the first time. 

Two photon absorption can now be observed and measured in a cesium 

vapor and in a beam of negative ions of iodine. 

With the availability of lasers, NBS developed 

negative ions of oxygen and hydrogen also play an important role in 

atmospheric and astrophysical problems because of their capacity 

for absorbing light. A technique for the study of light absorption by 

these negative ions was developed while maintaining temperatures 

and pressures characteristic of relevant atmospheric conditions. 

analyses of the atomic spectra from the rare earth elements are 

receiving first priority in the Atomic Energy Levels program. 

spectra and the energy levels determined from the spectra are becoming increasingly important in analyzing the data received from the 

Orbiting Astronomical Observatory (OAO) Project . 

The 

NBS released a critical evaluation of all known published atomic 

transition probabilities for the first ten elements of the periodic chart 

of the atoms, hydrogen through neon. 

first time all the available data critically analyzed to show reliability 

and accuracy for each entry. 

This brings together for the 

bibliographies on the literature of ionization and appearance potentials, 

on gaseous reactions involving small molecules, and other areas of 

chemical kinetics were prepared. A program of critical review on 

topics of chemical kinetic interest is well under way. 

etics Information Center should prove of great value to scientists and 

engineers concerned with propellants and combustion reactions. 

The NBS KinFrost Fingerprinted 

Graphic "fingerprints" of water frost and of carbon dioxide "frost" were obtained in 

NBS measurements. 

which may be composed of crystals of one or of both of these substances. 

prints, or spectra, will be checked against infrared spectra to be obtained from 

Venus in future space probes. Spectra may also aid in climatic studies of the planet. 

For example, it is not known why the clouds surrounding Venus apparently remain at 

the same temperature, both on the bright side of the cloud cover reflecting the sun's 

rays, and on the dark side away from these rays. 

The results should be useful in studies of the Venus cloud cover, 

The finger103 
Radiant Flux Measurements 

A comparison of two absolute radiant flux detectors was made in the spectral region 

500 - 1000 angstrom units. One is a thermopile, the other is a rare gas ionization 

counter. This work is now providing detector standards to NASA and its contractors 

so that their observations on the ultraviolet radiation from the sun can be put on an 

absolute scale. 

Study of Surface Chemistry 

NBS study of surface ionization processes such as the formation of positive cesium 

ions on a heated tungsten surface, is leading to an increased quantitative understanding of principles governing the phenomena. These studies are especially pertinent to 

the development of the ion engines for controlled propulsion of long range space vehicle s . 

Other NBS surface studies are concerned with the chemisorption of gases on metals 

under ultra-high vacuum conditions. 

vacuum, and doubtless laboratory studies will lead to an appreciation of the surface 

condition of materials under space conditions. 

The space environment is also one of ultra-high 

Other work centered about the reaction of atomic hydrogen with condensed film of 

unsaturated hydrocarbons at -196OC. 

hydrogen should provide significant clues to the interaction of atomic hydrogen with 

dust grains in interstellar space. 

This study of surface reactions of atomic 

Radiation Studies 

A program on penetration of high-energy radiation through matter is being directed 

toward charged particles and Bremsstrahlung encountered in a space environment. 

Calculations for aluminum and tungsten absorbers for 100 KeV and 10 MeV electrons 

are showing satisfactory agreement with available experimental data. The energy 

dissipation by electrons in the earth's atmosphere has been calculated, taking into 

account the density variation of the atmosphere with height and the influence of the 

earth's magnetic field. 

natural aurora as well as auroral studies to be carried out with satellites. 

This information will provide a better understanding of the 

Radiation Me asur eme nt 

NBS has started preliminary work to develop dosimetry techniques and standards for 

the Goddard Space Flight Center accelerator laboratory as well as a method to simulate in the laboratory the natural and artificial electron spectrum of the earth's magnetosphere. 

components and the cutoff thicknesses of satellite skins. 

Efforts are also being directed toward radiation effects on electronic 

The NBS synchrotron was used to calibrate the response of particle detectors to low 

energy electrons. 

satellite programs, to measure radiations in the upper atmosphere and in space. 

These detectors will be used by NASA, in its future rocket and 

High Temperature Calorimeter 

The importance of high temperature processes in rocket propulsion, in rocket construction materials, and in propellants, is increasing. NBS developed a calorimeter 

104 
for heat measurements at temperatures between 900° and 250OoC (about 4500OF). 

Measurements made on pure aluminum oxide, the heat capacity standard throughout 

the world, indicate that this calorimeter is the most accurate yet developed for this 

temperature range. 

Data on Diatomic Molecules 

The first of a proposed series of critical compilations of data on the structure and 

spectra of diatomic molecules was published as "The Electronic Spectrum of Carbon 

Monoxide. I' These surveys will provide the "best values" available for the scientists 

working on high temperature reactions, the earth's upper atmosphere, the sun, and 

other celestial bodies. 

New Calibration and Measurement Techniques 

Among the new calibration services recently developed is a system to measure high 

frequency and microwave power to support the urgent needs for calibrating the guidance and detection systems of missiles. 

effectiveness of using lasers in space communications, NBS has developed a new 

method for measuring the energy of pulsed laser beams. 

In support of research being done on the 

Improved Time and Frequency Standard 

It is important to NASA that its tracking stations have extremely accurate time information and that the time be precisely synchronized among stations. To meet this and 

other needs, NBS refined its standard of time and frequency -- popularly known as 

the atomic clock -- until it is accurate to within one second in 6,000 years. A new 

low-frequency radio station was built to improve the broadcast of time and frequency 

signals over the globe, and studies on how to best "code" these frequencies for timesignal information are now under way. 

Plasma Studies 

Plasmas are of strong interest to NASA since, for example, the type of gas which 

builds up in front of the heat shield of a capsule and interrupts capsule-to-ground 

communication during re-entry is known as plasma. 

potential as future energy sources for rockets. 

plasma phenomena and on stable plasmas that can be used as standards. 

Plasma devices also have strong 

NBS is conducting studies on basic 

Time Transmission by VLF Radio 

Very low frequency (VLF) radio station WWVL at Fort Collins, Colo., was established 

on an experimental basis, with support from NASA, for studies of the use of VLF in 

worldwide time synchronization. 

that the system is highly promising. To date extensive reception observations have 

been made at the NASA Coddard Space Flight Center, with the conclusion that WWVL 

propagation stabilities are sufficient for worldwide data accumulation at NASA tracking stations to be undertaken. 

Sufficient data have now been obtained to indicate 

New Microwave Calibration Service 

Work has been completed for the establishment of a new microwave calibration 

service. This is the first calibration service established in the frequency range 1.7 

105 
to 2.6 GHz. Calibration requests in this range have been received from both the 

military and industry; some of the requirements are associated with antennas for 

satellite tracking and moon-to-earth telecommunications systems. 

MATERIALS RESEARCH 

New Standard Materials for High Temperature Steels 

NBS developed three new standards for analysis and quality control in the production 

of certain steels. One represents a relatively new type of age-hardening steels called 

maraging steels. These alloys derived their name from the formation of martensite 

during age hardening. They are given remarkable metallurgical properties by a 

simple heat treatment and are being considered for use as the skin material of supersonic aircraft and space systems. 

Effect of Atmosphere on Metal Properties 

NBS examined the role of the heat treatment atmosphere during the production process 

to achieve optimum corrosion resistance and mechanical properties in steels widely 

used in aircraft and space systems. Other studies have dealt with the effect of various 

atmospheres on metal fatigue, since it is known, for example, that most structural 

metals have higher fatigue strengths in a vacuum than in ordinary air. 

Stressed titanium alloys, in contact with salts (chlorides) at moderate to high temperatures, are known to fail by stress corrosion cracking. When used in supersonic aircraft, these alloys are subjected to these conditions, and failures can occur. Accordingly, NBS is subjecting specimens of these alloys to such environments to determine 

the mechanism, or cause of the failures. 

New Data on Hinh-TemDerature Metal 

NBS scientists recently obtained new reliable data on the characteristics of the element rhenium at very high temperatures. Rhenium is an extremely hard metal with 

a high melting point. 

aerospace developments. This research, conducted with support from the National 

Aeronautics and Space Administration, is one part of a continuing program at NBS to 

provide science and industry with much-needed high-temperature data on materials. 

Because of these properties it has been used in a number of 

High Temperature Properties of Chemically Strengthened Glass 

NBS scientists have determined several mechanical properties of chemically strengthened glass at elevated temperatures. An increasing number of applications for the 

glass are being found, for not only does it have superior mechanical strength, but it 

can be formed in thin lightweight cross sections. 

in aircraft windshields. 

The glass shows promise for use 

Ceramic Semiconductors Found Superconducting 

New knowledge of the superconducting state of matter was obtained in research on 

semiconducting materials at NBS. The findings are especially significant because 

they indicate that by varying the composition of semi-conducting materials it is 

possible to control the essential properties of the superconducting state. 

could be helpful in the development of superconducting materials having properties 

Such control 

106 
tailored to specific applications as in high -field magnets, superspeed switches in 

compact computers, and magnetic shields in spacecraft. 

Studies in Rocket Fuels 

NBS scientists have measured the density of liquid and gaseous oxygen at pressures 

up to 340 atmospheres. This information is valuable in calculating the mass rate of 

fuel consumption in rockets. Also, NBS scientists are "listening" to faint radio 

signals, emitted by nuclei in liquid hydrogen, to determine the flow rate of that super - 

cold liquid. 

nuclear magnetic resonance (NMR) techniques to measure the flow rate of liquid 

hydrogen under conditions that are encountered in the fueling of rockets. 

the NBS program has consisted of extensive basic research to accurately determine 

the nuclear magnetic properties of liquid hydrogen, the determination of feasible 

techniques, and the construction of experimental equipment necessary to measure 

fluid velocity. The next phase of the program will be to construct field equipment 

needed for actual testing at NASA's rocket sites, where liquid hydrogen is used 

extensively as a propellant in many advanced U. S. missiles. 

The purpose of the investigation is to explore the feasibility of using 

To date, 

High TemDerature Measurement Standards 

Working standards for the measurement of temperatures in excess of 20OO0C are 

being developed at NBS through determining the melting points of ceramic materials, 

such as aluminum oxide. This work will help fill a long-standing need for high temperature reference points. 

Emissivity Measurement Standards 

NBS has developed three thermal emittance standards covering the range 800 to 

1600OK. 

emissivity of unknown or new materials. Data are used to select materials for 

satellite construction to majntain the desired internal temperature. 

These standards can be used to calibrate spectrometers for measuring 

Selenological Instrument Developed 

A unique, sanitary, single-crystal X-ray spectrometer was developed at NBS in 

association with the lunar geology effort, NASA Goddard Space Flight Center. 

device, scheduled for completion before the end of the year, will be used in experimentation leading to the development of equipment for lunar geologic exploration. 

The 

ATLAS - CENTAUR Fuel Studie s 

At the request of NASA Lewis Research Center, numerous prelaunch and in-flight 

problems associated with the liquid hydrogen fueled ATLAS- CENTAUR rocket were 

pursued at NBS. Experiments were conducted to determine the response time and 

configuration effects on both liquid level gauges and temperature sensors. 

behavior of these instruments must be known to assure proper propellant loading 

and utilizatiop. 

The 

ENGINEERING 

Transistor Reliability 

Failures among certain transistor types can be predicted from measurements of 

107 
leakage current before they are placed in service, according to a study recently completed at NBS. 

germanium -alloy transistors may increase the reliability of transistorized equipment, 

including weapon systems, communications systems, and space vehicle instrumentation. 

The application of screening procedures developed in this study to 

Semiconductor Flaws 

NBS scientists are investigating defects in semiconductor materials, in order to help 

industry attain the highest possible reliability in these devices. The materials being 

studied in this long-range program are silicon and germanium, essential in the fabrication of transistors and diodes which are now being widely used in specialized electronic assemblies. 

Smoke Danger in Burning Aircraft 

NBS completed one phase of a study for the Federal Aviation Agency on the smoke 

generated by burning aircraft materials. 

concentration of some poisonous byproducts resulting from flaming and smoldering 

fires were determined for a number of materials usually found aboard airplanes. 

Results of this and similar studies will enable engineers to choose materials for 

aircraft that will produce a minimum of dangerous smoke and will also be useful in 

designing systems for removal of any smoke that is generated. 

Smoke measurements and the approximate 

Marking Airplane Propellers 

NBS scientists developed a technique of marking multi-engine airplane propeller blades 

so that the moving blades will be more visible to those servicing or working near a 

plane at night. 

The NBS technique involves application of a 4-inch strip of phosphor paint on the tip 

of each propeller blade, both front and back. 

plane both in front of and behind the propellers. 

phosphor paint to glow; when the propeller is turning, the glowing blade tips form a 

visible circle of light. 

Ultraviolet lights are attached to the 

The ultraviolet light causes the 

Data for Nuclear'Explosion Detection 

NBS is collecting geophysical data on various perturbations which can result from 

naturally occurring phenomena and from nuclear explosions. 

enable the United States to determine more precisely whether or not nuclear devices 

have been detonated at high altitudes. An on-line data processor in conjunction with 

sensors and special-purpose signal conditioners and logical devices is collecting 

data for this project. 

The information will 

OFFICE OF STATE TECHNICAL SERVICES 

The Office of State Technical Services (OSTS), U. S. Department of Commerce, and 

the Office of Technology Utilization (OTU), National Aeronautics and Space Adminis - 

tration, have complementary responsibilities and objectives in disseminating the 

results of Federally-supported research and development for the benefit of the 

national economy. 

ship through which the technological information generated by NASA's space programs 

Accordingly the two agencies have established a working relation108 
are made available to the State designated agencies and educational institutions 

participating in programs under the State Technical Services Act of 1965. 

Cooperative Efforts of OSTS and OTU 

In a joint statement to the State designated agencies, OSTS and OTU announced their 

agreement for cooperative efforts at the national level. 

described the functions, operations, and resources of the NASA Regional Dissemination Centers (RDC's) and recommended that State designated agencies investigate such 

centers as additional sources of scientific and technical information and related services for their State Technical Services programs. 

The joint statement also 

Use of an RDC in STS 

The Pennsylvania Technical Assistance Program (PENNTAP), administrator of the 

STS program for the State of Pennsylvania, announced, September 16, 1966 that the 

Knowledge Availability Systems Center of the University of Pittsburgh, a NASA 

Regional Dissemination Center , will be used to provide technical information to the 

institutions participating in the State's technical services program. The participating 

institutions will pass on the technical information received from the RDC to the 

businesses and industries located in their areas of the State. Other States are following the PENNTAP activities carefully, and it is expected that others will follow 

Pennsylvania' s example. 

109 
CHAPTER 

IX 

INTRODUCTION 

The National Academy of Sciences, a private organization of scientists and engineers 

that serves as an official advisor to the Federal Government, is called upon to 

provide the government with programmatic and policy advice for the national scientific program in space research. 

of the Academy primarily by its Space Science Board, but the counsel of other 

NAS divisions and committees is also made available where aeronautical or space 

re search activities relate to their fields of specialization. 

during 1966 were the Divisions of Behavioral Sciences, Biology and Agriculture, 

and Earth Sciences, and the Committee on Atmospheric Sciences. 

These advisory services are carried out on behalf 

Among those called upon 

SPACE SCIENCE BOARD 

Or eanization 

In addition to its governmental responsibilities, the Space Science Board furthers 

space re search generally by encouraging the discussion of advances and opportunities 

in the field. Internationally, the Board, on behalf of the Academy, represents the 

United States scientific community on the Committee on Space Research (COSPAR) 

of the International Council of Scientific Unions. 

The Space Science Board is composed of 15 members, a number of consultants, 

and several invited participants from the major governmental agencies having 

interest in the space program. These participants, who regularly attend the 

meetings of the Board, include the Administrator of the National Aeronautics and 

Space Administration, the Associate Administrator for Space Science and Applications of NASA, the Executive Secretary of the National Aeronautics and Space Council, 

and representatives of the President's Science Advisory Committee, National Science 

Foundation, and Department of Defense. 

tific subcommittees of the NASA Space Sciences Steering Committee. In its relations 

with the international scientific community, the Board works through its Committee 

on International Relations, which maintains liaison with interested groups. A small 

number of standing committees and ad hoc groups carry out much of the Board's 

work. At the present time, the committees are: Executive Committee, Surfaces 

and Interiors of the Moon and Planets, Life Sciences, Geodetic Uses of Navigational 

Satellites, Potential Contamination and Interference from Space Experiments, and 

Large Space Telescope s. 

Close liaison is maintained with the scien111 
THE NATIONAL PROGRAM 

Scientific Priorities and Balances in Space Re search 

At a week-long meeting in June 1966, the Space Science Board made a study of 

possible alternative courses of the scientific space program for the immediate 

future. Undertaken at the request of NASA, the study proposed to define, in the 

light of competition for resources, a space program of optimal balance among the 

various scientific disciplines and tools and a set of priorities in the exploration of 

space. 

going continuing re fineme nt. 

The findings of the study have been transmitted to NASA, and are underWoods Hole 1966 Study of Cardiovascular and Respiratory Physiology 

The probable effects of long-duration space flight on the human cardiovascular and 

respiratory systems was the subject of a two-week study conducted by the Space 

Science Board at the request of NASA. After initial meetings and preparations 

during the Spring, 25 specialists convened at Woods Hole, Mass, during July 1966 to 

investigate the influences of acceleration, vibration, prolonged weightlessness, 

ambient atmospheric pressure, breathing-gas, and re-entry on the physiological 

functions of man. 

knowledge, and to identify courses of research and technical developments that 

should be undertaken in preparation for long-duration missions. Evaluation of 

flight experience and the factors involved in long-term missions suggested that the 

human cardiovascular and respiratory systems will function under space flight 

conditions; adverse effects of the space environment are likely to be insignificant or 

remediable by suitable life-support mechanisms. The conclusions and recommendations of the Study have been discussed at reporting sessions and were made available 

by the end of the Summer to interested agencies to serve as interim guidance pending 

the publication of the conference proceedings. 

The objectives of the study were to determine the current state of 

Scientists as Astronauts 

The Academy is conducting the announcement, processing of applications, and 

scientific selection of scientists to serve as astronauts in the NASA manned space 

flight program. 

in the natural sciences, medicine or engineering, or the equivalent in experience, 

and present the opportunity to conduct scientific experiments in manned orbiting 

satellites and to observe and investigate the lunar surface and circumterre stria1 

space. Following receipt of all applications by January 8, 1967, selection panels 

appointed by the Academy will evaluate applicants' scientific qualifications and 

transmit a list of recommended candidates to NASA in March. Final selection will 

be made by NASA from among those recommended, and the appointments will begin 

during the Summer of 1967. 

a continuing interest in the scientific roles of man in space and in the use of scientists in space missions. 

scientific qualities and qualifications required of scientists as astronauts and was 

subsequently asked by NASA to undertake the scientific selection of the first group 

of scientist-astronauts in 1965. This year, the program is being administered by 

the Academy's Fellowship Office with the cooperation of the Board and the Office of 

Information; the selection process will again be carried out by members of the ad hoc 

Committee. In preparation for the current program, members of the first group of 

These career appointments are open to persons having a doctorate 

Since 1961, the Space Science Board has maintained 

In 1964, an ad hoc Committee of the Board defined the 

112 
scientist-astronauts have met with members of the Committee and staff to discuss 

their progress, impressions, and suggestions regarding the appointments. 

Life Support for Manned Missions 

Working groups of the Board's Life Sciences Committee are continuing their study of 

present and future methods and requirements for providing life support on manned 

space missions. 

Two of the major aspects of support are nutrition and waste management: 

The Panel on SDace Nutrition 

Following its survey and evaluation of current research programs, the panel 

completed its initial report and recommendations. 

stresses those aspects which will have importance in long-duration 

missions, and it will be followed by a report on the acceptability and 

palatability of certain diets in long-term flight feeding. 

The Panel's study 

The ad hoc Panel on Waste Management 

This Panel is reviewing existing and prospective methods of water 

reclamation and waste disposal within the context of (a) short-duration 

flights -- up to 30 days, (b) intermediate-duration -- 30 days to 1 year, 

and (c) long-duration flights of 1 year or more. 

requirements for short missions can be stored as end items, they can 

be dealt with in the framework of available flight experience. In contrast, 

limitations of weight and space will necessitate some reclamation of water 

and waste disposal in flights of intermediate duration. 

presently concentrating its attention on such missions. 

Since life support 

The Panel is 

Committee on Potential Contamination and Interference from Space Experiments 

From time to time, the possibility arises that a proposed space activity will have 

adverse effects on the environment or on work in other fields. 

made up of specialists in several disciplines, attempts to foresee such eventualities, 

evaluate their likely impact, and, where appropriate, make recommendations to 

responsible agencies or experimenters. 

likelihood of interference, primarily to optical astronomy, that would be caused 

by a large solar reflector placed in high orbit to illuminate portions of the Earth 

during nighttime. 

possible cumulative effects of rocket exhausts expelled into the upper atmosphere, 

and potential contamination of the atmosphere and the Earth's surface by radioactive 

material from space -borne nuclear battery accidents. 

The Committee, 

The Committee is currently examining the 

In the past, problems referred to the Committee include the 

Committee on Large Space Telescopes 

The 1965 Woods Hole Summer Study recommended that a large optical telescope 

be placed in space in order to exploit the advantages offered by the space environment: dark skies perfectly transparent in all wavelengths, absence of optical 

distortions caused by the atmosphere, and absence of gravity effects on the instruments. The Study foresaw that something like 15 years of orderly development would 

113 
be required for such a project. In accordance with a further recommendation, the 

Space Science Board appointed an ad hoc panel of astronomers to work toward this 

Large Space Telescope and to encourage studies of those critical areas where particular research and development are required in the near future to advance the 

program. More specifically, the Committee is a means whereby astronomers can 

(1) provide the scientific experience necessary to define the technical properties of 

the telescope, (2) review technical developments relevant to its design, and (3) provide 

a forum for astronomical interest in the project. Committee meetings during 1966 

were concerned with technical aspects of the design, construction, and operation in 

space of a telescope comparable in size to the largest terrestrial telescopes; and 

with dialogues with other interested astronomers. 

