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ABSTRACT
 

This document presents formal NASA technical reports, papers published in technical 

journals, and presentations by MSFC personnel in FY 74. It also includes papers- of MSFC 

contractors. 

After being announced in STAR or C STAR, all of the NASA series reports may be 

obtained from the Scientific and Technical Information Facility, P.O. Box 33, College Park, 

Maryland 20740. 

The information in this report will be of value to the scientific and engineering 

community in determining what information has been published and what is available. 
FY 1974 SCIENTIFIC AND TECHNICAL REPORTS,
 

ARTICLES, PAPIiRS, AND PRESENTATIONS
 

Technical Publications Division
 

Manaeement Services Office
 
FOREWORD
 

In accordance with the NASA Space Act of 1958 the MSFC has provided for the widest 

practicable and appropriate dissemination of information concerning its activities and the results 

thereof. 

Since July 1, 1960, when the George C. Marshall Space Flight Center was organized, the 

reporting of scientific and engineering information has been considered a prime responsibility of 

the Center. Our credo has been that "research and development work is valuable, but only if its 

results can be communicated and made understandable to others." 

The N numbers shown for the reports listed are assigned by the NASA Scientific and 

Technical Information Facility, College Park, Maryland, indicating that the material is 

unclassified and unlimited and is available for public- use. The N number should be cited when 

requesting a document. 
GEORGE C. MARSHALL SPACE FLIGHT CENTER
 

Marshall Space Flight Center, Alabama
 

FY 1974 SCIENTIFIC AND TECHNICAL REPORTS,
 

ARTICLES, PAPERS, AND PRESENTATIONS
 

TABLE OF CONTENTS
 

Page
 

NASA TECHNICAL MEMORANDA .................................... I
 

NASA TECHNICAL NOTES .......................................... 32
 

NASA TECHNICAL REPORTS ........................................ 39
 

NASA SPECIAL PUBLICATIONS ........................................ 41
 

CONTRACTOR REPORTS ........................................... 42
 

MSFC IAPERS Ct4EARED FOR PRESENTATION ............................. 75
 
NASA TECHNICAL MEMORANDUM
 

TM X2935 October 1973 

An Analytical Analysis of the Dispersion 

Predictions for Effluents from the Saturn 

V and Scout-Algol III Rocket Exhausts. 

J_ Briscoe Stephens, Michael Susko, John 

W. Kaufman, C. Kelly Hill. AeroAstrodynamics Laboratory. N74-33327 

Predictions of the spatial concentration 

mapping of -the potentially toxic constituents 

of the exhaust effluents from a launch of a 

Saturn V and of a Scout-Algol III vehicle 

utilizing the NASA/MSFC Multilayer Diffusion Program are provided. In the case of the 

Saturn V, special attention was given to the 

concentration fields of carbon monoxide with 

a correlation of carbon dioxide concentrations. The Scout-Algol III provided an 

example of the centerlirie concentrations of 

hydrogen chloride, carbon monoxide, and 

alumina under typical meteorological conditions. While these re:;ults define the specific 

environmental impact of these two launches 

under the meteorological conditions existing 

during launches, they also provide a basis for 

the empirical monitoring of the constituents 

of the exhaust effluents of these vehicles. 

TM X-2938 December 1973 

Data for First NASA Atmospheric Variability Experiment (AVE I) Part 1: Data 

Tabulation. James R. Scoggins and Orvel 

E. Smith. Aero-Astrodynamics Laboratory. N74-15350 

This report presents a tabulation of 

rawinsonde data 'for NASA's first Atmospheric Variability Experiment (AVE 1) conducted during the period February 19-22, 

1964. Methods of data handling and processing, and estimates of error magnitudes are 

also given, 

Data taken on the AVE I project in 

1964 enabled an analysis of a large sector of 

the eastern United States on a fine resolutiot 

time scale. This experiment was run in 

February' 1964, and data were collected as a 

wave developed in the East Gulf on a frontal 

system which extended through the eastern 

part of the United States. The primary 

objective of AVE I was to investigate the 

variability of parameters in space and over 

time intervals of three hours, and to integrate 

the results into NASA programs which require 

this type of information. The results presented in this report are those from one 

approach, and represent only a portion of the 

total research effort that can be accomplished. 

This report consists of two parts: Part I 

- Data Tabulation and Part II - Graphical 

Presentation of Data. 

TM X-2939 November 1973 

Prediction of Engine Exhaust Concentrations Downwind from the Delta-Thor 

Telsat-A Launch of November 9, 1972. 

John W. Kaufman, Michael Susko, 

C. Kelly Hill. Aero-Astrodynamics Laboratory. N74-10583 

Presented in this report are the results of 

the downwind concentrations of engine 

exhaust by-products from the Delta-Thor 

Telsat-A vehicle launched from Cape 

Kennedy, Florida, on November 9, "1972 

(2014 EST). The meteorological conditions 

which existed are identified as well as the 

exhaust cloud rise and the results from the 

MSFC Multilayer Diffusion Model calculations. These predictions are herein compared 

to exhaust cloud sampled -data acquired by 

the Langley Research Center personnel. 
NASA TECHNICAL MEMORANDUM
 

Values of the surface level concentrations - TM X-64757 July 5, 1973 

show that very little hydrochloric acid (HCI), Terrestrial Environment (climatic) Critecarbon monoxide (CO), or aluminum oxide ria Guidelines for ]Use in Aerospace 

(Al 2 03) reached the ground. Vehicle Development, 1973 R~vision. 

Glenn- E. Daniels, Editor. AeroTM X-2948 December 1973 Astrodynamics Laboratory. N74-16293 

Data for First NASA Atmospheric Vari­

-ability Experiment (AVE 1) Part If: This document provides guidelines on 

Graphical Presentation of Data. James R. probable climatic extremes and probabilitiesScoggins and Orvel E. Smith. Aero-, of-occurrence of terrestrial environment data 

Astrodynamics Laboratorj,. N74-16321 specifically applicable for NASA space 

vehicles and associated equipment developThis report presents a graphical represen- ment. The geographic areas encompassed are 

tation of data for NASA's first Atmospheric The Eastern Test Range (Cape Kennedy, 

Variability Experiment (AVE i) conducted Florida); Huntsville, Alabama; New Orleans, 

during the period February 19-22, 1964. Louisiana; The Space and Missile Test Center 

Graphical representation is in the form of (Vandenberg -AFB California); Sacramento, 

synoptic charts and time cross section, California; Wallops Test Range (Wallops 

Island, Virginia); White Sands Missile Range, 

Data taken on the AVE I project in New Nexico; and intermediate transportation 

1964 enabled an analysis of a large sector of areas. In addition, sections have been included 

the eastern United States on a fine resolution to provide information on the general distritime scale. This experiment was run in bution of natural environment extremes in 

February 1964, and data were collected as a the United States (excluding Alaska and 

wave developed in the East Gulf on a frontal Hawaii), cloud cover, and some worldwide 

system which extended through the eastern climatic extremes. Although all these areas are 

part of the United States. The primary covered, the major emphasis is given to the 

objective of AVE I was to investigate the Kennedy Space Center launch area and 

variability of parameters in space and over Vandenburg Air Force Base due to importime intervals of three hours, and to integrate tance in NASA's future large space vehicle 

the results into NASA programs which require programs. 

this type of information. The results presented in this report are those from one This document presents the latest availapproach, and represent only a portion of the able information on probable climatic 

total research effort that can be accom- extremes, and supersedes information preplished. sented in TM X-64589. The information in 

this document is recommended for employment in the development of space vehicles 

This report consists of two parts: Part I and associated equipment design and opera­

- Data Tabulation and Part II - Graphical tional criteria, unless otherwise stated in 

Presentation of Data. contract work specifications. 

2 
NASA TECHNICAL MEMORANDUM
 

TM X-64758 July 9, 1973 

Statistical Properties of Filtered Pseudorandom Digital Sequences Formed from 

the Sum of Maximum-Length Sequences. 

G. R. Wallace, Glenn D. Weathers, and 

Edward 	R. Graf. Astrionics Laboratory. 

N73-27516 

...... 