Ad hoc Panel on Small Planetarv Probes 

At its November 1965 meeting, the Board noted the benefits that would accrue to 

current knowledge and to preparations for future space exploration from a systematic 

yet flexible program of small, unmanned space probes to the nearer planets and 

interplanetary space, carried out over the next five years. 

menters was named to examine the possibilities and detail the objectives of the relatively inexpensive probes, and to recommend a balanced program of exploration. 

Drawing on the counsel of interested NASA officials, the Panel has completed its 

initial development of a low-cost, vigorous program. 

A panel of space experiConference on the Martian Atmosphere 

At the request of NASA, the Space Science Board organized a conference of astronmers and spectroscopists to discuss the knowledge available on the Martian atmosphere from spectroscopic observations and to recommend a program that would 

increase that knowledge. 

Accurate information on the Martian surface pressure is one of the critical factors 

needed for the design of a spacecraft intended to land on Mars. Ultimately, soft 

landing of an experimental package will be necessary to obtain knowledge on the 

structure and composition of the planet and of possible existence of living forms. 

Uncertainty exists, however, regarding the density of the Martian atmosphere. It 

is known to be very tenuous, but estimates range from pressures where a parachute 

soft landing would be possible to those requiring a full retrothrust rocket system. 

The difference between the two techniques could determine whether a small package, 

severely limited in its instrumentation, or a larger, more useful one could be 

employe d. 

The findings and recommendations of the conference indicate that refinement of 

present observational techniques and the introduction of available new techniques 

can lead in the near future to substantial increase in knowledge of the Martian atmosphere. 

Solar Activity Conference 

A working conference on future research in solar activity was attended by astronomers 

and solar physicists concerned with radio, optical, ultraviolet and x-ray observations 

of the ,Sun. The symposium was divided into six sessions reflecting the various 

aspects of solar studies, and included summaries of recent findings and work in 

114 
progress; promising lines of investigation; future plans; and suggestions for future 

research. 

INTERNATIONAL ACTIVITIES 

COSPAR Ninth Meeting and Seventh International Space Science Symposium 

Held this year in Vienna, May 10-19, 1966, the Ninth Plenary Meeting of the International Committee on Space Research was structured around the discussions and 

recommendations of its six Working Groups and its specialized panels. Each of 

these groups is concerned with a specific aspect of space research and concentrates 

on the international advancement and exchange of knowledge and techniques, and 

cooperative experimentation in that field. 

the meeting included: (a) the establishment of an international Meteorological Rocket 

Network and procedures for collective distribution of the data; (b) coordinated solarparticle balloon measurements and organization of an alert system; (c) allocation of 

radio frequencies for satellite studies of the ionosphere, propagation, and geodesy; 

(d) compilation of southern star catalogue s; (e) more -detailed provisions for exchange 

of rocket and satellite information; (f) space education and training appropriate to 

the needs of developing nations; and (g) continuing study and refinement of criteria, 

in which the United States has played a leading role, to prevent contamination of the 

atmosphere and planetary bodies by space experiments. 

Some of the principal positions taken by 

The Seventh International Space Science Symposium, held in conjunction with the 

Plenary Meeting, was divided into three sessions: Life Sciences in Space Research; 

Moon and Planets; and Interaction of the Neutral Atmosphere and the Ionosphere. 

Of particular interest were invited papers on recent lunar photography by Ranger 8 

and 9, and Luna 9; circadian rhythms in the space environment; Soviet techniques 

for space probe sterilization; and a series of papers in the "Interaction" session that 

markedly clarified these complex proce sse s. As is customary, the scientific papers 

presented at the meeting are being collected and published. 

The meetings were attended by some 600 persons from 33 member countries and 

international scientific unions. U. S. participation was organized by the Space Science 

Board, which also prepared the annual report and bibliography on U. S. space research 

during 1965: United States Space Science Program, Report to COSPAR. 

International Relations Committee 

In order to broaden the base of the Committee and strengthen domestic liaison with 

the three principal scientific unions adhering to COSPAR, membership of the Board's 

International Relations Committee was expanded to include the chairmen of the U. S. 

National Committees for the International Astronomical Union (MU), the International 

Union for Geodesy and Geophysics (IUGG), and the International Scientific Radio Union 

(URSI). 

International Years of the Quiet Sun. 1964-1965 

The observational phase of the IQSY completed, scientists throughout the world are 

reducing the data obtained and compiling their findings. 

of the International Years of the Quiet Sun will be held in London in July 1967 jointly 

with the next year's COSPAR Meeting and Space Science Symposium. 

The final General Assembly 

Since many 

115 
space research activities are closely related to IQSY disciplines, COSPAR has 

maintained close cooperation in the planning and accomplishment of IQSY objectives. 

The current activity of one of its Working Groups is concerned principally with 

planning for observational coverage during the coming solar maximum, about 1968, 

which is expected to equal or even exceed the level sf solar activity during the 1957-58 

maximum of the ICY. 

new ones added. 

been carried out by the Academy's Committee for the International Years of the 

Quiet Sun, working closely with the Space Science Board. 

To this end, COSPAR technical manuals are being revised and 

The coordination and planning of U. S. participation in IQSY has 

World Data Centers 

The World Data Centers, established under the auspices of the International Council 

of Scientific Unions, collect data from many geophysical sources, especially 

ionospheric physics, solar activity, aurora, airglow, geomagnetism, and meteorology, 

and from a great variety of experiments on board rockets, satellites, and spacecraft. 

There are three World Data Centers: World Data Center A, in the United States; 

World Data Center B, in the U. S. S. R. and Czechoslovakia; and World Data Center C, 

in Western Europe and Japan. Each Data Center is divided into a number of Subcenter s representing the major discipline s of geophysics and space re search. 

Rocket and Satellite Subcenter of WDC-A which collects and exchanges results of 

re search conducted with spacecraft and sounding rockets continues to function under 

the aegis of the Space Science Board. 

The 

DIVISION OF BEHAVIORAL SCIENCES 

Committee on Hearing, Bioacoustics, and Biomechanics 

'IOrientation in the Exploration of Space" was the subject of a workshop sponsored 

by the Committee and held at NASA Ames Research Center, January 25-27, 1966. 

The general objective of the meeting, which brought together about 150 scientists 

from all over the world, was to review research on the vestibular organs, the 

semi-circular canals and the otolith apparatus of the ear. 

organs to space flight conditions, particularly weightlessne ss and acceleration, 

are of importance in planning of future space missions. 

ings is underway, and a-rrangements are being made for a similar workshop to be 

held in January 1967. 

The responses of these 

Publication of the proceedA Subcommittee on Aircraft Noise Around Airports was formed during 1966 to assist 

NASA, the Federal Aviation Agency, and other appropriate agencies, in the planning 

and accomplishment of research in this area. 

particular to advise on the psychoacoustic re search needed for quantitativd definition 

of tolerance levels, the habituation to be expected, and the possible advantages of 

noise parametric changes. 

The Subcommittee was asked in 

Committee on Vision 

During 1966, the Armed Forces-NRC Committee on yision was called upon to 

assist NASA in evaluating a proposed vision tester for use by astronauts while in 

orbit, and to advise the NASA Ames Research Center in the continuing improvement 

of space simulators. 

116 
Both Committees were asked to assist in the critical review of NASA's Bioastronautics 

Data Book and to recommend appropriate revisions for the next edition. 

have been completed and the reports forwarded to the Agency. 

These tasks 

DIVISION OF BIOLOGY AND AGRICULTURE 

Committee on Remote Sensine for Aaricultural PurDose s 

The Committee serves in an advisory capacity to those universities and other organizations interested in aerial sensing from aircraft and orbiting satellites of terrestrial 

soils, plants, and animals. These studies have indicated that aerial photography and 

satellite imagery in the infrared and other wavelengths offer much promise for 

accurate and rapid assessment and inventory of agricultural re sources, crop growth 

and health, density of animal populations, and the like. A Committee monograph on 

the subject is in preparation. 

DIVISION OF EARTH SCIENCES 

Committee on Space Programs for Earth Observation 

The Committee is advisory to the U. S. Geological Survey which, among other 

interested government agencies under the leadership of NASA, is undertaking a 

series of studies to define the geologic, hydrologic, geographic, and cartographic 

applications of scientific data to be acquired from Earth-orbiting satellites. These 

preliminary studies include early definition of: (a) instruments that are to be used 

to obtain information; and (b) scientific uses of the data. 

Committee on Remote Sensine of Environment 

The Committee was established to determine the status of sensor technology and its 

application to research on the Earth's environment. 

aerial and spacecraft platforms employed in combination with such sensors as multiband photography, ultraviolet, passive microwave, and infrared sensors, and radar. 

The Committee cooperates with other groups active in sensor technology and provides 

guidance and recommendations for development of a stronger national program in this 

field. 

It is investigating the use of 

Committee on GeoeraDhv 

The Committee on Geography, advisory to the Office of Naval Research, has supported 

a number of activities in the field of remote sensing, emphasizing both aircraft and 

satellite platforms. Principal among them have been the annual University of Michigan Symposia on Remote Sensing, with published proceedings, and the conference on 

the "Use of Orbiting Spacecraft in Geographic Research" held at the NASA Manned 

Spacecraft Center, Houston, January 28-30, 1965. The conference proceedings, 

Spacecraft in Geographic Research (NAS-NRC Pub. 1353, 1966), contains specific 

lists of objectives and requirements for observational satellites employed in fields 

incorporated in or allied to geography. 

117 
International Hvdrdogical Decade. 1965 - 1974 

The U. S. National Committee for the IHD coordinate s and stimulate s U. S. hydrological 

studies carried on in connection with the international program. The Committee has 

proposed that a satellite information system be developed which would measure 

various hydrologic parameters such as glaciers, snow cover, runoff, and vegetation. 

COMMITTEE ON ATMOSPHERIC SCIENCES 

The Feasibility of a Global Observation and Analysis Experiment (NAS-NRC Pub. 

1290, 1966) is a report of the Committee's Panel on International Meteorological 

Cooperation, prepared as a U. S. response to a United Nations resolution inviting 

the international scientific community to develop programs of atmospheric science 

re search to complement those of the World Meteorological Organization. In identifying the components required to obtain a physical definition of the large-scale motions 

of the entire lower atmosphere, the report stresses the applicability of space research 

tools. It advances a preliminary concept for a fully integrated observational, interrogation and communications system using satellite -borne sensors in conjunction with 

balloons, oceanic buoys, automatic land-based observing platforms, ships, and aircraft. A practical goal for this experiment is to develop a capability in long-range 

weather prediction. 

period of about two weeks is a sound scientific possibility. 

The studies indicate that extension of daily predictions for a 

The Committee and its specialized Panels examine present activities in re search 

and education as they relate to the opportunities and future progress in the atmospheric 

sciences. In addition, special studies requested by the Federal Government have been 

conducted. Currently, the fields under study include air-sea interaction, atmospheric 

electricity, and weather and climate modification. 

Committee on SST-Sonic Boom 

The 16-man Committee was established in 1964 in response to the President's request 

to the National Academy of Sciences to "plan an expanded sonic boom program. It Since 

its inception, the Committee has held 16 meetings and has worked closely with responsible government officials, particularly in OST, FAA, NASA, DOD, Department 

of Agriculture, and the President's Advisory Committee on Supersonic Transport. 

The Committee's position on various aspects of the supersonic transport sonic boom 

problem has been made available to the heads of interested government agencies. 

In addition to 6 meetings of the Committee and numerous meetings of several subcommittees over the past year, representatives of the committee and its NAS 

staff have attended 8 meetings of the OST Coordinating committee on Sonic Boom 

Studies as participant-consultants. Discussions in these meetings have concentrated 

on recent results on sonic boom field tests and other shorter-range aspects of the 

sonic boom problem. 

In general, the Committee has continuously urged that additional fundamental 

research on those portions of the problem that have not yet been resolved be 

supported by FAA, NASA, and DOD in order that the effects of the sonic boom on 

people, animals, and structures can be predicted with greater precision. 

Committee is currently searching for ways in which the sonic boom can be reduced 

as it is generated at the vehicle. 

The 

118 
SMITHSOWIAW ASTROPHYSICAL 

OBS ERV AT0 RY 

INTRODUCTION 

CHAPTER 

X 

Ten years of satellite geodesy culminated in the presentation of the Smithsonian 

Standard Earth, a representation of the geopotential and the figure of the Earth. 

Significant revisions have been made in the atmospheric model derived from 

satellite observations. 

Other significant accomplishments of the Observatory this year included: 

a. 

b. 

C. 

d. 

e. 

f. 

the SA0 Star Catalog of data on nearly a quarter of a million stars 

was published. 

a balloon carrying a spark chamber to detect energetic radiation from 

celestial sources was successfully flown. 

a method was proposed for radio communication on the moon. 

analysis of radar, infrared, and other observations led to the conclusion that the dark areas on Mars are elevations, the bright areas 

lowlands, and that parachute landings of modest spacecraft on the 

planet might be possible. 

two successful injections of artificial meteors into the atmosphere 

were recorded simultaneously by optical and radar devices. 

the GEMINI 6 and 7 rendezvous was photographed. 

The Observatory continues to operate a network of stations for the photographic and 

laser tracking of artificial satellites; several networks for meteor astronomy; 

laboratories for analyses of meteorites; and other facilities for gathering data. The 

burden of research is carried on by 55 scientists engaged in studies of meteors and 

meteorites, geodesy, aeronomy, stellar atmospheres, gamma rays, radio astronomy, planetary environments, and other topics. 

OPTICAL SATELLITE TRACKING 

The Observatory operates a network of astrophysical observing stations around the 

world for the precise optical tracking of satellites. 

teams with permanent observing sites distributed in 20 countries and 29 teams 

available for reentry patrol make visual observations of satellites. 

In addition, 116 moonwatch 

In response to changing scientific needs, the geographic coverage provided by the 

network of astrophysical observing stations was expanded by the move of three of 

119 
the twelve Baker-Nunn cameras to newly constructed sites in Ethiopia, Brazil, and 

Argentina, and by the utilization for the first time of the SA0 modified K-50 cameras 

for geodetic studies. 

sites in Iran and the Netherland Antilles, while a third was set up at a new station 

established in cooperation with the National Technical University in Athens, Greece. 

Two of these K-50 were located at the vacated Baker-Nunn 

In addition to furnishing data for scientific research, the camera stations provided 

launch and tracking support for NASA. Noteworthy among photographic successes 

were a sequence of the PAGEOS launch showingignition of the apogee thrust burn, 

separation and inflation of the balloon, which supplemented and confirmed NASA 

telemetry data, and photographs taken of the GEMINI 6 and 7 rendezvous just as the 

spacecraft began their separation. 

A laser system for satellite tracking operated throughout the year at the New Mexico 

astrophysical observing station. Range measurements accurate to about two meters 

were obtained from the three satellites now in orbit that incorporate retroreflectors: 

EXPLORERS 22, 27, and 29. The range data were used with the Baker-Nunn observations in the computation of satellite orbits. 

considered the scientific potential of the laser data, particularly in analyses of the 

dynamics of the earth. 

A geodetic seminar during the summer 

The SA0 Baker-Nunn cameras have photographed in excess of 60,000 flashes of 

GEOS-A, the first active satellite of the National Geodetic Program. 

reduction of these flashes will be made available to the National Geodetic Data 

Archive for eventual use by the international scientific community. 

second satellite of the Program, PAGEOS, an ECHO-type balloon, was launched, 

and SA0 was given a five-year tracking responsibility. PAGEOS will be used to 

provide simultaneous observations between SA0 Baker -Nunn stations in support of 

the Geometrical Geodesy Program in the Observatory. The SA0 cameras are also 

photographing PAGEOS simultaneously with the Coast and Geodetic Survey, NASA, 

USAF, and international groups in support of cooperative efforts. 

The precise 

At midyear, a 

Using over 40,000 optical satellite observations, Observatory scientists completed 

the Smithsonian Standard Earth, a determination of the geopotential and figure of the 

earth, a milestone in global geodetic investigations. 

nates determined in the sdution are of the order of 10 to 15 meters. The SA0 

Standard Earth will be used as the basis of future orbital analysis and geodetic 

investigation. 

The accuracy of station coordiAtmospheric drag determinations based on tracking data for two high-inclination 

balloon satellites, EXPLORER 19 and EXPLORER 24, have provided information 

concerning the upper atmosphere in high latitudes that was not available before. 

This new information has led to a considerable revision in the SA0 model of the 

diurnal bulge in the atmosphere. 

elongated in the north-south direction and that its center does not move much from 

the equator. 

It now appears that the diurnal bulge is noticeably 

Recent drag studies have also improved our knowledge af the density variations that 

accompany geomagnetic disturbances. While the time delay between the peak of the 

geomagnetic perturbation and that of the atmosphere does not seem to depend on the 

intensity of the perturbation, there appears to be a slight dependence on latitude. 

The delay time is somewhat smaller at high latitudes. It also appears that only 

120 
some of the atmospheric perturbations related to geomagnetic activity are enhanced 

in the auroral zones. 

This, year saw the publication of the SA0 Star Catalog, a project initiated in 1963 to 

lessen the manual labor in photoreduction of satellite films and to provide data for 

the automatic reduction program. 

published catalogs, the four-volume work is a uniform catalog of mean positions, 

proper motions, and other data on nearly a quarter of a million stars throughout the 

sky. 

prepared star charts. 

Drawing information from more than 40 previously 

The data are also available on magnetic tape, and will soon appear on specially 

METEORITIC STUDIES 

The Observatory operates several photographic and radar sensing systems to observe 

and record meteors during their passage in the earth’s atmosphere. 

provide data for scientists studying meteoroids in space and estimating the hazard 

they create for space travel. 

These systems 

A radar system in Havana, Ill., operated jointly with the Harvard College Observatory, makes observations of ionized meteor trails. 

estimates of the number of meteors of various sizes in different orbits and also 

determinations of wind velocities at heights of 50 to 70 miles. 

These measurements permit 

To enable a better estimate to be made of the size of meteors being observed by our 

detection systems, simulated meteors of known composition were fired from rockets 

by NASA at Wallops Island and their passage through the atmosphere observed by a 

network of three photographic and five radar stations. During the year, there have 

been two artificial meteor shots. These stations also make simultaneous observations of natural meteors to assist in providing a closer correlation of photographic 

and radar data. 

Through improved efficiency, the data-acquisition rate of the Prairie Network has 

increased by a factor of three during the past year, with over 350 meteors photographed simultaneously by two or more of the 16 camera stations. Analysis of the 

best observations suggests that the brightest bodies observed ablate severely. In 

these cases, the residue, as meteorites, is small, and always less than one kilogram. 

Several new results were obtained from the study of meteorites at SAO. 

improved scheme for classifying meteorites according to the degree of recrystallization was developed. 

between the degree of recrystallization and the primordial-gas content. (2) From 

the distribution of the nickel in the metal of 10 iron and 10 stony meteorites, the 

rate of cooling from 6OO0C to 4OO0C for these bodies was determined to be between 

l0C and 10°C per million years. This cooling rate has an important bearing on the 

size of the parent planet and on the original location of these bodies in the parent 

planet. (3) A new type of age, called a neutron exposure age, was determined for 

two stony meteorites. 

they were subjected either to significant space erosion or to a neutron irradiation. 

(4) The fall of the Hoba-West meteorite, which is the largest meteorite in the world, 

was determined to have occurred a’Fproximately 80,000 years ago. This result is of 

significance not only to meteoritics but also to the climatology of the region in South 

Africa where the meteorite is located. 

(1) An 

This improved system has led to an interesting correlation 

This age indicates that when these meteorites were in space 

121 
COMETARY STUDIES 

At the astrophysical observing stations, Baker -Nunn photographs were obtained of 

Comet Ikeya-Seki in January and of three new comets discovered in the summer 

from August onwards. The observations of Comet Ikeya-Seki were apparently the 

last obtained anywhere; they are being used to determine a precise orbit. This comet 

belongs to a group that contains at least eight members, and an investigation has been 

made of the possible evolution of the group. 

Baker-Nunn photographs are also being analyzed in a study of comet-tail structure 

and motion. 

A study is also being made of the past histories of all the short-period comets. Preliminary results indicate the presence of a number of comets moving in nearly 

circular orbits between Jupiter and Saturn; one of these comets, SchwassmannWachmann 1, has been observed there. Close approaches to Jupiter cause the orbits 

to be deflected to the vicinity of the earth, where they can be readily discovered. The 

problem of tracing back these orbits is rendered difficult because of repeated moder - 

ate approaches to Jupiter, and a slight error in the starting conditions can have a 

drastic effect on the final result. It is also important to establish whether significant 

nongravitational forces are involved, and for this reason a new discussion is being 

made of the observation of Encke's comet. 

LUNAR AND PLANETARY STUDIES 

Because the moon has no appreciable ionosphere to bend radio waves around its 

curvature, lunar astronauts will find normal radio communication impossible beyond 

their visual horizon. It has now been proposed that radio waves shot into the surface 

of the moon may be bent in a way analogous to ionospheric reflection. 

waves could then be coupled with above-ground antennas to link all parts of the moon. 

The plan depends on the depth of the dry, pumice-like rock thought to exist beneath 

the lunar surface; a preliminary test of the moon's internal structure by an orbiting 

satellite could determine the feasibility of this idea. 

The subsurface 

On the basis of photographs of the moon by NASA's RANGER series, the suggestion 

has been made that during its early life that body was kept liquid by radioactivity 

and that a porous crust with pockets of gas floated on the surface. The old craters 

were formed by meteoritic impacts and volcanism, and the maria and ghost craters 

by lava flows. 

During the November 12 solar eclipse, the Smithsonian astrophysical observing 

station in Peru performed with the Baker-Nunn camera an experiment aimed at 

more accurate determination of the ratio of the moon's diameter to the equatorial 

diameter of the earth. 

the Baker -Nunn are so well known (unlike those of the usual eclipse -observing 

instruments). 

This experiment was possible because the coordinates of 

A comprehensive analysis of radar, infrared, and other observations of Mars has 

led to a variety of new conclusions about the planet that have a bearing on future 

space exploration. 

were discovered, suggesting that the dark areas of Mars are comparable to terrestrial continental blocks, and the bright areas to dry, dust-filled ocean basins. 

Major elevation differences between the bright and the dark areas 

122 
Seasonal variations and wind-blown dust seem capable of explaining the seasonal 

changes on Mars. 

dust of the bright areas. 

spectroscopy of wars refer to an average over bright and dark areas. 

found from the MARINER IV occultation experiment are necessarily biased toward 

elevations and refer to the vicinity of dark areas. 

as typical of highlands, the predicted pressures in the centers of prominent Martian 

bright areas are of the order of 20 millibars, permitting parachute landings of relatively modest spacecraft at these locales. 

The "canals" of Mars are found to be ridges elevated above the 

Pressures determined from ground-based infrared 

The pressures 

If these latter pressures are taken 

OTHER SPACE STUEIES 

On May 28 a spark-chamber detector was successfully flown for six hours at an 

altitude of 125,000 feet from the NCAR Balloon Facility at Palestine, Texas. 

purpose of the experiment was to search for celestial gamma rays with energy 

greater than 50 million electron volts and to measure their flux and energy spectra. 

During the flight, the Crab Nebula, the sun, the galactic plane, and several radio 

sources came into the field of view of the detector. Data from the flight will also 

yield the gamma-ray flux and spectrum in the atmosphere as a function of altitude. 

The data were transmitted from the balloon and recorded on video-tape and kinescope film. 

One 

The kinescope film is now being analyzed. 

A cooperative program with various Argentine agencies has begun to sound the 

earth's magnetosphere by accurately measuring the variation in transmission time 

for HF radio waves guided in the magnetosphere by field-aligned ionization irregularities between conjugate points on the earth. The transmitter is located at the 

SA0 astrophysical observing station in Florida, and the receiver at an Argentine 

Navy installation in Usuhaia in Tierra del Fuego. 

123 
FEDERAL AVIATION AGENCY CHAPTER 

XI 

INTRODU CTION 

The Federal Aviation Agency's basic missions are to insure the safe and efficient 

utilization of the Nation's airspace, by military as well as civil users, and to foster 

civil aeronautics and air commerce. To support these missions, the Agency conducts 

a range of research and development activities centering on efforts to improve the air 

navigation and air traffic control facilities, both individually and as a system; to 

produce improved aircraft and aircraft components and appliances; and to promote 

aviation safety in other ways, including aeromedical research. 

The growth of U.S. civil aviation, remarkable in recent years, continued during 

1966. 

new highs. 

as well as of the airplane. 

as well as of efficiency, in airspace use. 

Key indicators, such as the number of aircraft landings and takeoffs, reached 

Reflected in this growth is past progress in the technology of the airway 

Reflected, too, is progress in the technology of safety, 

ADVANCES IN AIRSPACE USE AND CONTROL 

ARTS and SPAN 

The way toward the automated National Airspace System (NAS) of the future is being 

pioneered by developments that took place during 1966 at New York - developments 

growing out of FAA's ARTS (advanced radar traffic control system) and SPAN (stored 

program alphanumerics) test projects, which the year saw successfully completed. 

Begun in May 1965, these projects complemented each other: ARTS was concerned 

with the traffic problems of air terminals; SPAN with those of air route traffic control 

centers (ARTCC's), whikh control IFR (instrument flight rules) air traffic en route 

between airports. Both projects involved equipment that provides air traffic controllers automatically and continuously with the identity and altitude of aircraft appearing 

on their radarscopes, this information being electronically tagged in alphanumeric 

data blocks to the blips representing the various aircraft, and moving with the blips 

across the radarscope or radar display. 

The SPAN tests, conducted at the Indianapolis ARTCC, were completed in February 

1966, and early in March the equipment was dismantled and shipped to the New York 

ARTCC. This was a step in FAA's program to semiautomate air traffic control in 

the very busy New York area by late 1967. 

dures will make a vital contribution to this important advance in the handling of en 

route air traffic. 

The SPAN-tested equipment and proceResults stemming from the ARTS program will contribute to similarly advanced 

handling of Metropolitan New York airport traffic. 

operational program was completed at the Atlanta Airport in August 1966, and the 

The field appraisal of the ARTS 

125 
equipment is being turned over to FAA's Southern Region for operational use by the 

Atlanta control tower. 

Equipment and procedures similar to those appraised at Atlanta form the basis in 

large degree of a new facility being constructed by FAA at New York's Kennedy International Airport called a "common IFR room. 

New York facility will serve during the interim until installation of a full TRACON M 

capability (see below). 

equipped airports in the Metropolitan New York area -- Kennedy, La Guardia, and 

Newark -- controls its own traffic in a "parcel" of airspace allotted for this purpose. 

Drawbacks to this practice include its dependence on blocked airspace, which requires 

area-transiting aircraft to "tunnel" over or under, and the great amount of coordination necessary between air traffic controllers in the separate jurisdictions. 

common IFR room, by pooling the metropolitan airspace under central control -- and 

by providing substantial automation improvements , including radar and radar -beacon 

tracking -- will enable the controllers to utilize the New York terminal airspace to 

maximum advantage. 

The capability thus achieved for the 

Presently, each of the facilities serving the three radar- 

\ 

The 

NAS En Route Stage A and TRACON M 

As mentioned above, equipment and procedures derived from the ARTS and SPAN 

developments are being used to bring semiautomated air traffic control (ATC) capabilities to New York on an interim and expedited schedule. 

equipment under development for the National Airspace System is called, for the air 

route traffic control centers, the NAS En Route Stage A ATC Subsystem, and for the 

busiest metropolitan airport complexes , TRACON (Terminal Radar Approach Control) 

M. 

The more sophisticated 

Components of what will be the first operational field model of the NAS En Route 

Stage A equipment were being assembled, at year's end, at FAA's Jacksonville (Fla.) 

ARTCC. 

equipment, a key part of the NAS subsystem for ARTCC's. This equipment is used 

by both FAA and the Department of Defense because of its capacity to convert radar 

and beacon data to digital form usable for either air traffic control or air defense 

purposes. The Jacksonville field model is expected to be ready to start fleld tests 

in the first half of 1968. Plans call for the NAS En Route Stage A equipment to be 

installed at other ARTCC's as funds and equipment permit, priority being given to 

those serving the more congested areas and the main routes. The present expectation 

is that all the ARTCC's in the 48 contiguous States will be equipped by the early 1970's. 

The latter half of 1966 saw initial delivery there of common-digitizer (CD) 

The NAS TRACON M (referred to in last year's report as the Metroplex Stage A) is 

intended, under present planning, for metropolitan terminal complexes annually 

generating more than 300,000 instrument operations and normally including more 

than one major airport, served by more than one radar system. A highly sophisticated automation package, TRACON M will be capable of alphanumeric display and 

tracking of both radar and beacon data, and in addition will perform such computerbased functions as flight-plan processing and intersector coordination. 

areas now meeting the foregoing requirements for TRACON M are those at New York 

City, Chicago, Los Angeles, Oakland-San Francisco, and Washington, D. C. Since 

much of the equipment planned for TRACON M is similar to that being developed for 

the NAS En Route Stage A, much of the testing and development will parallel that of 

the ARTCC equipment, at a substantial saving in time and money. 

Terminal 

12 6 
Common IFR rooms like the one being constructed at New York are planned for 

Chicago, Los Angeles, Oakland-San Francisco, and Washington. TRACON M equipment, instead of the less advanced equipment being used initially at New York, will 

be installed at these locations. FAA expects the implementing of these common IFR 

rooms to take place at approximately the same time as the implementing of the 

adjacent centers with NAS En Route Stage A equipment. 

Direct Altitude and Identity Readout (DAIR) Equipment 

TRACON M is the most highly sophisticated version of a design under development by 

FAA for a modular terminal air traffic control system comprehensive enough to meet 

the needs of all radar -equipped terminals. 

dures are scheduled for use at medium-density airports. 

the concept specifies equipment capable of showing the altitude and identity of aircraft 

on controllers' radarscopes in numeric, rather than alphanumeric, form. 

altitude and identity readout (DAIR) equipment also eliminates the advanced functions 

performed by a computer, such as automatic tracking or flight-plan processing. A 

joint civil-military project, pursuant to an FAA-DOD agreement signed in January 

1966, the DAIR development effort is aimed for use at certain military facilities as 

well as at low-density civil terminals. 

Less sophisticated equipment and proceFor low-activity airports 

This direct 

Other Airwav-Improvement Efforts 

Besides the foregoing, a variety of FAA research and development efforts bore directly on the improvement of air navigation and air traffic control. 

able of these (outside the field of aeronautical communications, which follows) were: 

Among the more nota. initial testing of large screen displays to help air traffic controllers 

in their work. Results thus far indicate improvement in handoff 

procedures and making sector mosaics, and better capability for 

resectoring. 

common IFR room. 

Operational evaluations will continue in the New York 

b. first operation of a remote flight strip printer subsystem at the 

Cleveland air route traffic control center. 

at controller positions, this device eliminates the need for manual 

delivery of the strips to the controllers. 

completion of development and evaluation of FAA and U.S. Air Force 

TRACON consoles. 

console development. 

productive use of the air traffic control simulator at FAA's National 

Aviation Facilities Experimental Center, Atlantic City - - particularly 

for simulating, as a means of testing and improving, concepts and 

procedures pertaining to the combined TRACON operation projected 

for the New York metropolitan area. 

By printing flight strips 

c. 

FAA and the Air Force have agreed on a common 

d. 

e. a significant step toward procurement of a time -frequency collision 

avoidance system (CAS) test bed was the coordination of the engineering requirement with the ten organizations (from aviation, Government, and industry) represented on the collision avoidance group. 

The objective is an airborne time-frequency CAS capability that can 

127 
serve additionally as a test bed for future time -frequency applications 

in the areas of data acquisition, navigation, and communications. 

f. proof of feasibility of using radioactive krypton gas in a guidance 

system for taxiing aircraft. 

g. favorable evaluation of an inertial navigating device, on the basis of 

a flight-test program in which a U. S. international air carrier cooperated. Results strongly indicate practicality of this device for over - 

ocean navigation of civil turbojets. 

Ae r onauti cal Communic ati ons 

Management of the radiofrequency spectrum, in which FAA is interested to the extent 

that it affects aviation, gave rise to particularly notable efforts of the Agency in 1966. 

These and other noteworthy FAA activities in the vital field of aeronautical communications during the year included: 

a. participation in U. S. representation attending at Geneva, Switzerland, 

in March 1966, the International Telecommunications Union 

Extraordinary Administrative Radio Conference (Second Session). 

This conference prepared a revised allotment plan for the aeronautical mobile service, providing approximately 17 more radio 

channels to ease congestion of the spectrum. 

b. the engineering (January through June) of 777 specific frequency 

assignments within portions of the radio spectrum reserved for 

use by facilities comprising the National Airspace System, to 

insure an interference -free environment for these frequencies; 

650 of these frequencies were assigned to FAA facilities and the 

remainder to facilities owned or operated by the military, other 

Government agencies, or private industries. 

c. commencement, January 1, 1966, of 50- rather than 100-kilocycle 

spacing between voice channels throughout the civil VHF (very high 

frequency) air-ground communications band (118-136 megacycles). 

The additional radio-frequencies thus made available for air traffic 

control are now being applied, as planned, to expanding aviation 

requirements . 

d. completion of plans and their initial implementation, in the interest 

of air traffic control possibilities, for FAA to work closely with the 

National Aeronautics and Space Administration (NASA) in evaluating 

the applications technology satellite (ATS -B) , which was launched 

early in December 1966. 

e. further progress, within the National Communications System, in 

the worldwide integration of FAA and DOD point-to-point long-haul 

communications, under the FAA-DOD agreement effective February 1, 

1963. 

128 
AIRCRAFT DEVELOPMENT 

Supersonic Transport (SST) 

The competitive design phase of the supersonic transport development program ended 

in 1966. 

The best airframe -engine combination was chosen from the rival airframe designs 

submitted by two airframe companies and the rival engine designs submitted by two 

engine manufacturers. This selection culminated a careful evaluation of the competing designs by a large body of experts that included broad representation from both 

Government and the aviation industry. 

l8-mont.h period of accelerated effort under contracts awarded in mid-1965, extending 

an effort begun in mid-1964, when the best two out of three proposed airframe designs 

and the best two out of three proposed engine designs were selected for further competitive development. 

The designs were those resulting from an 

As 1967 begins, the designs in the winning airframe-engine combination are to be 

further refined and improved under month-to-month contracts, pending decisions re 

prototype construction. If constructed, the first of -the two prototype aircraft called 

for under present contingent planning would be expected to begin flight testing in 1970, 

leading to a proved and certificated SST ready for commercial service by mid-1974. 

Besides the completion of the design competition, 1966 saw further exploration of the 

sonic-boom problem in a 6-month test program launched in June at Edwards Air Force 

Base, Calif. A joint effort of the Air Force, NASA, and FAA, the program gathered 

additional data on the effects of sonic booms generated by aircraft of various sizes. 

A mixture of Air Force bomber and fighter types was used in the tests. 

Economic studies were also carried out: on the prospective demand for long-range 

travel through 1990; on the potential effects of a U. S. -developed SST on the inter - 

national balance of payments; on the costs of the SST, analyzes comprehensively in 

relation to development, production, and operation; and on the aircraft's prospective 

facility and service requirements. 

Other studies and research during the year included work in the areas of airworthiness standards, flight simulation, air traffic simulation, fuels, materials, operational environment, human factors, and flight controls and displays. 

Congress during the year appropriated $80 million to complete the last six months of 

the l8-month design effort, in which the Government's share of the cost was 25 percent, and $200 million to begin the prototype-construction phase. 

Subsonic Aircraft 

In the field of subsonic-aircraft development, FAA's main activity during 1966 was 

in military-civil projects, in which aircraft developed under Defense Department 

contracts to perform military missions are designed to meet civil airworthiness 

standards also -- completely in some cases and with deviations at the discretion of 

the armed service concerned in other cases. Notable items for the year included: 

129 
a. 

b. 

C. 

signing of an FAA-Army memorandum of understanding (in May) 

for a follow-on type-certification program applying to a production 

quantity of a flying crane (Army designation Y CH-54A). Originally 

issued a civil type-certificate by FAA in July 1965, this helicopter 

has been active for many months in the Army's Vietnam operations. 

continued progress in the Army's project for an advanced aerial fire 

support system (AAFSS). A compound helicopter (i. e., having fixed 

wings as well as rotors), this aircraft has civil potential as a highspeed (200 knot) executive transport or utility vehicle. 

further progress in the Air Force's project (launched last year with 

the signing of the design and production contract on September 30, 

1965) to develop a "jumbo" turbojet transport -- the C-5A. Under 

this contract, deviations from civil airworthiness requirements are 

authorized at the discretion of the Air Force. 

The Agency also pursues in the area of aircraft development a continuing program 

focusing - among other things - on safety problems related to aircraft structure and 

materials. 

safety standards applying to this aspect of aircraft development; major emphasis is 

given to the most important safety problems arising from civil aircraft operations. 

Efforts in 1966 were concerned notably with: 

The aim here is to provide a sound technological basis for improved 

a. 

b. 

C. 

d. 

determination of flammability, smoke, and toxicity character - 

istics of cabin-interior materials. 

development of crashworthiness of aircraft fuselages (crashworthiness refers to an aircraft's capability to preserve its 

passengers from injury or death in a crash, as distinguished 

from its airworthiness, or efficiency as a flying machine). Improved techniques were sought for analyzing the crash resistance 

of the fuselage as a step toward design guides for a crashworthy 

fuselage. 

development of a design procedure that upgrades gust design 

standards for civil transport aircraft and accounts for the effect 

of continuous random turbulence on flexible airframe structure. 

development of a design procedure for predicting loads induced on 

a flexible airframe when the aircraft is taxiing on uneven pavement. 

OTHER RESEARCH AND DEVELOPMENT 

Among other notable FAA research and development activities in 1966 to promote 

aviation safety and foster civil aeronautics were the following: 

a. development of a simplified cockpit enabling general aviation 

pilots to acquire full instrument-flight proficiency in an average 

of less than half the average time required when training was 

done with a conventional instrument panel -- 26 hours versus 55. 

130 
b. 

C. 

d. 

e. 

f. 

gh. 

i. 

jk. 

1. 

development of a device for preventing stall-spin accidents in 

general aviation aircraft approaching for landing, and also to 

prevent loss of speed control during accidental flight into clouds 

by non-instrument-rated pilots. 

development of a practical and inexpensive instrument for detecting 

the presence of harmful gases in the cockpit or cabin -- particularly 

carbon monoxide. 

development of a promising device to save aircraft passengers' lives 

in postcrash flame and smoke environments -- a flameproof bag with 

8-minute air supply to be fastened over the head. 

continued research on the nature of the lightning hazard to aircraft 

fuel systems, including lightning-triggering experiments and investigation of fuel-vapor phenomena within the aircraft's tanks. 

laboratory tests of a passive explosives -detection system designed 

to solve the aircraft sabotage problem. 

expansion of research on linear explosives for use outside aircraft 

to make access openings for rescue operations, and for use inside 

aircraft to make emergency exits. 

studies shedding light on how human circadian (24 -hour) rhythms - - 

and hence flight-crew energy and efficiency -- are affected by rapid 

transit of several time zones, as in long jet flights. 

progress toward developing devices to help pilots with the problems 

of both clear -air and storm-produced turbulence. 

appointment of a Noise Abatement Staff to coordinate FAA's efforts 

in implementing FAA's part of the concerted effort called for by 

the President to alleviate the problem of aircraft noise, following 

a special study of the problem and a report to the President on 

March 18, 1966, by a Jet Aircraft Noise Panel of the Office of 

Science and Technology. 

development of more realistic and definitive criteria for flight 

characteristics of both conventional and new types of aircraft. 

studies of the role V/STOL aircraft can play in the Nation's transportation complex, and of National Air space System additions needed 

to accommodate such V/STOL operations. 

131 
FEDERAL COMMUNICATIONS 

COMMISSION 

CHAPTER 

XI1 

INTRODUCTION 

This year saw a continuation of steps toward realization of the global commercial 

communications satellite system contemplated by the Communications Satellite Act. 

Commer cial communications via satellite were expanded to provide limited service 

between the United States and countries in the Pacific area. 

constructed around the world. Additional countries have joined the International 

Telecommunication Satellite Consortium (INTELSAT) so that as of December 31, 

1966, 55 countries had become members. 

Earth stations are being 

In the United States, the Commission authorized Communications Satellite Corpor - 

ation's participation in the construction of third generation satellites. 

sion issued an Order providing for ownership of United States earth stations by 

ComSat and. the other United States international communications common carriers. 

It has concluded its consideration of the circumstances under which, entities other 

than communications common carriers should be permitted to receive direct service 

from the Communications Satellite Corporation, and has initiated an inquiry into the 

legal, technical and economic questions involved in the establishment of communication satellite systems for domestic service. 

The commis - 

REGULATORY ACTIVITIES 

Late in 1965, the Commission issued authorizations to the Communications Satellite 

Corporation for the construction of two new earth stations, one to be located near 

Brewster Flat, Wash., and the other near Paumalu, Hawaii. These stations are 

undergoing final testing. 

Maine station for commer cial satellite communication service between the United 

States and Western Europe. 

In the Fall of 1965 the Commission authorized ComSat to join its foreign partners in 

the construction of additional satellites of a more advanced type than EARLY BIRD 

(INTELSAT I) to be used to fill communication needs of the APOLLO Space Program 

of the National Aeronautics and Space Administration, as well as commercial needs. 

The first of these satellites was launched in October and was to be placed in synchronous orbit over the Pacific. The synchronous orbit was not attained and the satellite 

is in an elliptical orbit over the Pacific. In this orbit it can be used only for limited 

periods of time. 

service under applicable tariffs to authorized communications common carriers for 

the period of time the satellite can be used. 

launched shortly after the first of the year. 

sequently for placement in synchronous orbit over the Atlantic. 

The Commission authorized ComSat to construct three new transportable earth stations, one each to be placed at its regular earth station sites, to provide earth station 

In addition, ComSat continues to operate the Andove$, 

The Commission has authorized ComSat to provide commercial 

A replacement satellite is to be 

A third satellite will be launched sub133 
capability for the NASA APOLLO Program pending the completion of the permanent 

earth stations. 

The Commission also authorized ComSat to participate in the construction of six 

satellites (INTELSAT III) of advanced design, for use at synchronous altitude in the 

global commercial communications satellite system. Each satellite will be capable 

of providing approximately 1200 high quality voice grade channels, and simultaneaous 

communication between a number of earth stations is planned. 

for the first of these satellites is in 1968. 

Tentative launch date 

The Commission issued a report and order on December 8, 1966, revising its interim 

policy governing the ownership of earth stations in the United States. 

vised policy ComSat will own 50% of each earth station and the remaining 50% will be 

divided among the United States international communications common carriers in 

accordance with a fixed quota system. The revised policy applies to existing as well 

as planned earth stations and is to remain in effect until the end of 1969. 

Under the reThe Commission instituted a Notice of Inquiry on March 3, 1966, involving consideration of the legal, policy and technical questions relating to the possible establishment of satellite systems for private or specialized domestic purpose; including 

distribution of commercial and educational television programs. 

novelty and importance of the problems presented, the Commission extended the 

scope of the inquiry and extended the time for final reply comments to February, 

1967. 

In view of the 

The Commission concluded its inquiry into the authorized user question, that is, 

whether or not entities other than common carriers may obtain service directly from 

ComSat. It concluded that only in unique or exceptional circumstances should it 

authorize direct service by ComSat to such entities. 

that the statute provides that ComSat may contract directly with the United States 

Government for the services of the communications satellite system. 