The statistics of 'filtered pseudorandom 

digital sequences called hybrid-sum sequences, 

formed from the modulo-two sum of several 

maximum-length sequences, are analyzed. The 

results indicate that a relation exists between 

the statistics of the filtered sequence and the 

characteristic polynomials of the component 

maximum-length sequences. An analysis procedure is developed for identifying a large 

group of sequences with good statistical 

properties for applications requiring the generation of analog pseudorandom noise. By use 

of the analysis approach, the filtering process 

is approximated by the convolution of the 

sequence with a sum of unit-step functions. 

The first five moments of the resulting weight 

tuples are used to characterize the statistics of 

the filtered sequence. At this point, a 

parameter reflecting the overall statistical 

properties of filtered pseudorandom sequences 

is derived. This parameter is called the 

statistical quality factor. A computer algorithm to calculate the statistical quality factor 

for the filtered sequences is presented, and 

the results for two examples of sequence 

combinations are included. The analysis 

reveals, that the statistics of the signals 

generated with the. hybrid-sum generator are 

potentially superior to the statistics of signals 

generated with maximum-length generators. 

Furthermore, fewer alculations are required 

to evaluate the statistics of 	a large group of 

hybrid-sum generators than 	 are required to 

evaluate the statistics of the same size group 

of -approximately equivalent maximum-length 

sequences. Pseudorandom signals generated by 

filtering hybrid-sum sequences have a potential application in a multichannel communications system evaluation technique. There are 

also applications for these sequences in areas 

such as coding theory and modulation format 

design for pseudonoise transponders. 

TM X-64759 April 20, 1973 

Thermal Conductivity of Particulate 

Materials: A Summary of Measurements 

Taken at the Marshall ESpace Flight 

Center. James A. Fountain, Ronald W. 

Scott, and Edward A. West. Space 

Sciences Laboratory. N73-27801 

Thermal conductivity measurements of 

particulate materials in vacuum are presented 

in summary. Particulate basalt and soda lime 

glass beads of various size ranges were used as 

samples. The differentiated line heat source 

method was used for the measurements. A 

comprehensive table is shown giving all 

pertinent experimental conditions. Leastsquares curve fits to the data are presented 

for K = A + BT and K = A + BT + CT 3 . 

The latter equation is shown to give a slightly 

better fit to the data in most cases. In the 

relatively low vacuum data, the curves K = A 

+ BT and K = A + BT + CT2 were fitted to 

the data. 

TM X-64760 June 12, 1973 

Development and Evaluation of Polyimide Laminates for Printed Wiring Board 

Applications. William J. Patterson. Astronautics Laboratory. N73-26581 

This report describes a developmental 

and evaluation program on polyimide 

3 
NASA TECHNICAL MEMORANDUM
 

laminates as printed wiring boards. The 

development of an experimental polyimide 

with low linear coefficient of thermal expansion normal to the plane of the board is 

discussed, 'and its properties are evaluated 

along with two commercial polyimide printed 

wiring boards for comparison with the type 

G-10 epoxy board. Thermal cycling data 

indicate an urgent need for effectively 

controlling the expansion normal to the plane 

of the board in order to minimize solder joint 

damage. 

TM X-6476.1 July 24, 1973 

Natural Environment Design Requirements for the Solar Electric Propulsion 

Stage (SEPS). Lewis E. Andrews. AeroAstrodynamics. N73-27708 

Given in this report are the natural 

environment design requirements for the Solar 

Electric Propulsion Stage. Environment criteria for the SEP Stage will cover earth orbital 

operations out to geosynchronous altitudes 

and also interplanetary missions including 

comet and asteroid missions, 

TM X-64762 July 27, 1973 

Notes for the Improvement of a Remote 

Sensing Multispectral Data NonSupervised Classification and Mapping 

Technique. Charles C. Dalton. AeroAstrodynamics. N73-27332 

The rep6rt examines the "Sequential 

Clustering" technique for the unsupervised 

automatic classification and mapping of earth 

resources satellite data, makes theoretical 

analysis of the tests which were used, and 

derives an alternative set of tests and their 

necessary algorithm, 

TM X-64763 August 1, 1973 

LST Phase A Design Update Study. 

Program Development. N73-28494 

This document is an update of the Phase 

A study (TM X-64726) of the Large Space 

Telescope (LST), based on changes in guidelines and new data developed subsequent to 

the Phase A study. The study defines an LST 

concept .based on the broad mission guidelines 

provided by the Office of Space Science 

(OSS), the scientific requirements developed 

by OSS with the scientific community, and 

an understanding of long range NASA 

planning current at the time the study was 

performed. 

The LST is an unmanned astronomical 

observatory facility, consisting of an optical 

telescope assembly (OTA), scientific instruments (SI), and a support systems module 

(SSM). The report consists of one volume. 

The report describes the constraints and trade 

off analyses that were performed to arrive at 

a reference design for each system and for the 

overall LST. 

The LST will be launched' into low earth 

orbit by the Space Shuttle and operated for 

10 to 15 years. The Shuttle will also be used 

to maintain the LST and to update the 

scientific instrument complement. Groundreturn maintenance is the primary maintenance mode, with limited on-orbit EVA as an 

adjunct. 

The LST will provide the' scientific 

community with several fundanentally unique 

capabilities which will permit the acquisition 

of new and important observational data. Its 

location in space permits observations over 

4 
NASA TECHNICAL MEMORANDUM
 

the entire spectrum from about 100 nm to One method of sampling materials for 

the far infrared, detection of embedded organisms utilizes the 

crushing action of a Mill Blender. Destruction 

A low cost design approach was followed of microorganisms is high and decreases 

in the study. This resulted in the use of accuracy of the biotests. 

standard spacecraft hardware, the provision 

for maintenance at the black box level, To improve upon this method and 

growth potential in systems designs, and the device, a Biodetection Grinder was developed. 

sharing of Shuttle maintenance flights with It is a device that employs a shearing action 

other payloads, to generate controllable, sized particles with a 

minimum of energy input. 

TM X-64764(Revised) June 1974 

The Project Management Role in Safety. TM X-64766 June 1973 

R. C. Callaway. Safety and Manned Stripping Flat Conductor Cable. 

Flight Awareness Office. N73-28937 W. Angele. Process Engineering Laboratory. 

"Techniques to be utilized by project 

management in the planning, implementation, Techniques and equipment are described 

and administration of a project safety pro- for stripping flat conductor cable (FCC) prior 

gram are presented. to cable termination to connectors. Major 

areas covered are the standard FCC insulation 

Safety functional responsibilities are clas- systems, methods for stripping unshielded 

sified into two categories: safety management cables, and methods for stripping shielded 

and safety engineering. The emphasis in this cables. 

document is the safety management role, and 

how safety activities are to be integrated TM X-64767 August 1973 

throughout the project and made visible in The Load-Carrying and Thermal Characthe work breakdown structure and cost teristics of Flat Conductor Cable. George 

accounting and reporting. Safety inputs into D. Adams. Process Engineering Laborathe RFP, contractor program plans. etc., tory. N73-29125 

constitute an effective method of safety 

achievement. The load-carrying and thermal characteristics of flat conductor cable and round 

The project manager must provide for wire cables have been investigated with all 

and have visibility into systematic identifica- conductors in each cable under varying loads 

tion and control of hazards. in air and vacuum environments. The test 

procedure- is described and results are preTM X-64765 August 9, 1973 sented in graphic form. Derating factors for 

Biodetection Grinder. F. J. Beyerle. both round wire and flat conductor cable are 

Process Engineering Laboratory. . established for operation in a vacuum environN73-29059 ment. Rating factors are established for flat 

5 
NASA TECHNICAL MEMORANDUM
 

conductor cable for use with round wire 

loading tables. The results of these tests show 

that single layer flat conductor cable can 

carry over 150 percent of the load of a 

conventional round cable of the same conductor size, or that the voltage drop across flat 

conductor cable will be lower than that of 

round cable under the same load. 

TM X-64768 May 16, 1973 

Space Shuttle Rendezvous, Radiation 

and Reentry Analysis Code. Dave M. 

McGlathery. Aero-Astrodynamics Laboratory. N73-30795 

Documented in this report is the development of a preliminary Space Shuttle 

Mission Design and Analysis Tool emphasizing 

versatility, flexibility, and user interaction 

through the use of a relatively small computer 

(IBM-7044). The Space Shuttle Rendezvous, 

Radiation and Reentry Analysis Code is used 

to perform mission and space radiation 

environmental analyses for four typical Space 

Shuttle missions. Included also is a version of 

the proposed Apollo/Soyuz Rendezvous and 

Docking Test Mission. Tangential steering 

circle to circle low-thrust tug orbit raising and 

the effects of the trapped radiation environment on trajectory shaping due to solar 

electric power losses are also features of this 

mission analysis code. 

The computational results include a 

parametric study on single impulse versus 

double impulse deorbiting for relatively low 

Space Shuttle orbits as well as some definitive 

data on the magnetically trapped protons and 

electrons encountered on a particular mission. 

TM X-64769 July 27, 1973 

Sensitivity and Comparison Evaluation of 

Saturn V Liquid Penetrants. G. H. Jones. 

Quality and Reliability Assurance Laboratory. N73-31529 

This report describes a sensitivity and 

comparison evaluation performed oi six 

liquid penetrants that were used on the 

Saturn V vehicle and other space hardware to 

detect surface discontinuities. 

The relationship between penetrant 

materials and crack definition capabilities, the 

optimum penetrant materials evaluation 

method, and the optimum measurement 

methods for crack dimensions were investigated. A unique method of precis developer 

thickness control was envolved, utilizing clear 

radiographic film and a densitometer. 

The method of evaluation included five 

aluminum alloy, 2219-T87, specimens that 

were heated and then quenched in cold water 

to produce cracks. The six penetrants were 

then applied, one at a time, and the crack 

indications were counted and recorded for 

each penetrant for comparison purposes. 

Measurements were made by determining the 

visual crack indications per linear inch and 

then sebtioning the specimens for a metallographic count of the cracks present. This 

method provided a numerical approach for 

assigning a sensitivity index number to the 

penetrants. 

Of the six penetrants evaluated, two 

were not satisfactory (one was not sufficiently sensitive and the other was too 

6 
NASA TECHNICAL MEMORANDUM
 

sensitive, giving false indications). The other 

four were satisfactory with approximately the 

same sensitivity in the range of 78 to 80.5 

percent of total cracks detected. 

TM X-64770 July 1973 

CVT/PCS Phase I Integrated Testing. 

Robert O. McBrayer and Jackie D. 

Steadman. Astronautics Laboratbry. 

N73-31207 

Five breadboard experiments representing three Sortie Lab Experiment disciplines 

were installed in a Payload Carrier Simulator. 

The experimenteis were asked to provide 

approximately ll2 pages engineering data, to 

provide an outline of the experiment protocol, and to simultaneously perform their 

experiments to their protocol for 8 hours per 

day, during the 4V. days of integrated testing. 

A description of the experiments and the 

Payload Carrier Simulator is provided. An 

assessmenf of the experiment interface with 

the Simulator and an assessment of the 

Simulator experiment support systems is 

presented. The results indicate that a hardware integrator for each experiment is 

essential; a crew chief, or mission specialist, 

for systems management and experimenter 

liaison is a vital function; a payload specialist 

is a practical concept for experiment integration and operation; an integration fixture for 

a complex experiment is -required to efficiently integrate the experiment and carrier, 

simultaneous experiment utilization of simulator systems caused unexpected problems in 

meeting individual experiment requirements; 

experimenter traffic inside the dual-floor 

simulator did not hamper experiment operations; and the requirement for zero-g operation will provide a significant design challenge 

for some experiments. 

TM X-64771 April 16, 1973 

Normal Probabilities for Cape Kennedy 

Wind Components - Monthly Reference 

Periods for All Flight Azimuths -

Altitudes 0 to 70 Kilometers. L. W. 

Falls. Aero-Astrodynamics Laboratory. 

N73-30625 

This document replaces Cape Kennedy 

empirical wind component statistics which are 

presently being used for aerospace engineering 

applications that require component wind 

probabilities for various flight azimuths and 

selected altitudes. The normal (Gaussian) 

distribution is presented as an adequate 

statistical model to represent component 

winds at Cape Kennedy. 

Head-, tail-, and crosswind components 

are tabulated for all flight azimuths for 

altitudes from 0 to 70 km by monthly 

.reference periods. Wind components are given 

for 11 selected percentiles ranging from 0.135 

percent to 99.865 percent for each month. 

Results of statistical goodness-of-fit tests 

are presented to verify the use of the 

Gaussian distribution as an adequate model to 

represent component winds at Cape Kennedy, 

Florida. 

TM X-64772 July 26, 1973 

Apollo 17 Heat Flow and Convection 

Experiments Final Data Analyses 

Results. T. C. Bannister, P. G. Grodzka, 

L. W. Spradley, S. V. Bourgeois, R. 0. 

Hedden, and B. R. Facemire. Space 

Sciences Laboratory. N73-31840 

A group of experiments called the 

Apollo 17 Heat Flow and Convection (HFC) 

Experiments was conducted by Astronaut 

7 
NASA TECHNICAL MEMORANDUM
 

Ron Evans on December 8, 1972, aboard the 

Apollo 17 spacecraft while in translunar coast 

on the way to the moon. These experiments 

together with the HFC experiments flown on 

Apollo 14 demonstrated and provided data on 

two types of low-g natural convection: 

cellular, surface tension-driven convection and 

convection in confined fluids caused by 

spacecraft and astronaut movements, 

Observed convection onset times show that 

surface tension-driven convection occurs at 

lower temperature gradients in low-g than in. 

one-g environments. Data on heat flow in 

confined fluids show that spacecraft and 

astronaut movements can cause significant 

degrees of convection, 

TM X-64773 August 10, 1973 

Effects of Ascent Trajectory Mode and 

Tank Disposal Method on Shuttle Payload Accommodation. James C. Blair, 

William W. Heuser, Jerome R. Redus. 

Aero-Astrodynamics Laboratory. 

N73-30831 

The capability of the Space Shuttle to 

deliver payloads of a given weight and length 

to the desired orbital altitude can be 

significantly affected by the trajectories and 

operational modes used for the Shuttle 

mission. This report documents an investigation of how Shuttle payload accommodation capability is affected by (1) external tank 

disposal by retro-rocket versus passive tank 

drop and (2) targeting the main engine burn 

for high apogee (direct insertion) versus the 

baseline parking-orbit ascent method. Missions 

launched from Eastern Test Range were 

investigated over a range of orbit altitudes to 

determine tank disposal requirements including footprint dispersions and alternate impact 

locations, performance, and Orbital Maneuvering System requirements. Passive tank 

drop, which is known to be superior to retro 

disposal from a Shuttle system standpoint, 

somewhat surprisingly proved to be advantageous from a payload accommodation standpoint also. Direct insertion is shown to be a 

means of accommodating long payloads at 

higher altitudes than permitted by the 

baseline ascent method; however, direct insertion required disposal of the tank in the 

Pacific rather than the Indian Ocean. It is 

recommended that direct insertion be c6nsidered a viable Shuttle ascent mode, but 

because of the preferability of Indian Ocean 

disposal and the desire for standardization of 

mission profiles, its use should be restricted 

to those payloads which cannot be accom­

"modated by the baseline ascent inode. 

TM X-64774 August 1973 

Measurement Capabilities of a OneDimensional LDV System. William C. 

Cliff and Charles E_ Fuller, III. AeroAstrodynamics Laboratory. N73-30427 

The capability of a single component 

laser Doppler velocimeter (LDV) system for 

the measurement of three dimensional mean 

and turbulent flow statistics is investigated. 

Sets of general equations defining the parameters measured by a single component LDV 

system are derived. Solutions to the equations 

for different configurations of a single 

forward scatter LDV system show that three 

dimensional mean velocity measurements can 

be made with a minimum restriction on the 

precision for detecting the Doppler frequency. 

Measurements of the three dimensional RMS, 

cross products and correlation parameters are 

shown to require a significantly higher 

precision in the Doppler freqqency detection. 