It was recognized, however, 

The Commission authorized live television broadcasts of GEMINI recovery operations 

in the Atlantic Ocean which were relayed via EARLY BIRD from the recovery ship to 

earth stations in North America and Western Europe for distribution by the television 

networks . 

Procurement Activities 

The Communications Satellite Act of 1962 requires the commission to maintain maximum competition in the procurement of equipment and services by ComSat and other 

carriers for the global communications satellite system and satellite terminal stations. To this end, the Commission nearly three years ago adopted its Communications Satellite Procurement Regulations. This past year saw the first amendment of 

the regulations, to exclude from their scope procurement by foreign entities for the 

space segment of the global system. Since January 1966, the Commission staff has 

reviewed ComSat procurements in the amount of 34 million dollars. Major awards 

included the spacecraft and related equipment for the INTELSAT III satellites to be 

launched in mid-1968 , and equipment for the Northwest (Brewst.er Flat, Wash.) and 

Hawaiian earth stations. 

134 
FREQUENCY SHARING CRITERIA AND INTERNATIONAL 

COORDINATION OF FREQUENCY USAGE 

In keeping with internationally agreed criteria, the Commission's rules specify 

sharing criteria and technical limitations intended to provide adequate protection 

against mutual interference so as to permit the communications satellite service to 

share use of certain microwave bands used by terrestrial services. 

is based on power limitations, permissible angles of elevation for earth station antennas, geographical separation of stations in the sharing services, and advance 

coordination of assignments. 

This protection 

These criteria are under continuing review at national and international levels to 

determine the degree to which present limitations can be eased. 

members participated in this and other work as members of the United States Delegation to the XI Plenary Assembly of the International Radio Consultative Committee 

(CCIR), Oslo, Norway, June 1966, convened under the auspices of the International 

Telecommunication Union. 

Commission staff 

The Commission, at the request of INTELSAT, coordinates with all administrations 

representing parties to the Interim Agreement the proposed frequency usage and 

physical deployment of INTELSAT satellites to be used in the global communication 

satellite system. When general agreement has been reached on the frequencies to 

be employed in the space segment of the system, the Commission notifies the International Frequency Registration Board of the ITU, on behalf of all administrations 

concurring in the frequency usage, so that the information may be entered in the 

Master International Frequency Register. 

AERONAUTICAL DEVELOPMENTS 

The Commission, in discharging its statutory responsibilities with respect to nongovernment uses of radio for aviation, prescribes the manner and conditions under 

which frequencies may be assigned for aeronautical telecommunications purposes. 

Such purposes include flight test telecommunications and telemetry functions used 

in the development and production of missiles, rockets, and satellites as well as 

aircraft. Additionally, the Commission assigns frequencies to aircraft radio stations, aeronautical enroute, radionavigation, aeronautical advisory, and other 

stations comprising the aviation radio services. 

Commission staff representatives have continued working, both nationally and inter - 

nationally, with other government agencies and the aviation industry towards development of system parameters and application of space radiocommunication techniques 

to the communication requirements of international civil aviation. Of particular 

interest in that regard was the study, prepared by the Commission staff representatives and industry, submitted by the United States Delegation and adopted by the 

ITU Extraordinary Administrative Radio Conference - Second Session (Aeronautical), 

Geneva-1966, of factors to be considered in the utilization of space communication 

techniques in the aeronautical mobile (R) service. Further, during January, April, 

June and November, 1966, tests were conducted by the air transport industry under 

authorization of the Commission to assess the relative merits of amplitude versus 

frequency modulation emission techniques, using current power versus substantially 

higher power aboard aircraft, as elements in a communication system between aircraft and aeronautical stations, relayed via satellite. 

135 
Commission staff representatives participated in the preparation of material which 

was submitted by the U. S. Delegation to the Communications -Operations Divisional 

Meeting, International Civil Aviation Organization (ICAO), Montreal, October - 

November 1966, responsive to the meeting agenda item on space communications. 

The Commission authorized Aeronautical Radio, Inc., and various scheduled airlines 

to participate in tests using NASA's Applications Technology Satellite #1 (ATS-I) 

during the first half of December. Satisfactory communications were exchanged, 

relayed via ATS-1, between a ground terminal and aircraft over the Aleutian Islands, 

Miami, New York, Kansas City and off the U.S. west coast. Communications were 

also exchanged, using ATS-1 relay, between aircraft located over the Aleutians and 

Miami and between aircraft over Miami and San Francisco. 

136 
INTRODUCTION 

USIA continued to tell the story of the United States in space, as part of its mission 

of informing foreign nations and audiences. 

range of USIA media were employed. 

covered the GEMINI flights and other special aspects of the space program. 

day developments were reported by the Voice of America and the Agency's wireless 

service. 

foreign nationals learned about space from Agency book translations, libraries , cartoon strips, space exhibits, pamphlets, pictures, and newspaper features. 

To carry the space story abroad, a wide 

Day-toMotion picture and television productions 

In the 104 countries where the U. S. Information Service staffs 218 posts, 

In a year dominated by GEMINI flights, USIA exhibited the GEMINI five spacecraft to 

over two milli,on persons in Argentina, Brazil, and Mexico, put the GEMINI 10 spacecraft on view in Japan, and organized Presidential good-will tours to the Far East 

and Latin America for astronauts of the GEMINI 6 and 7 and 8 and 11 missions. 

With the first manned APOLLO mission in prospect, USIA was already telling the 

APOLLO story, and further materials on this project were in preparation. 

GUIDELINES 

The following guidelines formed the basis of USIA treatment of space activities: 

a. 

b. 

C. 

The United States has a broadly-based, long-range space program 

which works to develop the technology equally for exploration, applications, and manned space, and reflects a capability second to 

none. 

The U. S. is committed to sharing space technology with other countries 

through international programs, sharing scientific results with others, 

conducting manned space operations openly, putting space to work for 

man by practical applications, and landing a man on the moon and 

returning him safely before 1970. 

It is U. S. policy to support the rule of law in space, and to use outer 

space for peaceful purposes. 

United Nations space treaty, first called for by President Johnson on 

May 7, that is intended to prevent the militarization of outer space and 

to insure peaceful exploration of the moon and other celestial bodies. 

The United States this year -supported a 

137 
LEADERSHIP IN SPACE 

U.S. accomplishments dominated the year in space -- completion of the GEMINI 

series, and successful lunar reconnaissance by SURVEYOR 1 and ORBITER 1 and 2 

were some of the achievements. The United States, which as recently as two years 

ago was on the defensive with respect to the Soviets, now commands a clear lead. In 

the eyes of world opinion, the United States was exhibiting a virtuosity and capability 

that the Soviets were not matching, and which evidenced leadership in space. 

TREATMENT 

Manned Flight 

Primary emphasis was given the GEMINI flights, plus SURVEYOR and LUNAR 

ORBITER, the lunar reconnaissance missions that support manned flight objectives. 

Each of the Agency's media branches gave full treatment to the five GEMINI flights of 

the year. 

Voice of America's short-wave broadcasts were the live relays and delayed retransmissions by local stations around the world -- providing a tremendous audience. 

The flight of GEMINI 9, for example, was carried by over 500 stations in 12 Latin 

American countries alone. 

USlA's wireless service averaged 13 stories per flight. Supporting the 

Voice of America's coverage of manned flight events is complex, as GEMINI 11 coverage demonstrates. World-Wide English Division gave comprehensive coverage from 

lift-off, through the in-flight experiments to splashdown. Live worldwide coverage 

was restricted to beginning and end of the-flight, but live specials on extra-vehicular 

activity were carried to areas on the air at the tirqe. Correspondents' reports from 

Houston were broadcast in regional programs, and "Dateline" included highlights of 

the various World-Wide English specials on appropriate days. 

Division carried live reports and wrap-ups in Spanish from Cape Kennedy, plus commentaries and current news in regular broadcasts. The Near East and South Asia 

Division reported the flight in all division language broadcasts -- with particularly 

full coverage in the longer Arabic airshows. The U. S. S. R. Branch covered much of 

the mission live in Russian, and with the Armenian and Ukrainian services caught the 

splashdown live via TV monitor. 

age drawing on reports from the newsroom, correspondents' reports from Houston 

and the Cape, and science features. 

Latin-American 

All other language elements gave appropriate coverForeign newsmen were informed in advance of the GEMINI flights through special 

packets prepared by the Agency's Press Service. 

NASA, they contained six or more special stories and as many as 10 photographs and 

drawings, and ware shipped to all posts by air at least three weeks before launch 

time. 

information on the designated tasks of each flight. 

Prepared in cooperation with 

This permitted foreign media to receive from USIA posts detailed pre-launch 

Also in the hands of posts was a GEMINI lecture with 58 slides, with supplements and 

extra slides. 

fore the first manned APOLLO flight. 

A new slide lecture on APOLLO was being prepared to be on hand beTelevision and movie audiences abroad were furnished informative and exciting shows 

about the U. S. space achievements. In Brazil, Argentina and Mexico the actual 

138 
GEMINI 5 spacecraft was exhibited to crowds totalling 2,139,000, many of whom 

stood four abreast for hours, in lines that stretched almost half a mile, to see the 

spacecraft. 

Manned flight was also the theme of a number of Agency pamphlets. 

Moon, 

118,000 copies printed in six languages. 

duced a fast pamphlet, "Steps to the Moon, It from materials furnished by the Press 

Service, printing 340,000 copies in six languages. 

of the American aerospace industry, "Wings USA, 

development accomplishment in aeronautics and space, and "Behind the Spacemen, It 

an account of the workers who make the astronauts possible, were designed and 

developed for the Agency free of charge by the Aerospace Industries Association, 

being printed in two languages for 46,000 copies. 

"Destination 

which tells the APOLLO story, was updated in a color production with 

The Regional Service Center in Manila proTwo pamphlets that tell the story 

which details research and 

SURVEYOR 1 

The successful soft-landing of SURVEY OR 1 and its long-lived picture transmission 

had great impact abroad. 

as Japan's Yomiuri Shimbun, which said the flight "demonstrates the advanced state 

of U. S. space technology and boosts American confidence in NASA's approach to the 

problem of putting men on the moon. 

SURVEYOR 1. 

USLA presented its accomplishments in much the same way 

-- 

USIA's wireless service carried 20 stories on 

SURVEYOR pictures serviced by the Agency brought the moon and U. S. space closer 

to millions. 

were distributed to 154 posts worldwide. 

hundreds of SURVEYOR photos was sent to 65 posts. 

were the peg for a four-panel paper exhibit, "Target Moon, 

went to 77 posts in English, French, Spanish and in blank copies for vernacular editions. 

A total of 6,580 prints of SURVEYOR 1 and its close-up photographs 

A special color view "reconstituted" from 

SURVEYOR'S accomplishments 

of which 4,845 copies 

LUNAR ORBITER 1 and 2 

The achievement of the LUNAR ORBITERS was presented as providing what RANGER 

and SURVEYOR could not: 

landing sites. Posts were serviced with 5,415 ORBITER pictures. LUNAR 

ORBITER 1 was also the subject of a 10-minute film for Latin American television, 

and of a segment of "Science Report, It a bimonthly newsreel for worldwide television. 

The wireless service sent 18 stories on the ORBITERS. 

Pictures of the large areas required for a landing to map 

U. S. Astronauts Abroad 

U. S. astronauts were again sent abroad by President Johnson, to share what the 

United States has learned from space. 

television audiences, students or scientists, chiefs of state or the man in the street, 

the astronauts were uniquely effective U. S. spokesmen. 

space exploration, supported by in-flight motion pictures, photographs from space, 

and an actual spacesuit, dramatically affirmed the success of American technology. 

Whether addressing press conferences or 

Their story of peaceful 

Our astronauts traveled to the capitals of Japan, Korea, Formosa, Bangkok, 

Malaysia, the Philippines, Australia, and New Zealand. In Japan they reached an 

139 
estimated audience of 46 million in six hours of television programming, and held 

lengthy sessions with space scientists. 

them to the capital. 

students, supervised by a Peace Corps science teacher, had used scavenged and 

donated materials to build TELETEK, a tracking station that had tracked a dozen 

U. S. space probes. 

In Seoul a quarter million Koreans welcomed 

In Kuala Lumpur they lectured at the Technical College, where 

In Latin America where our astronauts visited 13 cities, including 10 South American 

capitals, plus Panama City, in 24 days, the impact was even greater. They dominated both press and television in each city visited, and street crowds repeatedly 

swamped their motorcades. The astronauts talked to and mingled freely with the huge 

crowds, and left the impression that they had come to see the ordinary man, that they 

were men of the people who had come to talk to the people. 

with many chiefs of state. 

They also had audiences 

Press and Publications 

Space science is a recurring theme in Press Service output, intended to heighten 

world respect for U. S. technological competence. 

through the year were the ESSA weather satellites, the uprated SATURN, the GEMINI 

flights, ORBITING ASTRONOMICAL OBSERVATORY, NIMBUS 2, EXPLORER 32, 

SURVEYOR 1 and 2, PIONEER 7, ORBITING GEOPHYSICAL OBSERVATORY, 

MAPPING SATELLITE, LUNAR ORBITER 1 and 2, and an INTELSAT Communication 

Satellite. The wireJess file carried 143 stories on these projects, and another 73 on 

auxiliary space stories. 

formative story on the U. s. space effort. 

Principal space projects covered 

In fact, on very few days did the file not carry some inIn addition to the special GEMINI flight packets, 15 issues of the weekly column, 

"Science Today," were devoted to space science, and 10 of the biweekly column, 

"What's New in American Science and Technology, treated space science. The 

Features section also distributed 15 byliners by space program officials and scientists for publication. 

"Amerika Illustrated" carried four major illustrated articles on American space 

science and a 10-page picture spread for its Russian and Polish readers. "Topic, 

an illustrated monthly published in English and French for Africa, carried three 

major articles on space, while "A1 Hayat fi Amerika, an illustrated semimonthly 

aimed at the educated Arab world, averaged one article on space in each of its six 

is sues. 

USIA cartoonists treated space science in 15 strips of llItts A Fact, It and in eight 

strips of "True Tales. 

packets. 

The same artists produced drawings for the GEMINI flight 

In servicing special packets for the Features section, including the GEMINI flights, 

and special request from posts for exhibits, calendars, and magazines,. a total of 

497 black and white subjects and 216 in color were covered. 

pared, 76 posts ordered the 4-picture story "Monster Takes a Trip, 95 posts the 

15-picture story "Doorway to the Moon" and 39 others the same 8-picture story in 

color; 76 posts the 7-picture story "Make-Believe Maneuvers,I1and 90 posts the 8- 

picture story "Goddard's Bold Dream. 

Of picture stories pre140 
Two "paper shows" -- paper panels for exhibit use -- concerned space science. 

"U. S. Doorway to the Moon," a 5-panel on the Cape Kennedy moonport was ordered 

for a total of 4, 371 copies in four editions: English 1,799, French 829, Spanish 625, 

and 1,118 blank copies for printing in local languages. 

paper show was ordered for a total of 4,845 copies, with new orders still coming in. 

"Target Moon," a 4-panel 

Television 

The Agency prepared two films for worldwide television use on GEMINI flights, and 

two more to support astronaut trips abroad. In addition, "Science Report, It a bimonthly film report on American scientific developments distributed to 72 countries 

in more than three languages, carried reports on most of the GEMINI flights, and 

the missions of LUNAR ORBITER and SURVEYOR. 

Radio 

The Voice of America covered all aspects of space in the news as well as in reportage, 

commentaries, features and reports from correspondents at Cape Kennedy and Flight 

Control in Houston. 

delivered at Princeton University in May was broadcast in full in worldwide English 

and excerpted in various foreign languages. A VOA correspondent accompanied the 

astronaut tours to the Far East and Latin America. During the GEMINI 10 flight in 

July, a Press Service pamphlet, "Destination Moon, It was offered to the World-Wide 

English audience. Over 7,000 requests were received. 

President Johnson's address on the peaceful uses of space 

In addition to heavy news coverage, News and Current Affairs this year issued more 

than 16 commentaries, 140 correspondents' reports, and 90 features for use by 

World-Wide English and 37 foreign language services. 

Motion Pictures 

USIA produced a number of films on the GEMINI program, and distributed, worldwide 

in English, "First Reactor in Space," a 15-minute color film made by AEC, and 

worldwide in six languages, "Live Via Early Bird, It a 30-minute color film of the 

Communications Satellite Corporation. "Behind the Space Man, It a 30-minute color 

film demonstrating the persons and skills back of the astronauts, was in production. 

Exhibits 

Space exhibits featuring the actual GEMINI 5 spacecraft, full- and lesser-scale 

models of GEMINI 5, and 30 displays on the U. S. Space Exploration Program -- all 

of which in 1966 were made available to USIA by NASA -- plus older models and exhibits on space already in circulation among 500 USIA outlets around the world, 

attracted 5, 700,000 "clocked" viewers to supervised showings in 35 nations. 

The total estimated worldwide audience for approximately 19,000 printed exhibits on 

space themes in the hands of the USIA posts is conservatively placed at 19,000,000. 

This audience included not only general viewers but, more importantly, high government officials, leaders of the scientific and educational community, students, and 

representatives of other opinion-molding groups in more than 120 nations around the 

globe. 

141 
In Burma, a space exhibit of models and other components provided by USIA and 

NASA attracted 250,000 and -- according to reports from the U. S. Embassy in 

Rangoon -- did more to boost the standing of the United States with the Burmese 

people than any U. S. Government effort since the Burmese Government took office 

four years before. 

Information Centers 

U. S. Information Service posts furnish, in addition to the foregoing, a variety of 

space information to foreign nationals. 

lished and others are planned. 

in space science have circulated for showings in 18 countries in Europe, Latin 

America, and the Far East. 

GEMINI Mid-Program Conference, February 1966l' have been sent to post libraries. 

A number of books on space have been pubA collection of 145 books on American achievements 

Sixteen governmental publications on space such as 

142 
ARMS CONTROL AND 

DISARMAMENT AGENCY 

CHAPTER 

XIV 

INTRODUCTION 

Space and space activities continue to be important factors in the pursuit of United 

States arms control and disarmament objectives. 

The Arms Control and Disarmament Agency (ACDA) is concerned with preventing the 

proliferation of nuclear weapons and strategic delivery vehicles from nuclear to nonnuclear countries and also with achieving balanced arms control agreements which 

will slow down the arms race between existing nuclear nations. ACDA views the 

outer space treaty, which prohibits placing nuclear weapons and weapons of mass 

destruction in outer space, as a major step in slowing down the arms race between 

nuclear weapon powers by preventing space from becoming a future arena for arms 

deployment. 

Space can be a medium for promoting peaceful relations with other nations of the 

world through cooperative programs and can serve to divert resources from destabilizing armament programs by providing an arena for peaceful competition. Space 

also affords a medium which can be utilized for unintrusive verification of arms 

control agreements. 

ACDA's interest in space is reflected in international negotiations as well as its 

internal and external research programs. 

ARMS CONTROL PROGRAMS 

Preventing the &tension of the Arms Race to Space 

In 1963 the U. N. General Assembly unanimously adopted a resolution expressing the 

intention of all parties to refrain from stationing weapons of mass destruction in 

outer space. The "Outer Space" treaty would serve to extend, clarify, and codify 

this resolution. In his statement announcing this treaty the President said: "It is 

the most important arms control development since the limited Test Ban Treaty of 

1963. 

bodies or otherwise stationing in outer space, weapons of mass destruction. It also 

prohibits military fortifications or maneuvers on the moon and other celestial bodies 

with inspection rights to check compliance with the treaty. 

It prohibits the placing in orbit around the earth, stationing on celestial 

ACDAIs broad research program, including analyzing the applicability of certain 

principles of the Antarctic Treaty to outer space, has provided useful support in the 

negotiation of this treaty. The problem of verification and safeguards for such a 

treaty has been and continues to be the subject of extensive internal and external 

research activitfes. 

143 
Space Cooperation as an Aid to Arms Control 

Cooperative space programs tend to promote international understanding and greater 

awareness of common interests, thus creating an atmosphere of mutual trust in 

which negotiation of balanced arms control agreements becomes more probable. 

Cooperation in such areas as satellite communications, exchange of meteorological 

satellite data, space medicine data, and general scientific data all help to foster such 

a climate. 

ACDA has actively supported peaceful multinational space programs such as the 

European Launcher Development Organization. Programs of this type can assist 

in restraining the proliferation of rocket technology directly applicable to ballistic 

missiles at national levels. 

Use of SDace Vehicles for Inspection and Verification 

The Department of Defense VELA satellite program continues to be an important 

system in the monitoring of compliance with the limited nuclear test ban treaty. 

ACDA participates in this and other DOD Advanced Research Projects Agency 

developed programs aimed at increasing U. S. overall verification capabilities 

associated with this treaty and extending it to include all nuclear tests. 

Observation and inspection satellites are being carefully studied as potential contributor s to unintrusive inspection and verification systems for future arms control 

measures. 

collection from unmanned ground stations, photography, and other remote sensing. 

Studies are under way to develop sensors and data handling techniques for such arms 

control satellites. 

Satellites could perform such unintrusive inspection tasks as data 

Interaction of Arms Control Measures with Space Programs 

The U. S. proposed at the Eighteen-Nation Disarmament Conference that major 

powers explore the possibility of a freeze on strategic offensive and defensive 

nuclear weapon systems as a first step toward containing the arms race. 

Soviet reaction to date on this freeze proposal has been negative, studies carried 

out by the Agency have explored the interaction of various aspects of this proposal 

with the non-military space program. In cooperation with NASA, ACDA has studied 

the problem of restraining military missile development programs involving adequate 

verification without restricting peaceful space programs. 

Although 

144 
. c 

c 

Qo 

0 

I -I 

0 C cL> L 

145 

m 

v) 

0 0 0 0 0 d m N .- 

Appendix A- 1 
UNITED STATES LAUNCHING RECORD 

Earth Satellite Attempts Escape Payload Attempts 

Year Success Failure Success Failure 

1957 .................. 0 1 0 0 

1958 .................. 1959 .................. 1960 .................. 1961 .................. 1962 .................. 1963 .................. 1964 .................. 1965 .................. 1966 .................. Total .......... 