8 
NASA TECHNICAL MEMORANDUM
 

TM X-64775 August 1973 

A Modified Quadrupole Mass Spectrometer with Custom RF Link Rods Driver 

for Remote Operation. Philip W. 

Tashbar, Daniel B. Nisen, and W. 

Walding Moore, Jr., Space Sciences Laboratory. N73-30435 

A commercial quadrupole residual gas 

analyzer (RGA) system has been upgraded for 

operation at extended cable lengths. Operation inside a vacuum chamber for the 

standard quadrupole nude head is limited to 

approximately 2 m from its externally located 

rf/dc generator because of the detuning of the 

rf oscillator circuits by tie coaxial cable 

reactance. The advance of long distance 

remote operation inside a vacuum chamber 

for distances of 45 and 60 m was made 

possible without altering the quadrupole's 

rf/dc generator circuit by employing an rf 

link to drive the quadrupole rods. Applications of the system have been accomplished 

for in situ space simulation thermal/vacuum 

testing of sophisticated payloads. 

TM X-64776 March 30, 1973 

The V-3 Contamination Test of the 

Chamber A Facility and A Subsequent 

Cryogenic/Vacuum Study of the V-3 

Test Quartz Crystal Microbalance. 

W. Walding Moore, Jr., and Philip W. 

Tashbar. 	Space Sciences Laboratory. 

N73-30220 

The areas of orbital and ground contamination of flight experiment hardware 

have been well established. This report relates 

directly to results of vacuum chamber testing 

for the ground evaluation of flight experiment 

hardware performance. First, the data 

obtained during the V-3 contamination testing 

in the Johnson Space Center's Chamber A 

space simulation test facility are presented. 

Second, during the V-3 contamination test, 

the MSFC Space Sciences Laboratory's quartz 

crystal microbalance exhibited two periods of 

anomalous readings. Therefore, a subsequent 

small chamber test was conducted in a 

controlled cryogenic/vacuum environment. 

The objective was to reproduce with known 

parameters the anomalous behavior patterns 

of the V-3 test data. Analyses of the 

anomalous readings are made on the basis of 

these tests. Additionally, as a by-product of 

the small chamber tests, calibration curves 

then existing for the quartz crystal microbalance were empirically extended, and certain data-formatting aids were documented. 

TM X-64777 August 1, 1973 

Proposed Reliability Cost-Model. 

Dr. Leon M. Delionback. Systems/ 

Products Office. 	 N73-32372 

The research investigations which were 

involved in'this study include: cost analysis/ 

allocation, reliability and product assurance, 

forecasting methodology, systems analysis, 

and model-building. This is a classic example 

of an interdisciplinary problem, since the 

model-building requirements include the need 

for understanding and communication 

between technical disciplines on one hand and 

the financial/accounting skill categories on the 

other. 

The systems approach is utilized within 

this context to establish a clearer and more 

objective relationship between Reliability 

Assurance and the subcategories (or subelements) that provide, or reenforce, the 

9 
NASA TECHNICAL MEMORANDUM
 

reliability assurance for a system. Subcategories are further subdivided as illustrated by 

a tree diagram. The reliability assurance 

elements can be seen to be potential 

alternative -strategies, or approaches, depending on the specific goals/objectives of the 

trade studies. The scope was limited to the 

establishment of a proposed reliability costmodel format. 

The model format/approach is dependent 

upon the use of a series of subsystem-oriented 

CER's, and sometimes possible CTR's, in 

devising a suitable cost-effective policy, 

TM X-64778 June 8, 1973 

Quartz Crystal Microbalance Contamination Monitors on Skylab - A QuickLook Analysis. R. Naumann, W. Moore, 

D. Nisen, W. Russell and P. Tashbar. 

Space Sciences Laboratory. N73-31412 

Six quartz crystal microbalance contamination monitors were flown on Skylab to 

monitor the deposition of material from 

spacecraft outgassing and from the rendezvous 

and docking maneuvers of the Command/ 

Service Module. This report contains a 

quick-look analysis of the data from these 

units during the unmanned and manned 

portions of SL2. 

TM X-64779 September 1973 

Simulation of an Experiment Pointing 

System for the Space Shuttle. P. D. 

Nicaise. Program Development. 

N73-32760 

The pointing and Control of experiments 

during sortie missions are examined from the 

standpoint of accuracy and performance. The 

effect of gimbal characteristics, pallet stiffness, and variation in the servo control loop 

are described. Simulation results are shown 

for a number of pointing options under the 

disturbing influences of man motion, thruster 

firings, and experiment operations. One 

option of particular interest is the suspended 

pallet which offers the possibility of high 

accuracy pointing of very large payloads 

without using conventional gimbals. The 

pallet is suspended within the payload bay by 

non-rigid attachments such as springs, thereby 

isolating experiments from most Shuttle 

disturbances. Control moment gyros apply 

torques directly to the pallet to maintain 

pointing accuracy within the arc second 

range. Spring torques constrain Shuttle attitude so thruster operation is not required. 

The suspended pallet approach will meet the 

base stability requirements of any sortie 

experiment and offers the possibility of a 

standardized low weight, low cost alternative 

to gimbaled mounts. However, the practical 

aspects, including possible implementation 

problems, have not been fully explored. 

-, 

TM X-64780 August 1973 

Optimum Inclination for Shuttle 

Retrieval of Inclination Non-Sensitive 

Satellites. Douglas L. Blackwell. AeroAstrodynamiCs Laboratory. N73-31730 

This report presents the results of a 

study to identify the optimum inclination for 

a satellite when the satellite is inclination 

non-sensitive and is to be' retrieved. This 

inclination is such that it provides an 

opportunity for a retrieval flight at least once 

each day with minimal on-orbit phasing 

requirements and minimal ascent performance 

losses. 

10 
NASA TECHNICAL MEMORANDUM
 

TM X-64781 July 1, 1973 

A Comparison of Digital Computer 

Programs for the Numerical Solution of 

Ordinary Differential Equations. Hugo L. 

Ingram. Aero-Astrodynamics Laboratory. 

N73-32487 

Recently the determination of the best 

technique for numerically solving systems of 

ordinary differential equations on a digital 

computer has received much attention. Phyllis 

Fox in A Comparative Study of Computer 

Programs for Integrating Differential Equations; and Hull, Enright, Fellen, and 

Sedgewick in Comparing Numerical Methods 

for Ordinary Differential Equations made 

studies on the computational efficiency of 

several different numerical integration techniques, but their studies did not include the 

Runge-Kutta formulas developed by Fehlberg 

(NASA TR R-287 and R-3 15). The use of 

these formulas in conjunction with a stepsize 

control developed in this report is explained, 

and one of the formulas is chosen for 

comparison with other integration techniques. 

This comparison of one of the best of 

Fehlberg's formulas with the different numerical techniques described in the aforementioned studies on a variety of test problems 

clearly shows the superiority of Fehlberg's 

formula. That is, on each of the test 

problems, the chosen Fehlberg formula is able 

to achieve a given accuracy in less computer 

time than any of the other techniques tested. 

Also, the computer program for the chosen 

Fehlberg formula is less complex and easier 

to use than the computer programs for most 

of the other techniques. To illustrate the use 

of the chosen Fehlberg formula, a computer 

listing of its application to several example 

problems is included along with a sample of 

the computer output from these applications, 

TM X-64782 June 1974 

Recording and Cataloging Hazards Information. Revision A. Richard J.Stein. 

Safety and Manned Flight Awareness 

Office. N73-31918 

Investigating and reporting of accidents 

is basically a data collection process whose 

purpose is to discern causation factors of 

accidents. These factors, once known, lead, in 

turn, to either the establishment of boundaries or controls aimed at mitigating accident 

effects or eliminating accidents altogether. A 

procedure is herein proposed that suggests a 

discipline approach to hazard identification 

based on energy interrelationships together 

with an integrated control technique which 

takes the form of checklists. 

TM X-64783 September 1973 

Flammability of Materials in Gaseous 

Oxygen Enviornments. C. F. Key, J.G. 

Austin, J.W. Bransford. Astronautics 

Laboratory. N73-33081 

The restilts of evaluation of a wide 

variety of materials and configurations to 

determine their flammability characteristics in 

gaseous oxygen environments are reported. 

The data in this report are compiled to enable 

the designer to select materials applications 

that will meet the flammability requirements 

of MSFC SPEC 101B. 

TM X-64784 September 19, 1973 

Natural Environment Criteria for the 

NASA High Energy Astronomy Observatory (HEAO). Lewis E. Andrews. AeroAstrodynamics Laboratory. N73-33807 

This document provides environment 

criteria for the NASA High Energy 

11 
NASA TECHNICAL MEMORANDUM
 

Astronomy Observatory (HEAO) Program. 

Information in selected disciplinary areas is 

given for the region of space that is within 

1000 km from the earth's surface. This report 

supersedes NASA TM X-64576, "Natural 

Environment Criteria Guidelines for the 

HEAC," dated March 25, 1971. 

TM X-64785 September 18, 1973 

Binary Selectable Detector Holdoff Circuit: Design, Testing, and Application. 

K. A. Kadrmas. Aero-Astrodynamics Laboratory. N74-10501 

A very high speed switching circuit, part 

of a laser radar data acquisition system, has 

been designed and tested. The primary 

function of this circuit was to provide 

computer controlled switching of photodiode 

detector preamplifier power supply voltages, 

typically less than ±20 volts, in approximately 

10 nanoseconds. Thus, in actual use, detector 

and/or detector preamplifier damage can be 

avoided as a result of sudden extremely large 

values of backscattered radiation being 

detected, such as might be due to short range, 

very thin atmospheric dust layers. Switching 

of the power supply voltages was chosen over 

direct switching of the photodoide detector 

input to the preamplifier, based on system 

noise considerations. Also, the circuit provides 

a synchronized trigger pulse output, for 

triggering devices such as the Biomation 

Model 8100 100 MHz analog to digital 

converter. 

A point by point description of the 

circuit operation is presented, with actual 

signal waveforms shown. In addition, printed 

circuit board layouts and a parts listing are 

given to assist implementation of the circuit 

by interested individuals, 

Finally, further applications of this 

device are discussed and summarized. 

TM X-64786 May 23, 1973. 

The Development of a Two-Component 

Force Dynamometer and Tool Control 

System for Dynamic Machine Tool 

Research. Ian Alexander Sutherland. 

Process Engineering Laboratory. 

N73-33371 

The increasing demands for higher production rates necessitate a deeper knowledge 

of the metal cutting process under dynamic 

machining conditions. 

This work describes tie successful development of a tooling system that makes a 

controlled sinusoidal oscillation, simulating a 

dynamic chip removal condition, and measures the machining forces in two mutually 

perpendictular directions without any cross 

sensitivity. 

TM X'64787 September 1973 

A Survey of Integrated Optics with 

Bibliography. Robert B. Owen. Astrionics Laboratory. N73-33641-

A brief survey of the field of integrated 

optics is made. Light coupling into films, 

modulation of light propagating in films, and 

current integrated optics developments and 

devices are discussed. It is concluded that one 

can expect integrated optics technologyJ to 

revolutionize the electronics industry as cornpletely as did microcircuit technology. An 

extensive bibliography for the field of integrated optics is included in this reporr. 

12 
NASA TECHNICAL MEMORANDUM
 

TM X-64788 October 1973 

ATM C&D Panel/EREP Cooling System 

Contamination Problem. James G. 

Williamson. Astronautics Laboratory. 

N74-10792 

This report presents the history of a 

preflight contamination problem that 

occurred in the ATM C&D Panel/EREP 

Cooling System on the Skylab, the studies 

that were made by the Materials Division to 

determine the cause of the problem, and 

corrective actions that were made prior to 

lift-off. 

The results of all the observations, 

analyses and laboratory testing indicated that 

the contamination came from one or more of 

the EREP Tape Recorder coldplates and was 

caused by some abnormal electrolytic action, 

either during bench testing or in the spacecraft. Studies indicate that no such electrolytic action is likely to occur under normal 

operating conditions. 

TM X-64789 July 1973 

Design Guidelines for Use of Adhesives 

in Hybrid Microcircuits. Salvadore V. 

Caruso, K. L. Perkins, and J. J. Licari. 

Astrionics Laboratory. N74-10226 

Although it is generally accepted that 

the use of adhesives in the assembly of hybrid 

microcircuits offers advantages over other 

bonding methods, there currently does not 

exist a set of guidelines for the selection of 

adhesives which will insure that hybrid 

microcircuits assembled with them will meet 

the long use-life, high-reliability requirements 

of electronic :equipment for space applications. This study was directed to the 

identification of the properties of electrically 

insulative adhesives that potentially could 

cause problems in such an application, and to 

the development of evaluation tests to 

quantify these properties and thus form the 

basis for establishing suitable guidelines and, 

ultimately, specifications. Bond strength, 

outgassing after cure, and corrosivity were 

selected for detailed attention since they are 

considered to be especially critical. 

Introductory discussion includes enumeration and brief coiiments on the properties of adhesives considered to be important 

for the proposed application, a general review 

of polymeric types of adhesives, and identification of the major types of adhesives 

commercially available and specifically 

designed for microelectronic use. The specific 

tests developed to evaluate bond strength, 

outgassing after cure, and corrosivity are 

discussed in detail, and comparative results 

obtained for selected adhesives representative 

of the major types are given. 

TM X-64790 August 24, 1973 

A Reactive Torque Control Law for 

Gyroscopically Controlled Space 

Vehicles. John E. Farmer. Astrionics 

Laboratory. N74-10419 

This report develops a method of control 

based on the reactive torques as seen by the 

individual CMG gimbals. The application of a 

torque to the gimbal of a CMG rotates the 

momentum vector and applies a' torque to the 

spacecraft according to well-known laws. The 

response (rotation) of the vehicle produces a 

reverse or reaction torque opposing the 

torque producing the gimbal movement. The 

reactive torque and the pseudoinverse control 

schemes are contrasted in order to point out 

the simplicity of the first method. Simulation 

was performed only to the extent necessary 

to prove that reactive torque stabilization and 

control is feasible. 

13 
NASA TECHNICAL MEMORANDUM
 

TM X-64791 November 1973 

Low Temperature Mechanical Properties, 

Fractographic & Metallographic Evaluation of Several Alloy Steels. J. W. 

Montano. Astronautics Laboratory. 

N74-10530 

This report presents the mechanical 

properties of alloy steels, 4130, 4140, 4340, 

6150, and 8740. Test specimens were manufactured from approximately 1.00 inch (2.54 

cm) diameter bar stock which had been heat 

treated to two different hardness levels, 

(Rockwell C-30 and Rockwell C-40). 

The following mechanical tests were 

performed at temperatures of 800 F 

(+26.7 0C),, 00F (-17.8°C), -100 0 F (-73°), 

and -200'F (-129°C): 

1. Tensile test (Ultimate yield, modulus, elongation, and reduction of area) 

2. Notched Tensile Test 

3. Charpy V-Notched Impact Test 

(Impact Energy) 

4. Double Shear Strength Test 

(Ultimate and Yield). 

The test data indicate excellent tensile 

strength, notched/unnotched tensile ratios, 

ductility, impact, and shear properties at all 

test temperatures, except at -2000 F (-1290 C) 

where the impact strength of the higher 

strength group of alloy steels, 4130 (Rc-37) 

and 4140 (Rc-44) decreased to approximately 

9 ft-lb (12 joules) and 6 ft-lb (8 joules), 

respectively, 

Chemical, metallographic, and fractographic analyses were also performed to 

evaluate microstructure, microhardness andthe effect of decrease in temperature on the 

ductile to brittle failure transition, 

14 

TM X-64792 November 1973 

A Survey of Mass Analyzers. W. Walding 

Moore, Jr., and Philip W. Tashbar. Space 

Sciences Laboratory. N74-11289 

With the increasing applications of mass 

spectrometry technology to diverse services 

areas, a need has developed for a consolidated 

survey of the essential characteristics and 

features of the various instruments and 

techniques. This report is one approach to 

satisfying this need. Information has been 

collected and consolidated into a format 

which includes for each approach: (1) a 

general technique description, (2) instrument 

features information, and (3) a summary of 

pertinent advantages and disadvantages. With 

this information, the potential mass spectrometer user should be able to more efficiently 

select the most appropriate instrument. 