5 8 0 4 

9 9 1 2 

16 12 1 2 

35 12 0 2* 

54 12 4 1 

60 11 0 0 

69 8 4 0 

94 8 3 0 

95 12 5 l* 

4 37 93 18 12 

Notes : 

1. Information contained in this table is drawn from unclassified sources and is 

believed to be complete and accurate in keeping with the definitions given below. 

2. 

or sent to the Moon or into solar orbit. 

payload. 

are counted individually even though in a limited number of cases such separation 

failed to occur. 

the Earth to accomplish some specific research or application purpose and to return 

data to Earth. 

which carried only a radio beacon). 

but limited data return incidental to putting up a payload does not classify these as 

payloads in their own right. 

3. 

of attaining Earth orbit, or escape to the Moon or solar orbit as appropriate to the 

column indicated. 

much data as planned; other payloads failed to reach orbit or escape, yet returned 

useful data at least briefly. 

4. 

reference to multiple payloads) are the same as given above except in the Earth 

orbital category for 1959 (8 failures), 1960 (15 successes and 11 failures), 1961 (29 

successes), 1962 (48 successes and 6 failures), 1963 (38 successes and 8 failures), 

1964 (53 successes and 7 failures), 1965 (60 successes and 7 failures), 1966 (68 

successes and 4 failures), making totals of 325 orbi'tal launch successes, 18 escape 

launch successes, 72 orbital launch failures and 12 escape launch failures for a 

grand total of 424 launch attempts (3 escape failures were orbital successes). 

5. Data quoted include 2 U.S. payloads with British experiments, two Canadian 

payloads launched by the United States, one French payload launched by the United 

States, and one Italian payload launched by an Italian crew from U. S. territory. 

* These failed to go to escape as intended, but did attain Earth orbit and are in those 

totals. 

Numbers are given in terms of identified separate payloads placed in Earth orbit 

A few launchings have put up more than one 

If these payloads were intended to separate from each other in flight, they 

A payload is defined as an object put into orbit or sent away from 

Typically, a payload transmits telemetry, but not always (e. g. ECHO 

Some rocket casings may carry radio beacons, 

The sole criterion of success or failure used for the purpose of this table is that 

Some payloads reached orbit or escaped without returning as 

The corresponding data for number of launchings attempted (the count without 

NASC Staff 

Appendix A-2 

146 
SUCCESSFUL U. S. LAUNCHES -- 1966 

See explanatory notes c at end of table. 1 Apogee and 

Perigee 

Launch Date (in statute miles) 

Name Payload Data Period (minutes) Remarks 

Designation Inclination to 

Vehicle Equator (degrees) 

Jan. 19 Total weight: Not stated. 161 Decayed January 25, 1966. 

DEFENSE Objective: Development of space flight 86 

2A techniques and technology. 88.4 

Atlas Agena D Payload: Not stated. 93. EO** 

Jan. 19 Total weight: Not stated. 122 

DEFENSE Objective: Development of space flight 92 

2B techniques and technology. 87. 6 

Atlas Agena D Payload: Not stated. 93. EO** 

Jan. 20 Total weight: 32,546 lbs. (including 

APOLLO (A-004) 9,361 lbs. ballast) 

System Test 

Little Joe II 

Jan. 28 

DEFENSE 

5A 

scout 

Feb. 2 

DEFENSE 

7A 

Thor Agena D 

Feb. 3 

ESSA I 

8A 

Thor Delta 

Feb. 9 

REENTRY V 

Reentry Test 

scout 

Feb. 9 

DEFENSE 

9A 

Thor Agena D 

Orbit 

not 

Objective: Test launch launch escape ve- intended. 

hicle in abort during power-on tumbling; test 

canard subsystem for ability to reorient LES 

with aft heatshield forward. 

Payload: APOLLO launch escape vehicle, 

command module, boilerplate service module. 

Command module instrumented with 2 C-band 

transponders, 2 tape recorders, telemetry 

system, 2 cameras, 4 antennas. 

Total weight: 144 lbs. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: 305 lbs. 

Satellite system; obtain complete daily world 

coverage of weather systems. 

polygon, with 18" receiving antenna and 4 

22" transmitting whip antennas; contains 2 

wide-angle vidicon cameras; 2 tape recorders; 

2 spin-control systems (magnetic coil; small 

solid-propellant rockets); 2 infrared horizon 

sensors; transmitters; 63 nickel-cadmium 

storage batteries; 9,100 n-on-p solar cells. 

Objective: Initiate Tiros Operational 

Payload: 22" x 42" 18-sided hatbox-shaped 

753 

535 

105.9 

89.70 

252 

112 

90.4 

75.03 

520 

439 

100.3 

97.89** 

Total weight: 345 lbs. (including motor and Orbit 

135 lbs. of propellant). not 

density charring-ablator nosecap material; 

determine its thermal effectiveness to withstand high-speed reentry. 

Payload: Blunt-cone reentry spacecraft 

instrumented with thermocouples, springwire 

sensors, 2 telemetry transmitters, batteries, 

tape recorder; nosecap covered with lowdensity phenolic-nylon test material; 17" reentry rocket motor. 

Objective: Evaluate char integrity of low- intendad. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

316 

314 

94.8 

82.07 

Decayed January 23, 1966. 

Little Joe I1 performed well; planned 

pitch-up maneuver was executed and 

launch escape system provided abort in 

the power-on, tumbling region. Canard 

stabilized command module in proper 

attitude. LES jettisoned, command 

module parachuted to Earth safely. 

Still in orbit. 

Decayed February 27, 1966. 

As the first of the Tiros Operational 

Satellite (TOS) series, ESSA I initiated 

the world's first operational weather 

satellite system. Picture-taking on a 

global basis was initiated 2/5/66; each 

day, 13 orbits of TV data were read out 

and data used for operational and research purposes. Quality of TV data 

excellent. Still in orbit, still transmitting. 

Scout vehicle and payload instrumentation performance was good; flight 

trajectory normal. Reentry speed was 

near the planned 26,950 fps. 

Still in orbit. 

147 Appendix A-3 
Feb. 15 

DEFENSE 

12A 

Atlas Agena D 

Feb. 15 

DEFENSE 

12B 

Atlas Agena D 

Feb. 15 

DEFENSE 

12c 

Atlas Agena D 

Feb. 26 

APOLLO 

System Test 

Saturn IB 

SATURN 201 

Feb. 28 

ESSA I1 

16A 

ThrustAugmented 

Thor Delta 

Mar. 9 

DEFENSE 

18A 

Thor Agena D 

Mar. 16 

CATV VIII 

19A 

Atlas Agena D 

Mar. 16 

GEMINI VI11 

20A 

Titan I1 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: 11.000 lbs. (APOLLO spacecraft, including 300 lbs. of fuel). 

Test vehicle and spacecraft for 

structural integrity, compatibility, communications, separation; test APOLLO heatshield 

at 27.300 fps reentry speed; recover APOLLO 

spacecraft; check out ground facilities and 

equipment. 

Payload: Complete SATURN IB vehicle, including 80'2" x 21'5" s-IB 1st stage and 59'1" x 

21'9" S-IVB 2nd stage, and Instrument Unit; the 

APOLLO launch escape system, command module, service module, and adapter. 

Total weight: 290 lbs. 

Objective: Add Automatic Picture Transmission (APT) capability to Tiros Operational 

Gatellite system; provide daily coverage of 

local weather systems for weather stations 

around the world. 

polygon, with 18" receiving antenna and 4 

22" transmitting whip antennas; containing 2 

wide-angle APT vidicon camera systems, FM 

transmitters, 2 spin-control systems (magnetic coil; small solid-propellant rockets), 2 

infrared horizon sensors; 63 nickel-cadmium 

storage batteries; 9,100 n-on-p solar cells. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: 8, 351 lbs. 

for GEMINI VIIL 

adapter system, radar transponder, command 

control system, main engine, 2 secondary engines, attitude control system. 

Total weight: 8,351 lbs. (for GEMINI, including reentry and adapter modules). 

vehicle; perform extravehicular activity for 

1 orbit. 

Payload: 18'5" x 10' 2-module bell-shaped 

spacecraft, containing 2 astronauts, guidance 

and control equipment, rendezvous radar, 

cameras, 1 HF and 1 UHF transceiver, high 

and low frequency telemetry transmitters, 

tracking and recovery communications, fuel 

cell, environmental control system, recovery 

and reentry systems. 

Objective: 

Payload: 22" x 42" 18-sided hatbox-shaped 

Objective: 

Payload: 26' x 5' cylinder, containing 

Provide a rendezvous target for 

Objective: Rendezvous and dock with target 

154 

89 

96. 5 

88.8 

159 

73 

96.48 

88.1 

133 

92 

96. 5 

88. 6 

Orbit 

not 

intended. 

876 

839 

113.4 

101. oo** 

260 

112 

90.5 

75.02 

184 

177 

90.4 

28.88 

164 

99 

88.8 

28. 90 

Rendezvous 

orbit: 

184 

177 

90.4 

28.88 

Decayed February 22, 1966. 

Decayed February 16, 1966. 

Decayed February 22, 1966. 

First complete Saturn IB performed 

well; lor propulsion from 

service module caused the command 

module to reenter at 26,500 fps, some 

500 mph less than intended 18.500 mph, 

but within acceptable test limits; heatshield showed expected amount of charring. The Block I Apollo spacecraft 

performed well in its 1st test. 

craft landed in Atlantic 49 mi. ftom 

planned landing point, was picked up by 

U. S. S. Boxer. 

First operational weather satellite to 

offer cloud photos to local APT stations, 

sending immediate pictures to ground 

stations as it passes overhead. 

half of 2-satellite Tiros Operational 

Satellite (TOS) system which provided 

pictures ol Earth's entire 200-millionsq. -mi. area daily. ESSA U's pictures 

were "of superior quality." Still in 

orbit, still transmitting. 

SpaceSecond 

Decayed March 29, 1966. 

Still in orbit. 

GEMINI VIII achieved world's first 

docking in space, took place at 6:33 into 

flight. At 7 hrs. unexpected yaw and 

roll motion forced Astronauts Neil A. 

Armstrong and David R. Scott to undock, 

use their reentry control system to 

stabilize the GEMINI spacecraft, and 

reenter on revolution 7 of planned 44 

(10 hrs. 42 min. of planned 72 hrs. 50 

min.); landed in stipulated emergency 

area in Western Pacific, March 17, 

1966, were hoisted aboard U. S. S. 

Mason. The 2nd primary objective-- 

EVA for 1 orbit--was not achieved. 

Flight trouble had been caused by constant firing of short-circuited yaw 

148 
Mar. 18 

DEFENSE 

22A 

Atlas Agena D 

Mar. 18 

DEFENSE 

22B 

Atlas Agena D 

Mar. 25 

DEFENSE 

24A 

scout 

Mar. 30 

25A 

Atlas D 

W1-4 

Mar. 30 

OV1-5 

25B 

Atlas D 

Mar. 30 

DEFENSE 

26A 

Thor Altair 

Apr. 7 

DEFENSE 

29A 

Thor Age- D 

Apt. 7 

SURVEYOR 

30A 

Atlas-Centaur 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: 144 lbs. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: 193 lbs. 

Objective: Determination of zero G 

effects on photosynthetic organisms and 

amall vascular plants, and environmental 

effects on thermal control coatings. 

Payload Cylinder with hemispheric 

ends, 27 inches in diameter, 55 inches 

long. 

cell duckweed, with photocells to measure 

cell division; wafers and coatings for thermal experiment. 5000 solar cells for power 

of 22 watts. 

Carried chlorella algae and multiTotal weight: 252 lbs. 

Objective: Measurement of the optical 

radiation of Earth. background and space 

to provide a basis for surveillance techniques. 

Payload: Cylinder with hemiapheric ends, 

27 inches in diameter, 55 inches long. Carried 

5 optical sensors. 0.5 to 30 micron region, 3 

pointing at Earth, and 2 at horizon. 

veristat gravity gradient stabilization system. 

5000 solar cells for power of 22 watts. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: 1 730 lbs. 

Objective: Demonstrate capability of AtlasCentaur to place a SURVEYOR spacecraft on 

simulated lunar transfer trajectory using twoburn, indirect-ascent launch trajectory. 

Payload SURVEYOR mass model, ballasted 

to simulate SURVEYOR's retrorocket and solar 

panels and antennas; S-band transponder; operational-type separation system. 

Had a 

187 

91 

89.0 

101. oo** 

146 

85 

88.2 

100.90** 

Decayed March 24, 1966. 

Decayed March 23, 1966. 

699 Still in orbit. 

553 

105.3 

89.72 

62 7 

5 50 thermal control missions. Still in 

104.11 orbit. 

144.50** 

Completed its assigned biological and 

662 Stabilized succesmfdly and provided 

607 optical radiation information. Still in 

105.6 orbit. 

144.60 ** 

580 

392 

100.5 

98.61* 

187 

118 

89. 5 

75.07 

198 

109 

89.6 

30.77 

Apr. 8 Total weight: 3,900 lbs. (including 1,000 lbs. of 498 

ORBITING scientific instrumentation). 491 

ASTRONOMICAL Objective: Prove operational capability of 100.9 

OBSERVA- OAO system; stabilize and control so scientific 35.02 

TORY I data can be obtained. 

31A Payload: 10' x 7' octagonal cylinder, from 

Atlas Agena D which extend 6 solar paddles for total width of 

21'. Radio command system includes 2 VHF 

Still in orbit. 

Decayed April 26, 1966. 

Atlas-Centaur attained 100 -mi. parking 

orbit, but 2nd Centaur burn to inject 

SURVEYOR mass model from parking 

orbit into lunar transfer trajectory was 

unsuccessful. Centaur engines ignited 

but shut down within 8 sec. because 

hydrogen peroxide which operated 

propellant-feed boost pumps had leaked 

out. Improved RL-10 engines, flown 

1st time, operated successfully in 1st 

bum; modified guidance system and 

redesigned, balanced vent system performed satisfactorily; propellant control worked well in 25-min. coast. 

Reentered May 5. 1966. 

OAO I orbited and functioned normally 

for 36 hrs. ; on 4/10 battery failure 

ended communication with the satellite. 

No experiments had a chance to return 

data. Spacecraft did function and complex stabilization and control system 

was operating with intended accuracy. 

Still in orbit. 

149 
Apr. 9 

DEFENSE 

32A 

Atlas Agena D 

Apr. 22 

OV3- 1 

34A 

Scout FW4S 

May 14 

DEFENSE 

39A 

Atlas Agena D 

May 14 

DEFENSE 

39B 

Atlas Agena D 

May 15 

NIMBUS II 

40A 

Thor Agena B 

May 19 

DEFENSE 

41A 

scout 

May 23 

DEFENSE 

42A 

Thor Agena D 

wtennas and 2 pair. of command receivers; 

2 transmittera for wideband telemetry; 2 

transmitters for narrowband telemetry; 2 

radio tracking beacon transmitters; attitude 

control system; 4 experiment packages; 3 

nickel-cadmium batteries; 74,618 p-on-n 

solar cells. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: 152 lbs. 

Objective: Measurement of the angular 

distribution and energies of charged particles 

in the magnetosphere and upper ionosphere, 

with pitch angle of particles of primary 

interest. 

acroes and 29 inches high. 

plasma probe booms and 2 18-inch magnetometer booms. 

spectrometers. electrostatic analyzer. plasma 

probes. Geiger counter. 2 magnetometers, 

2-watt transmitter. 2560 n-on-p solar cells 

providing 30 watts of power, and nickelcadmium batteries. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Payload Right octagonal cylinder 29 inches 

Two 54-inch 

Carries proton and electron 

Total weight: 912 lbs. 

structure of the atmosphere; extend meteorological observations to regions of the electromagnetic spectrum not previously covered and 

simultaneously observe cloud cover; test basic 

technology for meteorological satelliter. 

Payload: 10'-tall structure, consisting of 

56"-diameter sensory ring forming the base, 

connected by a truss structure to smaller 

hexagonal- shaped package, and flanked by 2 

8' x 3' solar paddles covered with 10.500 n-on-p 

solar cells; containing 3 TV cameras, APT 

vidicon camera system. HRIR instrumentation, 

MRIR instrumentation; active 3-4s control 

system; 8 nickel-cadmium batteries; 3 transmitters; 2 receivers; tape recorders; temperature control system. 

Objective. Test instrumentation for studying 

Total weight: 144 lbs. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

23 

86 

89.6 

116. 90* 

3,557 

219 

151.7 

82.46 

222 

83 

89.4 

110. 4** 

344 

322 

109.94** 

7 32 

683 

108.1 

100.30** 

95.4 

Decayed April 26, 1966. 

Still in orbit. Performed successfully. 

Decayed May 21, 1966. 

Still in orbit. 

In good near-polar orbit, NIMBUS I1 

provided excellent data from all experiments, including weather photographs on a global scale. Achieved 

final test objective of 800-orbit continuous operation on 7/15/66. TV tape 

recorder froze 9/2/66, making picture 

storage impossible. Still in orbit, 

still transmitting. 

552 

5 34 

103.4 

90.00 

151 

104 

88.6 

66.02 

Still in orbit. 

Decayed June 9, 1966. 

150 
May 25 Total weight: 495 lbs. 

ATMOSPHERE Objective: Measure temperatures, compoEXPLORER XXXII sition, densities, and pressures in the upper 

44A 

Thor Delta FW-4.5 Payload: 35"-dia. hermetically sealed 

atmosphere on a global basis. 

sphere fitted with 2,064 solar cells, with a 

canted turnstile antenna projecting from the 

bottom and 2 18" electrostatic probes from 

the sides; sphere contains ion mass spectrometer, 2 neutral particle mass spectrometers, 

3 magnetron density gages, optical aspect sensors and switch detectors, 2 PCM telemetry 

systems, command receiver, tracking transmitter. tape recorder and timer clock, magnetic spin-axis orientation dipole, silver-zinc 

batteries. 

May 30 Total weight: 2,194 lbs. (weight at launch, 

SURVEYOR I 

45A 

Atlas Centaur Moon, 596 lbs. ) 

including 1,3777-1b. retromotor, propellants, 

etc. ; weight of SURVEYOR lander on the 

Objective: Demonstrate capability of launch 

vehicle, spacecraft, and ground equipment to 

fly a lunar-intercept trajectory, maneuver 

and communicate effectively, and softland the 

SURVEYOR spacecraft on the Moon. 

10'-high x 14' (around 3 extended 

landing gear) spacecraft, consisting of triangular aluminum frame to which are attached: 

a mast supporting rotatable planar array antenna and solar panel (with 3,960 solar cells); 

2 folding booms deploying conical omnidirectional antennas; thermal compartment housing 

2 transmitters, 2 receivers, silver-zinc 

battery; thermal compartment housing decoder 

and signal processing equipment; 2 altituderadar antennas; survey TV camera; retromotor 

with propellants and equipment; 3 vernier 

motors. 

Payload: 

Jun. 1 Total weight: 1,748 lbs. 

ATDA Objective: To provide a rendezvous target 

46A for GEMINI IX. 

Atlas D Payload: An ascent shroud target docking 

adapter, equipment section, reaction control 

system, battery. 

Jun. 3 Total weight: 8.268 lbs. (for GEMINI, inGEMINI IX cluding reentry and adapter modules). 

47A Objective: Conduct rendezvous and docking 

Titan II maneuvers; conduct extravehicular activities. 

2-module bell-shaped spacecraft, containing 2 

astronauts; guidance and control equipment, 

cameras, 1 HF and 1 UHF transceiver; rendezvous system computer; high and low frequency 

telemetry transmitters, tracking and recovery 

communications; 2 fuel cells; environmental 

control system; reentry and recovery systems. 

Payload: GEMINI, 18'5" x 10' (dia. at base) 

Jun. 3 Total weight: Not stated, 

DEFENSE Objective: Development of space flight 

48A techniques and technology. 

Atlas Agena D Payload: Not stated. 

1,688 

175 

116.0 

64.65 

Softlanded 

on Moon. 

177 

177 

90.3 

28.88 

169 

167 

89. 9 

28.80 

Rendezvous 

orbit: 

177 

177 

90.8 

28.88 

127 

89 

86.90 

88.4 

Higher apogee than planned (750 mi. ) 

cqused by excessive bum of Delta 

vehicle's 2nd stage. Programming 

adjustment of onboard sensors compensated for high orbit and the aeronomy satellite returned good data. 

Still in orbit, still transmitting. 

SURVEYOR I made softlanding on 

Moon (on 1 st U. S. attempt) on June 2. 

1966, landing in Oceanus Pmcellarum; 

transmitted 11,237 photos to Earth as 

well as engineering data indicating a 

lunar surface bearing strength of 5 psi. 

Survived lunar night, transmitted last 

photos July 14, 1966. 

Decayed June 11, 1966. 

GEMINI IXA began on June 1 with 

the launch of ATDA, substitute for 

the more complex Agena target vehicle; launch of GEMINI IXA was 

postponed until June 3 because of 

problems in the guidance system; on 

3rd revolution rendezvous was 

achieved as planned, but shroud on 

ATDA had not separated; docking was 

canceled, but 2 more rendezvous were 

made. 

day by Astronaut Eugene Cernan 

while Astronaut Thomas Stafford controlled the spacecraft. At 72 min. of 

EVA, Cernan's faceplate fogged as he 

attempted to don and operate Astronaut Maneuvering Unit, so EVA was 

terminated after 2 hrs. Reentry came 

June 6. 1966 after 72 hrs. 21 mi+ in 

orbit, landing 2 mi. from target in 

view of live TV carried by EARLY 

BlRD satellite. Spacecraft and astronauts were hoisted aboard U. S. S. 

EVA was conducted on 3rd 

Wasp. 

Decayed June 9, 1966. 

151 
Jun. 3 Total weight: Not stated. 

DEFENSE Objective: Development of space flight 

48B techniques and technology. 