TM X-64793 December 6, 1973 

A Brief Description of an Earth 

Resources Technology Satellite (ERTS) 

Computer Data Analysis and Management Program. Robert 'R. Jayroe, Jr. 

Aero-Astrodynamics Laboratory. 

N74-12165 

This report describes a data analysis and 

management procedure currently being used 

at Marshall Space Flight Center to analyze 

ERTS digital data. The objective of the report 

is to acquaint potential users with the various 

computer programs that are available for 

analysis of multispectral digital imagery and 

to show how these programs are used in the 

overall data management plan.. The report 

contains a brief description of each computer 

routine, and references are provided for 

obtaining more detailed information. 
NASA TECHNICAL MEMORANDUM
 

TM X-64794 - October 15, 1973 

Column Densities Resulting From 

Shuttle SublimatorlEvaporator Operation. Robert J. Naumann. Space Sciences 

Laboratory. N74-11848 

The proposed disposal of H20 from the 

Shuttle fuel cell operation by ejecting it in 

vapor form thr6ugh a supersonic nozzle at the 

rate of 100 lb/day has been investigated from 

the point of view of the possible interference 

to astronomical experiments. If the nozzle is 

located at the tail and directed along the 

Shuttle longitudinal axis, the resulting column 

density will be less than 101 1 molecules/cm2 

at viewing angles larger than 48 deg above the 

longitudinal axis. The molecules in the trail 

will diffuse rapidly. The column density 

contribution from molecules expelled on the 

previous orbit is 1.3 X 108 molecules/cm 2 . 

This contribution diminishes by the inverse 

square root of the number of orbits since the 

molecules were expelled. Summing the contributions from each orbit over a 30-day 

mission results in a maximum column density 

of 5 X 109..molecules/cm 2 along a perpendicular to the flight path. The maximum return 

flux from water molecule buildup along the 

flight path is 2.2 X 109 molecules/cm2 /sec at 

the stagnation point. 

The molecular backscatter from atmospheric molecules is also calculated. If the 

plume is directed into the flight path, the 

column density along a perpendicular is found 

to be 1.5 X 101' molecules/cm 2 . The return 

flux is estimated to be of the order of 1012 

molecules/cm 2 /sec at the stagnation point. 

With reasonable care in design of experiments 

to protect them from the backscatter flux of 

water molecules, the expulsion of 100 lb/day 

does not appear to create an insurmountable 

difficulty for the Shuttle experiments, 

TM X-64795 November 19, 1973 

Distributions of Eight Meteorological 

Variables at Cape Kennedy, Florida and 

Vandenberg Air Force Base, California. 

M. E. Graves, R. L. King and S. Clark 

Brown. 	 Aero-Astrodynamics Laboratory. 

N74-13325 

Extreme values, median values, and nine 

percentile values are tabulated for eight 

meteorological variables at Cape Kennedy, 

Florida and at Vandenberg Air Force Base, 

California. The variables are temperature, dew 

point temperature, relative humidity, station 

pressure, water vapor pressure, water vapor 

mixing ratio, density, and enthalpy. For each 

month eight hours are tabulated, namely, 

0100, 0400, 0700, 1000, 1300, 1600, 1900, 

and 2200 local time. These statistics are 

intended for general use for the Space Shuttle 

design trade-off analysis and are not to be 

used for specific design values, Appropriate 

documents, e.g., Appendix 10.10, Volume X, 

Space Shuttle Design Requirements, JSC Doc. 

No. 07700 and NASA TM X-64757 shall be 

used for specific natural design requirements 

data for the Space Shuttle, 

TM X-64796 December 5, 1973 

Summary

tions for 

of Atmospheric Data Observa155 Flights of MSFC/ABMA 

Related Aerospace Vehicles. D. L. 

Johnson. Aero-Astrodynamics Laboratory. N74-13312 

A summary of selected atmospheric 

conditions observed near launch time for 155 

NASA-Marshall Space Flight Center and Army 

Ballistic Missile Agency related vehicles, 

launched primarily from Cape Kennedy, 

Florida, between August 20, 1953, and 

November 16, 1973, is presented. Values of 

ambient pressure, temperature, relative 

15 
NASA TECHNICAL MEMORANDUM
 

humidity, ground winds, visual observations, 

density aloft, and wind/wind shear aloft are 

included. The extremes of these parameters 

are listed for each type of launch vehicle, 

This summary of atmospheric conditions 

at launch for the various vehicles is not meant 

to imply that this is the range of atmospheric 

conditions which may occur at the launch 

site. These were basically R and D type 

vehicles and an "operational" deployed 

vehicle might encounter a larger range (variation) of atmospheric conditions, It should be 

noted that the atmospheric conditions at 

launch for these vehicles were closely monitored during the prelaunch period. Adverse 

weather conditions were deliberately avoided 

based on trend indications, prediction of 

probably T-0 conditions and real time measurements. 

This report supersedes "Selected Atmospheric Observations for 101 Consecutive 

Flight Tests of the Redstone, Jupiter and 

Pershing Missiles," NASA MTP-AERO-60-14, 

December 19, 1960. 

TM X-64797 December 26, 1973 

Metabolic Analyzer. Cortes L. Perry. 

Astronautics Laboratory. N74-13819 

This is a description of an apparatus for 

the measurement of metabolic rate and 

breathing dynamics in which inhaled and 

exhaled breath are sensed by sealed, pistondisplacement type spirometers. These spirometers electrically measure the volume of 

inhaled and exhaled breath. A mass spectrometer analyzes simultaneously for oxygen, 

carbon dioxide, nitrogen and water vapor, 

Computation circuits responsive to the 

outputs of the spirometers, mass spectrometer, temperature, pressure and timing signals 

compute oxygen consumption, carbon dioxide 

production, minute volume and respiratory 

exchange ratio. A selective indicator provides 

for read-out of these data at predetermined 

cyclic intervals. The metabolic analyzer, as 

herein described, is being patented with the 

author and Dr. John A. Rummel, E.wvironmental Physiology Laboratory, Johnson Space 

Center as co-inventors. The system has had 

successful operation during the Skylab 

missions both on the ground and in flight as 

part of Skylab Biomedical Experiment M-171, 

Mr. Edward Michel, of Johnson Space Center, 

principal investigator. 

TM X-64798 January 1974 

The October 1973 NASA Mission Model 

Analysis and Economic Assessment. 

Program Development. N74-15507 

This document presefits the results of 

the 1973 NASA Mission Model Analysis 

performed by Program Development. Marshall 

Space Flight Center, under the direction of 

the Mission and Payload Integration Office of 

NASA Headquarters. The purpose of this 

analysis was' to, obtain an econo'mic assessment of using the Shuttle to accommodate 

the payloads and requirements as identified 

by the NASA Program Offices and the DoD. 

The 1973 Payload Model represents a 

baseline candidate set of future payloads 

which can be used as a reference base for 

planning purposes. The cost of implementing 

these payload programs utilizing the capabilities of the Shuttle system is analyzed and 

compared with the cost of conducting the 

same payload effort using expendable launch 

vehicles. 

16 
NASA TECHNICAL MEMORANDUM
 

There is a net benefit of 14.1 billion 

dollars as a result of using the Shuttle during 

the 12-year period as comp2red to using an 

expendable launch vehicle fleet. 

TM X-64799 January 18, 1974 

A Guide for Performing System Safety 

Analysis. J. M. Brush, R. W. Douglass Ill, 

and F. R. Williamson. Martin C. Dorman, 

ed. Systems/Products Office. N74-14689 

This document is a general guide for 

performing system safety analyses of hardware, software, operations and human elements of an aerospace program. The guide 

describes a progression of activities that can 

be effectively applied to identify hazards to 

personnel and equipment during all periods of 

system development. 

This document describes the general 

process of performing safety analyses; setting 

forth in a logical order the information and 

data requirements, the analytical steps and 

the results. These analyses are the technical 

basis of a system safety program. Although 

the guidance established by this document 

cannot replace human experience and judgement, it does provide a methodical approach 

to the identification of hazards and evaluation 

of risks to the system. 

TM X-64800 December 12, 1973 

Double Scattering Corrections for the 

Theory of the 'Sun's Aureole. Adarsh 

Deepak. Aero-Astrodynamics Laboratory. 

N74-14497 

Double scattering corrections for aureole 

radiances are calculated by adding the effects 

of two successive single scatterings. Atmospheric absorption, polarization, and variation 

of refractive index with altitude are ignored. 

Corrections due to spherical atmosphere have 

been taken into account by the use of a 

generalized Chapman function. Realistic 

scattering phase functions based upon the 

Lorenz-Mie theory and model altitude-size 

distribution are used. The model distribution 

is assumed to be representable in terms of 

two separable particulate components. We 

find that for a moderately clear day, -(O) 

0.5, and for forward scattering angles, the 

Radiance, B2 , due to double scattering is less 

than 6 percent 

scattering. 

of that due to single 

TM X-64801 

Notes for the 

January 23, 

Improvement of 

1974 

the 

Spatial and Spectral Data Classification 

Method. Charles C. Dalton. AeroAstrodynamics Laboratory. N74-15058 

This report examines the "Spatial and 

Spectral Clustering" technique for the unsupervised automatic classification and mapping 

of earth resources satellite data, and makes 

theoretical analysis of the decision rules and 

tests in order to suggest how the method 

might best be applied to other flight data 

such as Skylab and Spacelab. 

TM X-64802 January 1974 

The October 1973 NASA Mission Model 

Cost and Economic Analysis. Program 

Development. X74-71302 

This document presents the cost and 

economic results of The October 1973 NASA 

Mission Model Cost and Economic Analysis 

performed by the Program Development 

Directorate, Marshall Space Flight Center, 

under the direction of the mission and 

Payload Integration Office of NASA 

17 
NASA TECHNICAL MEMORANDUM
 

Headquarters. The purpose of this analysis 

was to obtain an economic assessment of 

using the Shuttle to accommodate the 

payloads and tequirements as identified by 

the NASA Program Offices and the DoD. 

The 1973 Payload Model represents a 

baseline candidate set of future payloads 

which can be used as a reference base for 

planning purposes. The cost of implementing 

these payload programs utilizing the capabil-

.ities of the Shuttle system is analyzed and 

compared with the cost of conducting the 

same payload effort using Expendable Launch 

Vehicles. 

There is a net benefit of $14.1 billion as 

a result of using Shuttle during the 12-year 

period as compared to using an Expendable 

Launch Vehicle fleet. 

TM,X-64803 February 12, 1974 

Remote Sensing in Agriculture. Sanford 

W. Downs, Jr. Astrionics Laboratory. 

N74-18040 

The purpose of this report-is to show 

some examples of the use of remote sensing 

in cultivated crops, forestry, and range 

management. It is not the intent to show all 

the uses of remote sensing, but rather to 

illustrate what can be done and is being done 

in a few selected, areas. These are the 

determination of crop areas and types, 

prediction of yield, and detection of disease; 

the determination of forest areas and types, 

timber volume estimation, detection of insect 

and disease attack, and forest fires; and the 

determination of range conditions and inventory, and livestock inventory. This is done bysummarizing articles in the literature and 

giving specific examples of work being 

performed at the Marshall Space Flight 

Center. No attempt has been made to provide 

an extensive bibliography. Although remote 

sensing includes photography, radar, infrared 

scanners, television, and passive microwave 

receivers, this report is confined primarily to 

aerial photographs 

images. 

and photo-like ERTS 

TM X-64804 

Diffusion from a 

November 16, 1973 

Line Source. Rowland 

E. Burns. Aero-Astrodynamics Laboratory. N74-17333 

The problem with predicting pollutant 

diffusion from a line source of arbitrary 

geometry is treated. The concentration at the 

line source'may be arbitrarily 'varied with 

time. Special attention is given to the 

meteorological inputs which act as boundary 

conditions for the problem, and a mixing 

layer of arbitrary depth is assumed. Numerical 

application of the derived theory indicates the 

combinations of meteorological parameters 

that may be expected to result in high 

pollution concentrations. 

TM X-64805 February 13, 1974 

Conceptual Design of the Scientific 

Instrument Arrangement for the Large 

Space Telescope. J. Zurasky and 

D. 	Korsch. Astrionics Laboratory. 

N74-16112 

This report documents the work of the 

Astrionics Laboratory, Technology and Fleetromechanical Engineering Divisions (S&EASTR-R and M), at the Marshall Space Flight 

Center in support of the Large Space 

Telescope Working Group (LSTWG). A 

18 
NASA TECHNICAL MEMORANDUM
 

description of the Scientific Instrument 

arrangement for the Large Space Telescope 

(LST) is given, with some of the rationale for 

selecting this concept. The first section of this 

report, entitled Initial Design, describes the 

basic configuration and was designed for an 

f/20 telescope focal plane. The subsequent 

LSTWG meeting held in November gave some 

redirection to the scientific requirements, and 

these changes are described in the section, 

Configuration Update. 

TM X-64806 February 14, 1974 

Large Space Telescope (LST) Pointing 

Control System (PCS) Analytical 

Advanced Technical Development (ATD) 

Program. Sherman M. Seltzer. Astrionics 

Laboratory. N74-17165 

The purpose of this memorandum is to 

describe the Large Space Telescope (LST) 

Pointing Control System (PCS) Advanced 

Technical Development (ATD) program. The 

approach used is to describe the overall PCS 

development effort, showing how the analytical ATD program elements fit into it. Then 

the analytical ATD program elements are 

summarized (although alluded to summarily 

in the introduction and several times in the 

body of this memorandum, the hardware 

development portion of the ATD program is 

omitted). If only the list of ATD program 

elements were presented and described, the 

program would appear disjointed. However, 

by showing how these program elements fit 

into the overall PCS development effort, their 

connection to the program and their purpose 

is then evident, 

TM X-64807 February 14, 1974 

Development of Coatings to Control 

Electroosmosis in Zero Gravity Electrophoresis. A. C Krupnick. Astronautics 

Laboratory. N74-18196 

A major problem confronting the operation of free fluid electrophoresis in zero 

gravity is the control of eleetrokinetic 

phenomena and, in particular, electroosmosis. 

Due to the severity of counter flow, as a 

result of electroosmosis, the electrical potential (" potential) developed at the surface of 

shear must be maintained at near, or close to, 

zero millivolts as possible. Based upon this 

investigation, it has been found that the 

,nount of bound water or the degree of 

hydroxylation plays a major role in the 

control of this phenomena. Of necessity, 

factors, e.g. adhesion, biocompatibility, 

protein adsorption, and insolubility were 

considered in this investigation because of the 

long buffer-coating exposure times required 

by present space operations. Based upon tests 

employing microcapillary electrophoresis, it 

has been found that y amino propyl trihydroxysilane produced a coating which provides the lowest potential (-3.86 my) at the 

surface of shear between the stationary and 

mobile layers. This coating has been soaked in 

both borate and saline buffers, up to three 

months, in a pH range of 6.5 to 10 without 

deleterious effects or a change in its ability to 

control electrokinetic effects. 

TM X-64810 April 1974 

MSFC'Skylab Airlock Module. Skylab 

Program Office. 

Vol. I N74-26321 

Vol. II N74-26338 

This report presents the history and 

development of the Skylab Airlock Module 

and the Payload Shroud, NASA Contract No. 

NAS9-6555, from initial concept through 

final design, related test programs, mission 

performance and lessons learned. 

Although some problems were 

encountered, the Airlock Module performed 

19 
NASA TECHNICAL MEMORANDUM
 

successfully throughout the three manned 

Skylab missions. 

TM X-64812 April 1974 

MSFC Skylab Multiple Docking Adapter. 

Skylab Program Office. 

Vol. 1 N74-26328 

Vol. II N74-26329 

This report presents the history of the 

development of the Skylab Multiple Docking 

Adapter (MDA), NASA Contract No. NAS8-

24000, from initial concept through its final 

design, related test programs, mission performance, and lessons learned, 

The MDA performed with no significant 

problems throughout the three manned 

Skylab missions, 

TM X-64813 May 1974 

MSFC Skylab Orbital Workshop. Skylab 

Program Office. 