Atlas Agena D Payload: Not stated. 

Jun. 7 Total weight: 1.. 135 lbs. 

ORBITING Objective: Demonstrate operation of 3-axis 

GEOPHYSICAL 

OBSERVATORY 111 lated geophysical measurements within 

stabilized spacecraft for 1 mo. ; make corre49A 

Atlas Agena B 

Jun. 7 

DEFENSE 

51A 

Atlas Agena D 

Ju~. 9 

SECOR VI 

51B 

Atlas Agena D 

Jun. 9 

ERS 16 

SIC 

Atlas Agena D 

Jun. 10 

OV3-4 

52A 

scout 

Jun. 16 

GGTS 1 

5 3A 

Titan IIIC 

magnetosphere and interplanetary space. 

lite; from the sides extend 2 rotatable solar 

panels (covered with 33,000 solar cells) and 

2 solar-oriented experiments, one of them 

with a 30' antenna; from the ends extend 2 

22' booms and 4 shorter booms, all supporting experiments; total of 21 experiments; 

attitude control system; 3 tracking beacon 

transmitters; 2 telemetry transmitters; 2 tape 

recordere; 2 nickel-cadmium batteries. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Payload: 67" x 32" x 31" box-shaped satelTotal weight: 46 lbs. 

Objective: To continue geodetic measurements to tie the Pacific Island chain to North 

America and to provide an equatorial net. 

Payload: Solid state transponder and 

telemetry transmitter in a rectangular package 

9 x 11 x 13 inches covered with solar cells. 

Total weight: 11 lbs. 

to test metal-to-metal adhesion of space propulsion materials. 

experiment actuators, including 4 with seat-andpappet valves and 1 cyclical metal-to-metal contactor with 8 materiel combinations. Telemetry 

transmitter and solar cells to supply 2.5 watts, 

plus battery of experiment functions. 

Objective: Test of cold-welding experiments 

Payload: Octohedron 9 inches one side with 5 

75 

75 

88.3 

87.00 

75,602 

169 

2,907.9 

30.90 

Decayed June 9, 1966. 

OGO III went into planned highly 

elliptical orbit; all 21 experiments 

returned good data; attitude control 

system exceeded primary objective 

of 1-mo. operation, operating more 

than 6 weeks, then going into spinstabilized mode. Still in orbit, still 

transmitting. 

2,206 Decayed December 3, 1966. 

115 

124.3 

90.04** 

2,248 Still in orbit. 

106 

124.9 

90.05*+ 

2,233 Still in orbit. Performed to supply 

110 useful data. 

124.7 

90.02** 

Total weight: 173 lbs. 2,933 

Objective: Measurement of the spectral and 398 

and depth dose of the inner Van Allen belt. 

across and 29 inches high, with 5 18-inch booms. 

142.2 

Payload: Right octagonal cylinder 29 inches 40.79 

Carries tissue equivalent ionization chambers, 

linear energy transfer spectrometer, electron 

and proton spectrometers, solid state charged 

particle spectrometer and tri-axial magnetometer, 2-watt transmitter, 2560 n-on-p solar 

cells, and nickel-cadmium batteries. 

Total weight: 104 lbs. 

Objective: Test of gravity gradient 

stabilization at high altitude, intended to 

achieve steady state pointing accuracy of 

- +Eo in pitch and roll within 60 days. 

Payload: Symmetrical polyhedron with 24 

faces, 32 inches high and 36 inches in diameter. 

Two %?-foot booms extended in gravity gradient 

test. Main body covered with 1824 n-on-p solar 

cells. 

sensors. Telemetry transmitter. 

Two Earth albedo sensors and 5 Sun 

21,004 

20,857 

1,333.8 

0.17 

Still in orbit. Performed as planned. 

Still in orbit. Performed as planned. 

152 
Jun. 16 

IDCSPl, 2, 3. 4, 

5. 6. .. and 7 

53B, C. D. E, 

F, GandH 

Titan LUC 

Jun. 21 

DEFENSE 

55A 

Thor Agena D 

Jun. 23 

PAGEOS I 

56A 

Thor Agena D 

Jul. 1 

AMP EXPLOR58A 

ER XXXW 

Total weight: 700 lbs. (100 lbs. each). 

defense communications satellite-mystem 

with the first 7 of 22 spacecraft. 

24 faces, 32 inches high and 36 inches in 

diameter. 

cell#, supplying 40 watts primary power. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Objective: Establishment of an interim 

Payload Symmetrical polyhedrons with 

Each covered with 8000 n-on-p solar 

Total weight: 247 lbs. (including PAGEOS, 

inflation powders, canister, and adapter; 

PAGEOS alone, 125 lbs. ) 

orbit to act as passive portion of worldwide 

geodesy system. 

sphere; inflation powders; canister; adapter. 

Total weight: 206 lbs. (including 81-lb. 4thstage motor). 

Objective: By means of lunar-anchored 

spacecraft, study magnetic tail and magObjective: Orbit 100' sphere into circular 

Payload: 100' (when inflated) Mylar 

~- 

Thrust-Augmented netohvdrodvnamic wake of Earth once a-month: 

Improved-Delta 

Jul. 5 

APOLLO 

59A 

Saturn IB 

SATURN 203 

Jul. 12 

DEFENSE 

62A 

Atlas Agena D 

Jul. 14 

ov1-8 

6 3A 

Atlas D 

Jul. 18 

CATV X 

65A 

Atlas Agena D 

(Orbital range:) Still in orbit. Successfully distributed 

21.004-21.295 

20,857-20.905 tivated. 

in planned orbits and payloads ac1,334.4-1.347.4 

0.04-0.40 

221 

121 

90.0 

80.09 

2,656 

2,602 

181.4 

87.05 

.. measure interplanetary magnetic fields, 

solar plasma, and energetic particles. 

Payload: 28" (dia. ) x 8" octagonal spacecraft, with 2 7' booms deploying flux-gate 269,964 

magnetometers; 3 radiation monitors; 9,858 

solar-wind analyzers; 4 solar paddles 

mounting 6,144 n-on-p solar cells; 13 

silver-cadmium batteries; transmitter. 

8,540.0 

28.69 

Total weight: 58,500 lbs. (includes S-IVB 

stage, instrument unit, and nose cone and 

19,000 lbs. of hydrogen). 

Objective: Evaluate S-IVB/IU stage in 

orbit, including behavior of liquid hydrogen 

in orbit. 

combination; liquid hydrogen and liquid 

oxygen fuel; 2 cameras; telemetry. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Payload: 92 ' -long S - IVB / IU / nos econe 

Total weight: 74 lbs. 

reflector more efficient in performance and 

less subject to solar wind can be developed 

for communications relay. 

orbit, which was to photolyze, leaving a fine 

wire grid. 

Objective: To test whether a passive 

Payload: 30-ft. diameter balloon, inflated in 

131 

113 

88.5 

31.98 

162 

93 

88. 7 

95.53** 

627 

61 9 

105.3 

144.20** 

Total weight: 7, 184 lbs. 216 

Objective: To provide rendezvous target 214 

for GEMINI X. 91. 5 

Payload: 26' x 5' cylinder, containing adapter 28.86 

system, radar transponder. command control 

system, main engine, 2 secondary engines, 

attitude control system. 

Decayed July 4, 1966. 

PAGEOS I went into orbit remarkably 

close to planned one (2,64612,636 

mi. ). Still in orbit. 

AMP EXPLORER XXXIII's intended 

lunar orbit was changed to alternative highly elliptical orbit when 

launch vehicle acquired excess speed. 

All experiments returned good data. 

Early results indicated tail of Earth's 

magnetosphere extended more than 

75,000 mi. beyond Moon's orbit. 

Still in orbit, still transmitting. 

Heavibst weight orbited by U. S. to 

date. S-IVB stage went into good 

orbit; simulated restart of engine was 

confirmed. Intended 3-day flight 

ended in 4th orbit, when deliberately 

induced internal over-pre ssure s 

ruptured bulkhead, fragmented payload. Fragments began reentering 

July 5, 1966. 

Decayed July 20, 1966. 

Experiment successful. Still in 

orbit. 

Decayed December 29, 1966. 

153 
Jul. 18 Total weight: 8,248 lbs. (for GEMINI, 

GEMINI X including reentry and adapter modules). 

66A Objective: Conduct rendezvous and 

Titan II docking maneuvers with GATV. 

Payload 18' x 10' (dia. at base) 2- 

module bell-shaped spacecraft. containing 

2 astronauts; guidance and control equipment; cameras; 1 HF and 1 UHF transceiver; 

rendezvous system; computer; high and low 

, frequency telemetry transmitters, tracking 

and recovery communications; 2 fuel cells; 

environmental control system; reentry and 

recovery system. 

After GATV 

boost 

GEMINI X achieved rendezvous and 

docking with its GATV; while docked, 

Michael Collins used the AGENA engine to maneuver the combination into 

proper orbit for rendezvous with 

GEMINI VLU GATV, undocked from 

its GATV and rendezvoused with 

passive GEMINI VIII GATV. Collins 

performed 2 periods of EVA. Standup 

EVA was terminated because of eve 

irritation and umbilical EVA 

because of spacecraft fuellhortage. 

Reentry occurred on 44th revolution 

after 70 hrs. 47 min. of flight on 

July 21, 1966. Astronauts were 

picked up by helicopter, flown to 

U. S. S. Guadalcanal. 

468 Astronauts John W. Young and 

185 

95.2 

28.80 

Jul. 28 Total weight: Not stated. 146 Decayed August 6, 1966. 

69A techniques and technology. 88. 3 

Titan IIJB Agena D Payload: Not stated. 94.14** 

DEFENSE Objective: Development of space flight 94 

Aug. 4 Total weight: 165 lbs. 2,781 

OV3-3 Objective: Measurement of the charged 223 

70A particle hazards to space payloads. 136.9 

scout Payload: Hexagonal cylinder containing: 81.47 

Triaxial fluxgate magnetometer to measure 

magnetic aspect in correlation with directional 

particle data. 

power density of electrostatic plasma waves; magnetic fluctuation experiment; omnidirectional proton and electron spectrometers; high and low 

energy hydrogen-helium nuclei telescopes; 

Faraday cup and electron and proton spectrometers; medium energy electron spectrometer; induction coil to measure magnetic field; electron 

field antenna. 

VLF experiment for spectral 

Solar cells and telemetry system. 

Aug. 9 Total weight: Not stated. 

DEFENSE Objective: Development of space flight 

72A techniques and technology. 

Thor Agena D Payload: Not stated. 

Aug. 10 Total weight 853 lbs. 

LUNAR ORBITER I Objective: Place 3-axis-stabilized LUNAR 

7 3A 

Atlas-Agena D 

ORBITER spacecraft in lunar orbit; obtain 

high-resolution photos of various types of 

lunar terrain related to APOLLO and 

SURVEYOR. 

Payload: 5'6" x 5' (dia. ) (when deployed, 

18'6" along the antenna booms and 12' across 

solar panels) conical spacecraft. with body 

containing attitude control system, retromotor, S-band transmitter, dual-lens (24" and 

3" focal length) camera system, 2 radiation 

dosimeters; high and low gain antennas. 

Aug. 16 

DEFENSE 

74A 

Atlas Agena D 

Aug. 16 

DEFENSE 

74B 

Atlas Agena D 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload- Not stated. 

176 

118 

100.10** 

89.2 

- /Lunar 

orbital 

data1 

1.152 

119 

218 

12.2 

205 

89 

89.2 

93.20** 

325 

316 

94.9 

93.16** 

Still in orbit. 

the desired data. 

Successful in returning 

Decayed September 11, 1966. 

LUNAR ORBITER I on August 14 

became 1st U. S. probe to achieve 

lunar orbit; on August 21 perilune 

was reduced to 36 mi., on August 25 

to 30 mi. ; photographed all 9 primary 

APOLLO landing sites, including the 

one containing SURVEYOR I, and 7 

other APOLLO sites. and 11 areas 

on back side of the Moon. Total of 

207 frames (sets) of photos were 

taken and relayed back to Ear&, a 

malfunction caused image smear in 

high-resolution camera. On October 

29, 1966 LUNAR ORBITER I was 

crashed into the Moon's far side to 

make way for next launch. 

Decayed August 24, 1966. 

Still in orbit. 

154 
Aug. 17 Total weight: 140 lbs. 

PIONEER VII Objective: Obtain scientific data on mag75A netic field, solar plasma. cosmic ray, and 

Thrust-Augmented electron density at points farther from the Sun 

Improved Delta 

Aug. 18 

DEFENSE 

76A 

scout 

Aug. 19 

DEFENSE 

7 7A 

Atlas AgeM D 

Aug. 19 

SECOR VII 

77B 

Atlas Ageria D 

Aug. 19 

ERS-15 

77c 

Atlas Agena D 

Aug. 25 

APOLLOSystem Test 

Saturn IB 

SATURN 202 

Sep. 12 

GATV 

80A 

Atlas Agena D 

Sep. 12 

GEMINI XI 

81A 

Titan II 

than from ~rti for- a period of at least 3 moa. 

spacecraft, with a boom protruding from the 

top containing communications antennas; the 

sides covered with solar cells except for a 

narrow band in which are located the experiments and 3 booms, 2 for orientation jets and 

1 for the magnetometer; data storage; transmitter; batteries; total of 6 experiments. 

Total weight: 144 lbs. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Payload: 37" (dia. ) x 35" cylindrical 

Total weight: 46 lbs. 

ment program. 

inches covered by solar cells, and 8 antennas 

extended from sides, 1 from top. Contains 

solid state transponder, plus telemetry 

system. 

Total weight: 11 lbs. 

techniques and technology. 

faced with solar cells. and 1 dipole antenna, 

Total weight: 56, 900 lbs. (includes S-IVB 

stage. instrument unit, and APOLLO modules 

and launch escape system). 

Objective: Evaluate command module heatshield at high heating load; test vehicle/ 

spacecraft for structural integrity, separation, 

and general functioning. 

144' -long S-IVB f IUfAPOLLO 

adapter-command module-service escape 

system combination; cameras; telemetry; 3 

fuel cells; guidance and control system. 

Objective: To continue geodetic measurePayload: Rectangular package 9x1 1x1 3 

Objective: Development of space flight 

Payload: Octahedron 9 inches on a side 

Payload: 

Total weight: 7,199 lbs. 

Objective: 

for GEMINI XI. 

Payload: 26' x 5' cylinder, containing 

adapter system, radar transponder, command 

control system, main engine, 2 secondary 

engines, attitude control system. 

Total weight: 8,509 lbs. for GEMINI, including reentry and adapter modules. 

maneuver with GATV XI during 1st revolution. 

bell-shaped spacecraft, containing 2 astronauts; guidance and control equipment; 

cameras; 1 HF and 1 UHF transceiver; rendezvous system; computer; high and low frequency telemetry transmitters, tracking and 

recovery communications; 2 fuel cells; environmental control system; reentry and recovery system. 

To provide a rendezvous target 

Objective: Conduct rendezvous and docking 

Payload: 18'5" x 10' (dia. at base) 2-module 

1.125 au* 

1.010 au 

402.95 days 

.0946 

689 

649 

106.8 

88.85 

2,294 

2,283 

167.6 

90.13** 

2.295 

2,282 

167.6 

90.02** 

2,294 

2,275 

167.4 

90.11** 

Orbit 

not 

intended. 

185 

174 

90.5 

28.83** 

After GATV 

boost: 

851 

180. 

107.0 

28.83 

PIONEER VII went into planned orbit 

qutside that of Earth and away from 

the Sun. All experiments returned 

data. On September 25, 1966 

PIONEER VII appeared to have detected the tail of the Earth's magnetosphere at 3.25 million mi. from Earth 

as Earth passed between the Sun and 

the probe. Still in orbit, still transmitting. 

Still in orbit. 

Still in orbit. 

Still in orbit. 

Still in orbit. 

Successful suborbital flight was 3rd 

flight for Uprated SATURN 1. 2nd for 

operqtional APOLLO command module. After separation from s-IVB 

2nd stage, service module engine 

boosted spacecraft to 706-mi. altitude, 

then restqrted 3 more times on way 

down, accelerating command module 

to reentry speed of 19,900 mph and 

maximum heat of 2, 700°; splashdown 

occurred in Pacific some 500 mi. SE 

of Wake Island; pickup was by U. S.S. 

Hornet. 

Decayed December 30, 1966. 

GEMINI XI spacecraft rendezvoused 

with GATV XI and then docked with it 

1 hr. 34 min. into the flight. Astronauts Charles Conrad and Richard F. 

Gordon each docked twice. While still 

docked, they used the GATV propulsion to maneuver to an 8511180 orbit, 

then to lower orbit again. After separation a tether exercise was conducted, 

followed by another rendezvous EVA 

was performed twice, but the umbilical one was curtailed when Astronaut 

Gordon became excessively fatigued. 

Automatic reentry was normal; 

155 
Sep. 15 

DEFENSE 

82A 

Thor Burner II 

Sep. 16 

DEFENSE 

8 3A 

Atlas Agena D 

Sep. 16 

DEFENSE 

8 3B 

Atlas Agena D 

Sep. 20 

SURVEY OR II 

84A 

Atlas Centaur 

Sep. 20 

DEFENSE 

05A 

Thor Agena D 

Sep. 28 

DEFENSE 

06A 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: 2, 194 lbs. (weight at launch, 

including 1, 377-1b. retromotor, propefiants, 

etc. ; weight of SURVEYOR lander on the 

Moon, 596 lbs. ) 

vehicle, spacecraft, and ground equipment to 

fly a lunar-intercept trajectory, maneuver 

and communicate effectively, and softland the 

Surveyor spacecraft on the Moon. 

Payload: lO'-high x 14' (around 3 extended 

landing gear) spacecraft, consisting of triangular aluminum frame to which are attached: a mast supporting rotatable planar 

array antenna and solar panel (with 3,960 

solar cells); 2- folding booms deploying conical 

omnidirectional antennas; thermal compartment housing 2 transmitters, 2 receivers, 

silver-Einc battery; thermal compartment 

housing decoder and signal processing equipment; 2 altitude-radar antennas; survey TV 

camera; retromotor with propellants and 

equipment; 3 vernier motors. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Objective: Demonstrate capability of launch 

Total weight: Not stated. 

~ .. Objective: Development of space flight 

Titan IIIB Agena D techniques and technology. 

Payload: Not stated. 

Oct. 2 Total weight: 325 lbs. 

ESSA III Objective: Orbit TOS satellite carrying 2 

87A Advanced Vidicon Camera Systems (AVCS) 

Thrust Augmented to maintain satellite weather system capaDelta 

Oct. 5 

DEFENSE 

89A 

Atlas Agena D 

bility of providing worldwide cloud-cover 

photos once a day for operational use by ESSA. 

Payload 22" x 42" 18-sided hatbox-shaped 

polygon, with 18" receiving antenna and 4 22" 

transmitting whip antennas; containing 2 AVCS, 

FM transmitters, 2 spin-control systems 

(magnetic coil; small solid-propellant 

rockets), 2 infrared horizon sensors; 8 solar 

and terrestrial radiation sensors; 63 nickelcadmium batteries; 9,100 n-on-p solar cells. 

559 

432 

100.8 

98.50** 

203 

91 

89.2 

93.90** 

306 

2 90 

94.2 

92.02** 

Impacted 

the 

Moon. 

2 54 

111 

90.4 

85.05 

178 

91 

80.8 

93.97** 

923. 

861 

114.6 

101.02** 

Total weight: Not stated. 2,298 

Objective: Development of space flight 2.280 

techniques and technology. 167.6 

Payload: Not stated. 90.24** 

splashdown came on 45th revolution 

within 2 mi. of predicted impact 

point, on September 15, 1966. The 

flight had lasted 71 hrs. 17 min. 

Astronauts .were picked up by helicopter and flown to U. S. S. e. 

Still in orbit. 

Decayed September 23, 1966. 

Still in orbit. 

SURVEYOR II was launched into nearperfect lunar-transfer trajectory by 

Atlas Centaur; at midcourse maneuver, 

failure of 1 of 3 vernier engines to 

ignite caused spacecraft to tumble; 

39 other attempts were made to start 

balky engine, without success. Since 

softlanding was impossible, many engineering checks were made,.then on 

September 22, 1966 the retzomotor 

was fired; all communication was lost 

30 sec. later; SURVEYOR 11 craehed 

on Moon SE of crater Copernicus. 

Decayed October 12, 1966. 

Decayed October 7. 1966. 

ESSA III was put into near-polar 

orbit by 1st Delta vehicle launched 

from WTR. All systems functioned 

normally and photos were of excellent quality. Still in orbit, still 

transmitting. 

Still in orbit. 

156 
Oct. 5 

SECOR VIII 

89B 

Atlas Agena D 

Oct. 12 

DEFENSE 

90A 

Atlas Agena D 

Oct. 12 

DEFENSE 

90B 

Atlas Agena D 

Oct. 26 

SURVEYOR 95A 

Atlas Centaur 

Oct. 27 

INTELSAT IIA 

96A 

Total weight: 46 lbs. 

ment program 

inches, covered with solar cells. High 

altitude transponder, storage batteries, 

telemetry system, power regulator. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: 1,627 lbs. 

Objective: Demonstrate capability of 

Centaur vehicle to perform a two-burn, indirect ascent mission. 

Payload: SURVEYOR mass model, 

ballasted to simulate SURVEYOR'S retrorocket and solar panels and antennas; S-band 

transponder assembly; operational-type 

separation system. 

Total weight: 357 lbs. (with apogee motor; 

192 lbs. in orbit). 

Objective: To continue geodetic measurePayload: Rectangular packdge 12xl4xJO 

Obiective: Place satellite and auogee motor 

2,299 

2.282 

167.6 

90.20** 

131 

95 

88.6 

90.95** 

103 

103 

88.9 

90.88** 

Completed 

geocentric 

part of 

orbit. 

23,342 

185 

-I 

669.6 

Thrust Augmented into proper transfer orbit, provide tracking and 26.41 

Improved Delta 

Oct. 28 

OV3-2 

97A 

scout 

Nov. 2 

DEFENSE 

98A 

Atlas Agena 

Nov. 2 

DEFENSE 

98B 

Atlas Agena 

Nov. 3 

OV4-3 

99A 

Titan IIIC 

telemetry, and backup calculations through 

the transfer orbit so the satellite can be injected into synchronous orbit. 

satellite, with apogee motor and whip anAfter apogee 

motor firing: 

Payload: 56" (dia.) x 26 1/2" circular 23,330 

2,072 ~~ 

tennas beneath and sleeve rising above and 

covering the antennas; 2 frequency translation 

mode repeaters; 4 traveling wave tube amplifiers; control system; 2 batteries, 12.756 

n-on-p solar cells. 

Total weight: 201 lbs. 

Objective: Measurement of the charged 

particle environment near Earth. 

Payload: Electrostatic analyzer; ion mass 

spectrometer; plasma probe; retarding potential analyzer; standing wave impedance probe; 

2 aspect sensors (a magnetometer and a solar 

sensor); transmitter and power supply. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: 21, 300 lbs. 

to provide data on the aerodynamics of its long 

shape during launch and exit from the atmosphere. 

Payload: A modified Titan II oxidizer tank 34 

feet long by 10 feet in diameter, including: a 

hydrogen-oxygen fuel cell generating 200 watts; 

a biocell experiment to test cell growth under 

weightless conditions; 18 corner reflectors experiment of laser optical measurements; 2 micrometeoroid detectors; heat transfer experiment 

Objective: To carry various experiments, and 

728.0 

17.6 

991 

198 

104.2 

81.99 

181 

100 

89.0 

90- 95 

161 

114 

88.8 

90.60** 

184 

183 

90.4 

32.85 

Still in orbit. 

Decayed October 20, 1966. 

Decayed October 21, 1966. 

Atlas Centaur attained 100-mi. parking orbit; Centaur liquid hydrogen 

engines reignited and burned full 

thrust to send SURVEYOR mass model 

on simdated lunar transfer trajeo 

tory. Reentered November 6, 1966. 

Eighth and last Centaur development 

flight. 

Delta launch vehicle put INTELSAT 

II-A in even better transfer orbit 

than hoped for; test signals were excellent; on October 30, 1966 apogee 

motor was fired in attempt to put the 

satellite into synchronous orbit but 

engine did not perform. Satellite 

remained in elliptical orbit, transmitted occasional commercial 

messages. Still in orbit, still transmitting. 

Still in orbit. Successful in returning 

the desired data. 

Decayed November 15, 1966. 

Decayed November 16, 1966. 

.r 

Still in orbit. 

157 
Nov. 3 

OV4-1R 

99B 

Titan IIIC 

Nov. 3 

OV1-6 

99c 

Titan IIIC 

Nov. 3 

OV4-1T 

99D 

Titan IIIC 

Nov. 3 

GEMINI 

Vehicle Test 

Titan IIIC 

Nov. 6 

LUNAR 

ORBITER II 

lOOA 

Atlas Agena D 

Nov. 8 

DEFENSE 

102A 

Thor Agena D 

Nov. 11 

CATV XII 

103A 

Atlas Agena D 

Nov. 11 

GEMINI XII 

104A 

Titan II 

with potassium fluid, 35-foot ionospheric 

sounding antenna. 

Total weight: 300 lbs. 

messages can be transmitted at low power 

through ionosphere ducts of the F layer. 

to measure cosmic noise and electron and air 

density-. 

Cylinder with one end dorhed, 55 

inches long and 17 inches in diameter. 

plus telemetry system to relay OV4-1T data. 

Silver oxide-zinc batteries. 

Total weight: 445 lbs. 

techniques and technology. 

with solar cells at each end, 27 inches in 

diameter, 68 inches long. 

Total weight: 240 lbs. 

Objective: To test whether intersatellite 

Also, 

Payload: 

Receiver, 

Objective: Development of space flight 

Payload: Cylinder with hemispheres covered 

Objective: Same as OV4-1R above. 

Payload: Cylinder with one end domed, 55 

inches long and 17 inches in diameter; transmitter on 20, 34, and 46 mc, silver oxide-zinc 

batteries. 

Total weight: Not stated. 

in actual suborbital flight launched from a vehicle on its way to orbit with other satellites. 

accommodate a 2-foot diameter hatch through 

the heat shield. 

Total weight: 850 Ibs. 

ORBITER spacecraft in lunar orbit; obtain 

high-resolution photos of various types of 

lunar terrain relating to APOLLO and 

SURVEY OR. 

Payload: 5'6" x 5' (dia. ) (when deployed 

18'6" along the antenna booms and 12' across 

solar panels) conical spacecraft, with body 

containing attitude control system, retromotor, S-band transmitter, dual-lens (24" 

and 3" focal length) camera system, 2 radiation 

dosimeters; high and low gain antennas. 

Objective: To test a reentry at orbital speed 

Payload: A used GEMINI capsule modified to 

Objective: Place 3-axis-stabilized LUNAR 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

Total weight: 7,000 lbs. 

for GEMINI XII. 

adapter system, radar transponder, command 

control system, main engine, 2 secondary 

engines, attitude control system. 

Total weight: 8,297 lbs. for GEMINI, including reentry and adapter modules. 

Objective: Conduct rendezvous and docking 

maneuver with CATV XII during 3rd revolution. 

Payload: 18'5" x 10' (dia. at base) 2-module 

bell-shaped spacecraft, containing 2 astronauts; 

guidance and control equipment; cameras; 1 HF 

and 1 UHF transceiver; rendezvous system; computer; high and low frequency telemetry 

Objective: 

Payload: 26' x 5' cylinder, containing 

To provide a rendezvous target 

182 

180 

90. 3 

32.83 

180 

179 

90. 3 

32.83 

197 

179 

90.6 

32.84 

Not 

applicable. 

Dunar 

orbital 

dag, 

1,162.6 

121.8 

218 

12.2 

193 

107 

100. oo** 

177 

156 

89. 3 

90.0, 

28.85 

179 

158 

89. 9 

28.84 

Still in orbit. 

Decayed on December 31, 1966. 

Still in orbit. 

Driven downward at 17,500 mph and 

and reentered near Ascension Island 

where recovered only 6 to 7 miles 

from intended landing point. 

LUNAR ORBITER 11 on November 10 

deboosted and went into lunar orbit; 

on November 15 another retromotor 

firing dropped the perilune to 31.4 

mi., then to 25.8. Some 211 high 

and medium resolution photos of the 

lunar surface were taken, including 

13 primary APOLLO sites and 17 

secondary. Readout of photos proceeded until December 6, when failure 

of high-power transmitter terminated 

readout; several photos of 1st APOLLO 

site photographed were lost. Engineering and selenodesy data continued to be transmitted. Still in 

orbit, still transmitting. 

Decayed November 29, 1966. 

Decayed December 23, 1966. 

GEMINI XII rendezvoused and docked 

with CATV XII in 3rd orbit as planned, 

but trouble in the CATV prevented 

Astronauts James A. Lovell, Jr., and 

=win E. Aldrin, Jr., from using the 

CATV propulsion system for further 

maneuvers. Aldrin had 3 EVA 

periods, 2 standup and 1 umbilical, 

for total of 5 hrs. 58 min. On 

158 
transmitters, tracking and recovery communications; 2 fuel cells; environmental control system; reentry and recovery systems. 

Dec. 5 Total weight: Not stated. 

DEFENSE Objective: Development of space flight 

109A techniques and technology. 

Atlas Agena D Payload: Not stated. 

Dec. 11 

OV1-9 

lllA 

Atlas D 

Dec. 11 

ov1-10 

lllB 

Atlas D 

Dec, 6 Total weight: 1,550 lbs. (including 76-lb. 

ATS I 

llOA 

Atlas Agena D motor firing). 

apogee motor system and 768 lbs. of apogeemotor propellant; 775 lbs. after apogeeObjective: Place into synchronous orbit and 

on station the spin-stabilized spacecraft; operate spacecraft for minimum of 30 days; obtain 

useful data from a number of the application, 

technology, and scientific experiments. 

Payload: 58 (dia.) x 53" cylinder, surfaced with 22,000 n-on-p solar cells; from 

the bottom end protrude 8 VHF antennas and 

apogee motor; from the top end protrude 8 whip 

antennas for telemetry and the microwave antenna; within the spacecraft are the guidance 

and control system; 2 VHF traveling-wave-tube 

transponders; 4 telemetry transmitters; 3 applications, 5 technology, and 6 scientific experiments; 6 nickel-cadmium batteries. 

Total weight: About 300 lbs. 

Objective: Study of radiation hazards of 

space flight. 

Payload: 

end covered with solar cells, 27 inches in 

diameter and 55 inches long. Experiment on 

altitude determination and spin rate. 

experiments on cosmic radiation and biohazards. 

employing tis sue - equivalents. 

Cylinder with hemisphere at each 

Three 

Total weight: About 300 lbs. 

around the Earth. 

end covered with solar cells, 27 inches in 

diameter and 55 inches long. Eight experiments on Lyman-alpha, dayglow, nightglow, 

solar X-ray, cosmic radiation, magnetic 

fields, and thermal coatings, plus a vertistat 

system of 6 controllable stabilizing booms. 

Objective: Study of space environment 

Payload: Cylinder with hemisphere at each 

Dec. 14 Total weight: Not stated. 

DEFENSE Objective: Development of space flight 

113A techniques and technology. 

Titan IIIB Agena Payload: Not stated. 

Dec. 14 Total weight: 936. 5 lbs. (includes 275-1b. exBIOSATELLITE I periment capsule). 

114A Objective: Inveatigate effects of weightlessThrust-Augmented ness and controlled gamma radiation plus 

Improved Delta weightlessness on living organisms aboard an 

attitude-controlled spacecraft with less than 

10-4g effect for 3 days; maintain onboard environmental control to keep the organisms alive 

and expose radiation sources for the flight 

duration; recover the spacecraft. 

Payload: 6' x 56" (dia. at base) cylindercone adapter section, covered with thermal 

insulating material, and containing attitude 

control system (nitrogen jets, IR sensors, 

226 

86 

89. 7 

104.63** 

22,870 

22,228 

1,466.0 

0. 23 

2,290 

295 

142. 

99. 

November 12, 1966 GEMINI XII rendezvoused with total solar eclipse and 

photographed it. Reentry occurred 

in 59th revolution on November 15, 

1966; splashdown was in the Atlantic, 

4 mi. from aiming point, after 94 hrs. 

34 min. 31 sec. of flight. Astronauts 

were picked up by helicopter and 

landed on U. S. S. Wasp. 

Decayed December 14, 1966. 

ATS I was launched into elliptical 

orbit; on December 7, 1966 the apogee 

motor was fired, circularizing orbit 

at synchronous altitude; all experiments performed well; by December 13 

the Applications Technology Satellite 

had photographed a 1-day weather 

pattern over one spot on Earth, relayed color TV from one U. s. coast 

to the other; relayed earth-to-spaceto airliner conversation using existing 

VHF equipment in airliner. 

orbit, still transmitting. 

Still in 

Still in orbit. Experiments performed 

as expected. 

2 

14** 

477 

597 

98.8 

93.79 

228 

86 

89.5 

109.50** 

192 

184 

90. 5 

33.50 

Still in orbit. Experiments performed 

as expected. 

Decayed December 24, 1966. 

Onboard systems and experiments 

performed normally, but spacecraft 

was not recovered. 

tiate retrofire and reentry was sent 

on December 17, 1966 but retrofire 

did not occur. 

Command to iniStill in orbit. 

159 
Dec. 21 

PRIME XV-5D 

Vehicle Test 

Atlas SLV-3 

Dec. 29 

DEFENSE 

118A 

Thor Agena D 

magnetometer), telemetry (transmitter, 2 

receivers, decoders, tape recorder, tracking beacon), silver-zinc batteries and power 

controller; antenna; 40" (dia. at base) reentry 

vehicle, containing experiment capsule with 

13 biological experiments, Strontium 85 

radiation source and dosimeter; life support 

system; separation and entry systems; deorbit telemetry transmitter; programmer, 

tracking beacon, tape recorder; recovery 

system. 

Total weight: Under 900 lbs. Orbit 

Objective: Development of maneuverable, not 

lifting body spacecraft technology. intended. 

Payload: A wedge-shaped body with flat 

bottom, rounded nose and top, with 2 short 

vertical tailfins. 

Total weight: Not stated. 

Objective: Development of space flight 

techniques and technology. 

Payload: Not stated. 

329 

300 

94.4 

75.02 

Flew close to the planned path, and 

reached the intended recovery area. 

Telemetry returned, but recovery of 

the craft not achieved. 

Still in orbit. 

NOTES: Successful launches are judged solely by the criterion of whether orbit of Earth or escape from Earth was achieved 

when so intended. Additionally, the table includes listings of important probes and vehicle tests not intended to orbit, but in 

these cases, no criterion of success has been applied; some achieved their purposes, others did not. 

orbital launchings with eight payloads not in this table failed to achieve orbit. 

Seven additional EarthLaunch date is based on Greenwich mean time. 

Name is the payload identification. 

Designation is the international COSPAR astronautical number of orbital objects. 

- 

Vehicle is the launch craft type. 

Total weight refers to the orbital weight of the object containing the payload; it does not include the weight of any separate 

miscellaneous burned-out rocket casings, protective coverings, etc. 

Objective and Payload are self-explanatory. 

Orbital elements are those filed with the United Nation8 a8 available; otherwise they are taken from the NASA Goddard 

Satellite Situation Report or other official public releases. 

Apogee and Perigee refer to the greatest and least distances respectively from the Earth of geocentric orbiting objects. 

In the case of data marked with an asterisk(*), the data refer to Aphelion and Perihelion, the farthest and closest distance between objects in heliocentric orbit and the Sun. 

nomical units. 

These latter instead of being measured in statute miles are measured in astro- 

(The mean distance between Earth and Sun is called 1 au. ) 

Period refers to the time in minutes (unless otherwise marked) required to complete one Earth orbit. (In the case of heliocentric orbits the period is measured in days. ) 

Inclination refers to the tilt of Earth orbits in relation to the Equator, measured in degrees of latitude at the points of the 

orbit farthest away from the Equator. 

of retrograde flight, i. e., somewhat westerly instead of the normal easterly. 

is measured in degrees of tilt to the Ecliptic (the plane of the Earth's orbit in relation to the Sun.) 

Inclinations in excess of 90 degrees carry double asterisks (**), indicating some amount 

In the case of heliocentric flights, the inclination 

Remarks are self-explanatory. 

Appendix A- 3 NASC Staff 

160 
UNITED STATES SPACE LAUNCH VEHICLES 

Thrust (in Max. Height less Payload (pounds) 

Thousands Dia. Spacecraft 300 NM First - 

Vehicle Stages Propellant of pounds) (feet) (feet) orbit Escape Launch 

scout 1. Algol (IIB) Solid 88 3.3 72 320 50 1965 (60)* 

Thor Delta 

2. Castor 11 

3. Antares I1 

4. Altair 111 

Solid 

Solid 

Solid 

1. Thor (DSV-3E-1) LOX/RP 

2. Delta (DSV-3) IRFNAIUDMH 

3. Altair IJl Solid 

Thrust augmented 1. Thor (DSV-3E-1)plus LOXlRP 

Thor Delta three TX33-52 Solid 

2. Delta (DSV-3) IRFNA/UDMH 

3. Altair 111 Solid 

Thor Agena 1. Thor (DM-21) LOX/RP 

2. Agena IRFNA~UDMH 

Thrust augmented 1. Thor (DM-21) plus LOX/RP 

Thor Agena 3 TX 33-52 solid 

2. Agena IRFNAIUDMH 

Atlas Agena 

Titan 11 (GLV) 

Titan IIIA 

Titan IIIB Agena 

Titan IIIC 

Atlas Centaur 

Saturn I 

1. Atlas booster and LOXlRP 

2. Agena IRFNAIUDMH 

1. Two LR-87 N204 / Aerozine 

2. LR-91 N204 IAeroeine 

1. Two LR-87 N~O~lAerozine 

2. LR-91 NZOql Aerozine 

3. Transtage N204 /Aero zine 

1. Two LR-87 N2041Aerozine 

2. LR-91 N204/Aerozine 

3. Agena WFNA/UDMH 

1. Two 5-segment Solid 

2. Two LR-87 NZ04/Aerozine 

3. LR-91 N204/Aerozine 

4. Transtage N20qIAerozine 

1. Atlas booster and LOXIRP 

2. Centaur (Two LOX/LH 

sustainer 

120" diameter 

sustainer 

RL-10) 

1. S-I (8 H-1) LOXIRP 

2. SIV (6 RL-10) LOX~LH 

60.5 

22 

5.9 

169 

7.1 

5.8 

169 plus 

54 each 

7.1 

5.8 

170 

16 

170 

54 each 

16 

388 

16 

4 30 

100 

430 

100 

16 

430 

100 

16 

2,400 

430 

100 

16 

388 

30 

1,500 

90 

8 

11 

8 

11 

10 

90 950 150 1966 (60) 

90 1.275 275 1965 (60) 

76 1,600 -- 1962 (59) 

76 2,200 -- 1963 (60) 

91 6,300 1,150 1961 (60) 

10 90 (8,000 @ -- 105 NM) 

10 110 5,000 

10 112 7,700 

10 x 30 110 23,000 

-- 

1,700 

5,000 

1964 

1964 

1966 

1965 

10 112 8,500 2, 300 1962 

21.6 120 15,000 -- 1st stage 

1961 

2nd stage 

Block 11 

1964 

Uprated Saturn I 1. S-IB (8 H-1) LOXlRP 1,600 21.6 142 23,500 1966 

2. S-IVB (1 J-2) LOX~LH 205 (40.500 @ 

105 NM) 

Saturn V 1. S-IC (5 F-1) LOX/RP 7,500 33 28 1 220,000 95,000 1967 

2. S-I1 (5 J-2) LOX~LH 1,025 (285,000 @ 

3. SIVB (1 J-2) LOX/LH 205 105 NM) 

NOTES: Definitive data are difficult to compile. 

as intended orbital altitude. 

and in engine thrust. First stage thrust shown is sea level value. 

performance, and future modifications may be expected in several cases. 

under development. * The date of first launch applies to this latest modification with a date in parentheses for the earlier version. 

Propellant abbreviations used are as follows: 

single mixture both fuel and oxidizer --Solid; Inhibited Red Fuming Nitric Acid and Unsymmetrical Dimethlhydrazine- -IRFNA/ 

UDMH; Nitrogen Tetroxide and Aerozine--N2O4/Aerozine; Liquid Oxygen and Liquid Hydrogen--LOXILH. 

Payload capacity data vary according to the place and direction of launch as well 

Vehicles still under development may fall short of or exceed their projected capacities, both in payload 

Modifications of existing vehicles have already raised their 

fi general, these data apply to the latest versions now 

Liquid Oxygen and a modified Kerosene--LOX/RP; Solid propellant combining in a 

Values marked -- are either zero or not pertinent for the vehicle. 

161 Appendix B 
EXECUTIVE OFFICE OF THE PRESIDENT 

NATIONAL AERONAUTICS AND SPACE COUNCIL 

WASWINOTON 

D.ecember 31, 1966 

LISTING OF MAJOR SPACE IIFIRSTStt 

ACHIEVED BY THE U. S. AND THE U. S. S. R. 

One of the iridexes used to compare the space programs of the 

United States and the Soviet Union are the "firsts" achieved by 

each nation. 

the quality of achievement, such compilation can be misleading. 

However, a compilation of "firsts" broken down into meaningful 

areas can help in judging emphasis and even relative progress if 

coupled with other evidence. 

Like all indexes which measure the quantity but not 

Regardless of whether a "first" gives either country a significant 

lead in a particular area of space technology, the fact of being first 

is not insignificant in the formation of public opinion. In fact, 

regardless of actual technological competence, the relative position 

of the U. S. and the U. S. S. R. in space is often judged by the "firsts" 

achieved by each. 

A list of all of the "firsts" scored by each side would be long and 

meaningless. An effort has been made to select those actions or 

accomplishments which seemed to be of major imp.ortance. Moreover, because of the closed nature of some aspects of both nations' 

space programs, the list of tlfirststl is even less complete. 

In order to establish some measure of perspective, the list of 

"firsts" printed on the reverse, is divided into major categories 

of space interest. Other breakdowns could have been employed. 

Most important to note is that this is not a comparison of space 

competences but rather is primarily a cataloging based upon the 

timing of events. 

Appendix C 162 
LISTING OF MAJOR SPACE "FIRSTS" ACHIEVED BY THE U.S. AND THE U.S.S.R. 

UNITED UNION OF SOVIET 

Event 

XIALBT REP 

Satellite 

3LICS 

Launch 

Date 

FATES 

Satellite Launch 

Date Event 

Discovery of Van Allen 

Discovery that Earth is 

First orbiting solar observ. 

First probe of Venus 

First geodetic satellite 

First close-up pictures of 

the lunar surface 

First coded data over 

100 million miles 

First Mars space pictures 

First comprehensive 

micrometeoroid satellite 

First lunar orbit pictures 

Radiation Belts 

"pear shaped" 

~~ 

First orbiting geophysical laboratory 

First photos of the 

moon's far side 

First comprehensive 

cosmic ray station 

First pictures from 

lunar surface 

First lunar surface 

test 

2/1/58 

3/26/58 

3/17/58 

3/7/62 

6/27/62 

10/31/62 

1/28/64 

11/28/64 

11/28/64 

2/16/65 

8/10/66 

Explorer I 

&III 

Vanguard I 

Dso I 

Mariner II 

4nna IB 

Ranger VI1 

Mariner IV 

Mariner IV 

Pegasus I 

Lunar Orbiter I 

5/15/58 

10/4/59 

7/16/65 

1/31/66 

12/21/66 

Sputnik 111 

Luna 111 

Proton I 

Luna IX 

Luna XIII 

SCIENCE 

12/18/58 

8/7/59 

4/1/60 

4/13/60 

5/24/60 

8/12/60 

10/17/63 

First active communicaFirst TV pictures from 

First weather satellite 

First navigation satellite 

First missile detection 

First passive communicaFirst nuclear explosion 

tions satellite 

space 

satellite 

tions satellite 

detection satellite 

First manned orbital 

First manned propulsion 

First sustained space 

First docking of two craft 

maneuver 

outside craft 

rendezvous 

Score 

Explorer VI 

Tiros I 

Transit IB 

Midas I1 

Echo I 

Vela Hotel 

Gemini III 

Gemini IV 

Gemini VI1 

and VI 

Agena Target 

Gemini VIII 

APPLICATIONS 

11/3/57 

8/19/60 

4/12/61 

8/11/62 

8/12/62 

10/ 12/64 

3/18/65 

3/23/65 

6/3/65 

12/4/65 

12/15/65 

3/16/66 

3/16/66 

First biosatellite 

First orbited animals 

recovered 

First orbited human 

recovered 

First approximate 

rendezvous 

First multi-manned 

craft in orbit 

First man to leave 

capsule in space 

Sputnik II 

Korabl -Sputnik 

II 

Vostok I 

Vostok 111 

&Iv 

Voskhod I 

Voskhod II 

BIOASTRDNAUTIC! 

AND MANNED 

SPACE FLIGHT 

First multiple payloads 

First recovered payload 

First air snatch payload 

First synchronous satellite 

First multiple orbits 

First hydrogen-fueled 

rocket to orbit 

First sub-orbital test of 

an ion engine 

First propulsion of two 

craft docked in orbit 

recovery 

First satellite 

First escape payload 

First lunar impact 

First orbital launch 

First flight-by Venus 

First flight -by Mars 

First ion engine test 

First plasma rocket 

First Venus impact 

First lunar 

First lunar orbiter 

platform 

in orbit 

tested in orbit 

soft -landing 

Sputnik I 

LUM I 

Luna 11 

Sputnik V 

Venera I 

Mars I 

Voskhod I 

Zond ll 

Venera 111 

Luna M 

Luna X 

10/4/57 

1/2/59 

9/12/59 

2/12/61 

2/12/61 

11/1/62 

10/12/64 

11/30/64 

11/16/65 

1/31/66 

3/31/66 

Transit IIA & 

Discoverer XI11 

Discoverer XIV 

Syncom I1 

Vela Hotel 

I and 11 

Centaur 11 

SERT IA 

Agena Target 

Gemini X 

Solrad I 

Vanguard I 

Transit IVA 

Transit VBN 1 

Snapshot I 

Gemini V 

6/22/60 

8/10/60 

8/18/60 

7/26/63 

10/17/63 

11/27/63 

7/20/64 

7/18/66 

SPACE FLIGHT 

AND PROPULSlOH 

First solar cells on craft 

First craft with isotope 

First craft powered only 

First nuclear reactor in 

First space use of fuel cell 

power 

by nuclear energy 

orbit 

3/17/58 

6/23/61 

9/28/63 

4/3/65 

8/21/65 

AUXILIARY POWEl 

SYSTEMS 

December 31, 1966 

NATIONAL AERONAUTICS AND 

163 
HISTORICAL SUMMARY -- PROJECT GEMINI 

Mission and 

Launch Date 

Gemini 3 

Mar. 23, 1965 

Crew Duration Highlights 

Grissom & 

Young 

4 hours , 53 minutes 

First U.S. two man crew, first 

use of orbital maneuvering system, 

fir st controlled reentry. 

97 hours , 56 minutes 

First extravehicular activity, first 

use of personal propulsion. Near 

rendezvous achieved. 

Gemini 4 

June 3, 1965 

McDivitt & 

White 

190 hours, 

56 minutes 

Demonstrated psychological feasi - 

bility of lunar trip by staying in 

space for period of lunar trip. 

Gemini 5 

Aug. 21, 1965 

Cooper & 

Conrad 

Gemini 7 

Dec. 4, 1965 

Borman & 

Lovell 

330 hours, 

35 minutes 

Set manned space flight duration 

re cord. 

Gemini 6 

Dec. 15, 1965 

Accomplished first rendezvous , coming within six feet of Gemini 7. 

Schirra & 

Stafford 

25 hours , 51 minutes 

Gemini 8 

Mar. 16, 1965 

Armstrong & 

Scott 

10 hours, 

42 minutes 

First dual launch and docking with 

an Agena. Mission curtailed by 

short circuit in craft's thrusters. 

Stafford &I 

Cer nan 

Unable to dock due to failure of 

shroud to completely separate from 

the target's docking adapter. 

Extravehicular activity perf or me d. 

Gemini 9 

June 3, 1966 

72 hours, 

21 minutes 

70 hours, 

46 minutes 

First dual rendezvous (with its own 

target vehicle and the one launched 

for Gemini 8). 

maneuvers using Agena as propulsion 

stage. Extravehicular activity with 

first manned retrieval of an experiment. 

First docked vehicle 

Gemini 10 

July 18, 1966 

Young & 

Collins 

Gemini 11 

Sept. 12, 1966 

Conrad & 

Cor don 

71 hours, 

17 minutes 

Rendezvous and docking achieved on 

fir st revolution. Extravehicular 

activity. Successful station keeping 

with Agena target vehicle tied together by a tether. 

(851 miles). 

Highest apogee 

Gemini 12 

Nov. 11, 1966 

Lovell & 

Aldrin 

94 hours , 34 minutes Extravehicular activity record set 

(five hours , 37 minutes). Station 

keeping with ,target vehicle achieved 

by use of tether. 

Appendix D 164 
N 

rl 

3 

2 

a 

5 

E 

I 

c 

W 

k 

a 

V 

Id 

0 

fi 

4 

.rl d 

.rl c, 

mz 

d 

.Y Q) 

o\ 

0 

d 

b 

m 

0 

fi 

ul 

$ 

Id 

k 

m 

ul 

$ 

1 

m 

rl 

(u 

0 

I 

m 

0 

N 

In m 

0 m 

0 

d 

m N tc N 

m d 

rl 

Appendix E 165 
SPACE ACTIVITIES OF THE UNITED STATES GOVERNMENT 

Historical Summary and 1968 Budget Recommendations January 24, 1967 

NEW OBLIGATIONAL AUTHORITY 

(In millions of dollars) 

NASA Dept. of 

Total Spacell Defense 

1955 56.9 56.9 

1956 72.7 72. 7 

1957 78. 2 78. 2 

1958 117.3 117.3 

1959 305.4 235.4 

1960 523.6 461.5 

1961 964.0 926.0 

1962 1824.9 1796.8 

1963 3673.0 3626.0 

1964 5099.7 5046.3 

1965 5249.7 5167.6 

1966 5174.9 5094.5 

3.0 

30. 3 

71.0 

205.6 

489.5 

560.9 

813.9 

1298.2 

1549.9 

1599.3 

1579.4 

1692.8 

1968 

Budget 

1967 4967.6 4864.2 1670.5 

1968 5050.0 4930.4 1998.3 

- AEC 

-- 

7.0 

21.3 

21.3 

34.3 

43.3 

67. 7 

147.8 

213.9 

210.0 

228.6 

186.8 

181.3 

151.6 

Com- Inte- Agrimerce rior culture - NSF 

29.6 4.3 

34.8 4. 8 

-- 

7.3 

8.4 

3.3 

.1 

.6 

1.3 

1.5 

3.0 

3.2 

3.2 

--- 

2.4 

2.8 

Total 

Space 

59.9 

117.3 

178.9 

347.5 

759.2 

1065.8 

1808.2 

3294.8 

5434.5 

6861.4 

6991.0 

7007.9 

6752.3 

7123.1 

1/ 

Source: Bureau of the Budget 

bcludes amounts for aircraft technology in 1959 and succeeding years. Amounts 

for NASA-NACA aircraft and space activities not separately identifiable prior to 1959. 

U.S. SPACE BUD6ET - NEW OBLI6ATIONAL AUTHORITY BILLIONS OF DOLLARS 

8. 0 

1968 REQUEST 

JAN. 24, 1967 

1961 1962 1963 1964 1965 1966 1967 

NASC STAFF 

Appendix F-1 166 
SPACE ACTIVITIES OF THE UNITED STATES GOVERNMENT 

Historical Summary and 1968 Budget Recommendations January 24, 1967 

EXP ENDIT UR ES 

1955 

1956 

1957 

1958 

1959 

1960 

1961 

1962 

1963 

1964 

1965 

1966 

1968 

Budget 

1967 

1968 

(In millions of dollars) 

Total 

Total Space L/ Defense AEC merce rior culture NSF Space 

Dept. of Com- Inte- Agri- NASA 

- 

73.8 

71. 1 

76. 1 

89. 2 

145.6 

401.0 

744.3 

1257.0 

2552.3 

4171.0 

5092.9 

5933.0 

5600.0 

5300.0 

73. 8 

71. 1 

76. 1 

89. 2 

58.8 

329.2 

693.6 

1225.9 

2516.8 

4131. 3 

5035.0 

5857.9 

5505.0 

5 190.0 

1.5 -- -- -- -- -- 

-- 6.2 

-- 7.3 

-- 4.0 

-- 1.5 

16.5 6.3 -- -- 

47.5 19.2 -- -- 

135.5 20.2 -- -- 

341.0 32.6 -- -- 

518.1 41. 1 -- -- -- -- 

710.0 64.3 -- -- -- -- 

1028.8 130.0 1.0 -- .9 -- 

1367.5 181.0 12.2 -- -- 1.1 

1563.5 220.1 12.3 -- -- 2.6 

1591.8 232.2 24.1 -- -- 3.0 

1637.4 188.3 28.1 4.0 -- 2. 8 

1680.0 182.6 29.5 4.1 -- 2.0 

1840.0 152.2 40. 1 4.6 0.4 2.4 

75.3 

100.1 

150.1 

248.9 

433.9 

888.4 

1467.9 

2386.6 

4078.6 

5929.8 

6886.1 

7718.5 

7403.2 

7229. 7 

1/ Excludes amounts for aircraft technology in 1959 and succesding years. 

Amounts for NASA-NACA aircraft and space activities not separately identifiable 

prior to 1959. 

Source: Bureau of the Budget 

U.S. SPACE BUDGET - EXPENDITURES BILLIONS OF DOLLARS 

8.0 

70 6.8- .. - 

6.0 

5.0 

4. 0 

3. 0 

2.0 

1.0 

1961 1962 1963 1964 1965 

167 

1966 1967 

7. 2 

1968 REQUEST 

JAN. 24. 1967 

NASC STAFF 

Appendix F-2 
SPACE ACTIVITIES BUDGET 

1968 Budget Document 

January 24, 1967 

(In millions of dollars) ~~~ ~ 

New Obligational Authority Expenditures 

1966 1967 1968 1966 1967 1968 

(Actual) (Estimated) (Actual) (Estimated) 

Federal Space Programs 

NASA 1/ ................. 5094.5 4864.2 4930.4 5857.9 5505.0 5190.0 

Department of Defense. ... 1692.8 1670.5 1998.3 1637.4 1680.0 1840.0 

Atomic Energy Commission 186.8 181.3 151.6 188.3 182.6 152.2 

Department of Commerce.. 26.5 29. 6 34.8 28. 1 29.5 40. 1 

Department of Interior.. ... 4. 1 4. 3 4. 8 4.0 4.1 4.6 

Department of Agriculture. -- -- 0.4 -- -- 0.4 

National Science Foundation 3.2 2.4 2. 8 2. 8 2.0 2.4 

TOTAL 7007.9 6752.3 7123.1 7718.5 7403.2 7229.7 

NASA 

Manned space flight.. .... 3530.3 

Space applications. ....... 11 5. 3 

Space technology.. ....... 403.7 

Aircraft technology. ..... 80.4 

Supporting operations .... 333.8 

Scientific investigations.. . 689. 0 

Adjustments to NOA basis t 22. 5 

Total.. .............. 5174.9 

3398.2 

559.5 

112.2 

384.8 

103.4 

349.6 

t 60.0 

4967.6 

3435.8 

602.5 

161.0 

424.3 

119.6 

366.8 

5050.0 

-60.0 

4210.2 

664.1 

113.6 

435.4 

75.1 

434.6 

5933.0 

-- 

3825.0 

660.0 

110.0 

450.0 

95.0 

460.0 

5600.0 

-- 

- 

3575.0 

600.0 

140.0 

440.0 

110.0 

435.0 

5300.0 

-- 

1 / Excludes amounts for aircraft industry. - 

Source: Bureau of the Budget 

Appendix F-3 168 
INDEX 

A-7 62,63 

Advanced Aerial Fire Support 

System (AAFSS) 129 

Advanced Research Projects 

Agency (ARPA) 58, 68, 144 

Aeronautics 28, 30, 128-131, 135 

Aeronautics, Astronautics Coordinating 

AGENA 

Agriculture, Dept. of 118 

Air Force, U. S. 32,47, 63, 64, 127 

ALOUETTE 44, 99, 100 

Ames Research Center 30, 36, 118 

Andover, Maine, Ground Station 133 

Antarctica 90, 143 

Board (AACB) 47-49,67, 71 

1, 12, 13, 23, 26,41, 54, 73, 79 

APOLLO 2, 3, 12, 14-18, 21, 29, 34, 41,43, 

72, 74,77,84, 101, 102, 133, 134, 137-139 

APOLLO Applications 

APOLLO Telescope Mount 

Applications Technology Satellites 11, 19, 

24, 26, 38,42, 94, 128, 136 

Argentina 45,46, 123, 137, 138 

Arms Control and Disarmament 

ASSET 66 

Astronauts 

18, 19, 26, 33, 45 

APOLLO-SATURN 11, 14-18, 33,41,42 

19, 22, 35 

Agency 143, 144 

12, 16, 32, 33, 34, 45, 50, 77, 

83-85, 112, 113, 139-141 

Astronomy 113, 114 

ATLAS 

Atomic Energy Commission 12, 38, 

Australia 

Automatic Picture Transmission 

4,26, 30,43, 73, 79, 107 

75-79, 141 

12, 42, 43, 83, 94, 139 

(APT) 24,46,81,82, 93-95 

Bennington, USS 65 

Bioastronautics 30, 72, 117 

Biosatellites 5, 11, 23, 26 

Bolivia 90 

Brazil 45, 46, 90, 137, 138 

C-5A 53, 61, 129 

C-130 65 

Canada 43,83, 98 

CENTAUR 4,26, 34,43, 107 

Cerro Tololo Inter American 

Chile 83 

Coast and Geodetic Survey 92,97, 

Commerce, Dept. of 12, 51,91-109 

Command Service Module (CSM) 14, 

Communications, Defense Satellite 

Communications Satellites 128, 133 

Communications Satellite Act of 

Communications Satellite Corp. 2, 

COSPAR 100, 111, 115, 116 

Counterinsurgency Aircraft 

Czechoslovakia 11 6 

Observatory (Chile) 88 

98, 101, 120 

16, 17, 73 

Program 54, 55 

1962 133, 134 

85, 133, 134, 141 

(COIN) 63 

DATS 68 

Deep Space Network 43 

Defense, Dept. of 2, 12,42, 47,48,49, 

50, 53-74, 77, 79, 84, 85, 92, 102, 111, 

118, 127 

DELTA 26,73 

Denmark 46 

EARLY BIRD 14,24,41, 133,134, 141 

Eastern Test Range 59 

ECHO 98, 120 

Ecuador 83 

Electronics Research Center 34 

Environmental Science Services 

ESSA Satellites 

Ethiopia 120 

European Launch Development Org. 

European Space Research Org. 

EVA 13 

EXPLORER 4, 19,20, 34, 58, 99, 120 

Administration 19, 91-101 

19, 24, 91-94, 141 

(ELDO) 85, 144 

(ESRO) 46,47,84,85 

169 
F-1 Engine 17 

F-104 30 

F-11A 4, 62 

Federal Aviation Agency 29,48, 108, 

Federal Communications Commis - 

116,118 

sion 133-136 

France 43,46,90 

French National Center for Space 

FR-1 43 

Studies 45 

GEMINI 1, 2, 3, 11-14, 18, 22, 23, 33,41, 

42,46, 53, 60, 71, 73, 74, 91, 95, 96, 100- 

102, 119, 134, 137-142 

Geological Survey, U. S. 117, 140 

GEOS 25, 58, 59, 120 

Germany 45,85 

GLOTRAC 42 

Goddard Space Flight Center 34,42, 

101, 104, 105 

Gravity Gradient Stabilization 24 

Greece 45, 120 

Health, Education and Welfare, 

Helicopters 130 

HL-10 Lifting Body 5, 33 

Hurlburt, E. 0. Center for Space 

Dept. of 12 

Research 88 

IGY 89 

IMP 20 

India 46 

INTELSAT Consortium 85 

International Year of the Quiet Sun 

(IQSY) 89 

Iran 120 

Israel 45,96 

Italy 45, 90 

INTELSAT -11 2,24,43,85, 133- 135, 140 

5-2 Engine 17 

Japan 45, 90, 116, 137, 139 

Jet Propulsion Laboratory 

(JPL) 27,49, 77 

Jupiter, Planet 122 

Kennedy, Cape 15, 16, 58, 72,85, 101, 102 

Kennedy Space Center 16, 17, 18,47, 51 

Kitt Peak National Observatory 87 

KIWI 39 

Langley Research Center 30 

Lasers 34 

Lawrence Radiation Laboratory 37 

LES 57 

Lewis Research Center 35,107 

Los Alamos Scientific Laboratory 38 

Lunar Excursion Model (LEM) 2, 14, 

Lunar Orbiter 2, 3, 11, 18-21, 26, 34, 

16-19,22,73,99, 100 

43, 72,73,81, 138-141 

M-1 Engine 5, 30 

Malagasy 12,83 

Manned Orbiting Laboratory 

(MOL) 2, 3, 50 

Manned Spacecraft Center (MSC) 16, 

43,77 

Manned Space Flight Network 41,44, 

53, 60 

MARINER 5,21,22,43, 123 

Mars, Planet 22, 27, 114, 122, 123 

MERCURY, Project 13 

Merritt Island 18 

Mexico 12, 83, 137, 138 

Michoud Assembly Facility 17, 18 

Mississippi Test Facility 17, 18 

NASCOM 43,44 

National Academy of Sciences 

National Aeronautics and Space 

11 1 - 

118 

Administration 2, 7, 11 -52, 67, 69, 

105, 108, 111, 112, 117, 118, 122, 

71-73, 75, 77, 78, 83, 84, 92, 94, 97- 

138-142 

National Aeronautics and Space 

National Bureau of Standards 98, 

National Science Foundation 87 -90, 

National Environmental Satellite 

NATO 57 

Naval Research Laboratory 117 

Navy, U.S. 12, 32, 101 

Navigational Satellites 59 

Council 7-10, 111 

102-108 

111 

Center (NESC) 91-97 

170 
NERVA 4, 11, 38, 39,40, 72, 75, 76 

Netherlands 45,46, 90, 93-95, 120 

New Zealand 139 

Nigeria 12,42,46, 83, 84 

NIMBUS 19,24,25 

Norway 46, 135 

Nuclear Space Systems 36, 37 

Nuclear Rocket Program 38-41 

0 rbiting Astronomical 0 bs e rvato ry 

Orbiting Geophysical Observatory 

Orbiting Solar Observatory (OSO) 

(OAO) 19,26,41, 103, 140 

(OW) 19, 34,41, 99, 140 

4, 11 

OV-10 63 

Pakistan 46 

PAGEOS 4, 58,98, 120 

PEGASUS 34 

Peru 83, 122 

PHOEBUS 5, 38, 39,40,76 

PIONEER 4,43 

Propulsion, chemical 30 

Propulsion, electric 5 

Propulsion, nuclear 38,41, 75 

Propulsion, solid 30 

Radars 66 

RANGER 122, 139, 142 

SANMARCO 45 

S-I1 SATURN Stage 18 

SATURN I 

SATURN V 

2, 3, 14-19, 30, 101 

2, 3, 14-18, 22, 34, 35 

SCOUT 26,45 

SCANNER, Project 35 

SECOR 58 

SERT 38 

Smithsonian Institution 119-123 

Smithsonian Institution Astro - 

physical Observatory 11 9-123 

SNAP 5, 36,77-79 

Sounding Rockets 45,46 

South Africa 83 

Space Rescue 9 

Space Suit 32 

Space Science Board 

Spain 45, 83, 84 

SPASUR 60 

STADAN 42 

11 1, 112 

START 66 

State, Dept. of 81-86 

SURVEYOR 2, 3,4, 11,17-20,26,41, 

43, 72, 74, 81, 138-141 

Supersonic Transport (SST) 

Sweden 46 

SYNCOM 55 

2, 3, 9, 

11, 27, 28, 129 

Technology Utilization 48, 51, 52 

THOR 26, 30, 60 

TITAN 11 60 

TITAN 111 

TIROS 24, 59,91-94, 99 

34,41, 53-57, 60, 79 

TIROS Operational Satellite 

Tracking and Data Acquisition 41 -44, 

System 5, 9, 92, 99 

83, 84, 92, 94 

United Nations 

United Nations Space Treaty 

United States Information Agency 

USS Mason 13 

USSR 2, 3, 9, 10,46, 92, 95, 116, 138, 

140 

United Kingdom 12,45,46,83,84 

81 -83, 97, 118, 143 

1, 2,4, 

8,81-83, 137, 143 

137 - 142 

Vandenberg AFB 59 

Vehicle Assembly Building (VAB) 18 

VELA 79, 144 

Voice of America 137-142 

VOYAGER 5,21,22,49 

V/STOL 5, 30, 64, 131 

VTOL 30, 69, 70 

Wallops Island 45, 92, 94, 121 

Western Test Range 59-61 

World Meteorological Organization 

(WMO) 118 

X-15 5, 11,29, 50, 65 

XB-70 

XC-142A 65 

4, 11, 30, 50, 63 

YCH-54A 129 

171 

GSA DC 67-11743