Vol. I N74-28328 

Vol. II N74-28329
 

Vol. III N74-28330 


Vol. IV N74-28331 


Vol. V N74-28332 


This report documents and summarizes 

the results of the Orbital Workshop technical 

contract including development, verification, 

mission performance, and conclusions based 

on program results and experience. The report 

is published in five (5) volumes. 

TM X-64815 June 28, 1974 

MSFC Skylab Apollo Telescope Mount 

Summary Mission Report. A. R. Morse. 

Skylab Program Office. N74-28311 

This report presents a summary of the 

Apollo Telescope Mount (ATM) performance 

during the 8.3-month Skylab mission. The 

report contains a brief description of each 

ATM system, system performance summaries, 

discussion of all significant ATM anomalies 

which occurred during the Skylab mission, 

and, in an appendix, a summary of the 

Skylab ATM Calibration Rocket Project 

(CALROC). The text -is supplemented and 

amplified by photographs, drawings, curves, 

and tables. 

The report shows that the ATMI not only 

met, but exceeded premission performance 

criteria, and that participation of Man in 

space for this scientific investigation greatly 

enhanced the quality and quantity of the data 

attained. 

TM X-64816. March 1974 

MSFC Skylab Mission Sequence Evaluation. J. D. Hoverkamp. Skylab Program 

Office. N74-28317 

Planned and actual major Skylab 

sequences are presented. Off-nominal events 

are highlighted. Differences between planned 

and actual events are discussed. 

TM X-64817 July 1974 

MSFC Skylab APCS Mission Evaluation. 

W. B. Chubb. Skylab Program Offide. 

This report offers the results of detailed 

performance analyses for all Attitude and 

Pointing Control System in-orbit hardware 

and software. Performance is compared with, 

requirements, test results, and prelaunch 

predictions. 

20 
NASA TECHNICAL MEMORANDUM
 

A brief history of the Attitude and communication, generating rendezvous ranging 

Pointing Control System evolution leading to information and radio frequency transmission 

the launch configuration is presented. This and reception. 

historical information, as well as a brief 

physical description of the' launch configura- A brief history of the system evolution 

tion, is included as an aid to a clear based on the functional. requirements along 

understanding of mission performance. with a physical description of the launch 

configuration is included as an aid to a clear 

In conclusion, the report asserts that the understanding of the System performance. 

Attitude Pointing and Control System satisfied all imposed requirements. Conclusions In conclusion, the report affirms that the 

based upon flight data analysis offer insights Instrumentation and Communication Systems 

which may be beneficial during early concept satisfied all imposed requirements.. Recomand design requirement stages of future mendations are offered which may be benespacecraft systems. ficial to future space programs. 

TM X-64818 June 1974 TM X-64821 June 2974 

MSFC Skylab Electrical Power Systems MSFC Skylab Apollo Telescope Mount 

Mission Evaluation. A. P. Woosley. Experiment Systems Mission Evaluation. 

Skylab Program Office. A. F. . White, Jr. ATM Experiments 

Branch. N74-28318 

Planned and actual major Electrical and 

Caution and Warning Performance is pre- This report presents a detailed evaluation 

sented. Off-nominal events are highlighted, of the Skylab Apollo Telescope Mount (ATM) 

Differences between planned and actual experiments performance throughout the 

events are discussed. eight and one-half month Skylab Mission. 

Descriptions and the objectives of each 

TM X-64819 June 1974 instrument are included. Also included is a 

MSFC Skylab Instrumentation and Corn- discussion of the anomalies experienced, the 

munication System Mission Evaluation. causes, and corrective actions taken. ConB. M. Adair. Skylab Program Office. clusions, based on evaluation of the performance of each instrument, are presented. This report presents an evaluation of the Examples of the scientific data obtained, as 

in-orbit performance of the Instrumentation well as a discussion of the quality and 

and Communications Systems. Performance is quantity of the data, are presented. This 

compared with functional requirements and report shows that the ATM instruments, 

the fidelity of communications, individually larger and more complex than 

any previous instruments flown on satellites, 

In-orbit performance includes processing surpassed all performance expectations. In 

engineering, scientific, experiment, and many cases the instruments greatly exceeded 

biomedical data, implementing ground- their design operating life. The patial resolugenerated commands, audio and video tion of each instrument was an order of 

21 
NASA TECHNICAL MEMORANDUM
 

magnitude better than any similar instrument 

flown on previous satellites. This report also 

shows that, as never before, it was possible to 

simultaneously collect multispectral data of 

specific solar phenomena. This report clearly 

demonstrates the major advantage of Man to 

point the instruments precisely at small 

targets and immediately react to unpredictable events. As .a result of the data 

obtained by the ATM instruments, many 

theories of solar physics will undergo significant revisions. 

TM X-64826 May 1974 

MSFC Skylab Contamination Control 

Systems Mission Evaluation. Skylab 

Program Office. N74-26335 

Cluster external contamination control 

evaluation was made throughout the Skylab 

Mission. This evaluation indicated that contamination control measures instigated during 

the design, development, and operational 

phases of this program were adequate to 

reduce the general contamination environment 

external to the Cluster below the threshold 

sensitivity levels for experiments and affected 

subsystems specified by Principal Investigators 

(Pis) and Technical Discipline Managers 

(TDMs) except for anomalous conditions. 

Launch and orbit contamination control 

features included eliminating certain vents, 

rerouting vents for minimum contamination 

impact, establishing filters, incorporating 

materials with, minimum outgassing characteristics and developing operational constraints and mission rules to minimize contamination effects. 

Prior to the launch of Skylab, contamination control math models were 

developed which were used to predict Cluster 

surface deposition and background brightness 

levels throughout the mission. 

The rdport summarizes the Skylab systern and experiment contamination control 

evaluation. The Cluster systems and experiments evaluated include Induced Atmosphere, 

Corollary and ATM Experiments, Thermal 

Control Surfaces, Solar Array Systems, 

Windows, and Star Tracker. 

TM X-64827 March 1974 

Spacelab Phase B Study Environmental 

Control System Component Handbook. 

R. A. Bums and A. J. Ignatonis. Astronautics Laboratory. N74-18512 

This document contains descriptions of 

candidate components for the Phase B Study 

of the Spacelab Environmental Control Systern. Most of the hardware was defined for 

the baseline ECS design concept. A low cost 

design approach was followed, with most of 

the components being selected from the 

Apollo and Skylab Programs. 

TM X-64828 February 14, 1974 

Spacelab Soft Mockup Comparative 

Evaluation. Harry Watters. Astronautics 

Laboratory. N74-20537 

An' assessment of two proposed Spacelab 

configurations with diameters of 14 and 12 

feet was conducted by using two inexpensive 

wooden mockups containing cardboard fixtures. Also examined was an alternate mounting arrangement for the 12-foot diameter 

configuration, taking advantage of conforming 

equipment racks to the cylinder walls. A 

volume comparison of the three configurations was made using a life sciences payload 

which is considered to be one of the more 

voluminous payloads. As a- result of the 

22 
NASA TECHNICAL MEMORANDUM
 

study, it was found that crew volume in the machining variables, such as feed and depth12-foot baseline configuration appeared of-cut, and can lead to another machining 

marginal for the life sciences payload, espe- problem - namely, machine tool instability ­

cially where crewmen were engaged, in more commonly known as chatter. 

activities with competing demands. It was also 

found that the 12-foot configurations of life The object of this work is to acquaint 

sciences payloads offered little margin for the reader. with these problems, to examine 

stowage or equipment growth. Increased the variables that may 'be encountered when 

demands would necessitate longer module machining a material like titanium, 'and to 

lengths. Similar results could be expected advise the machine tool user on how to 

with other large volume payloads. maximize the output from the machines and 

tooling available to him. 

TM X-64829 March 1974 

A Solution to the Problem of Optimizing Recommendations are made on ways of 

the Fuel Bias for a Liquid Propellant improving machining tolerances, reducing 

Rocket by an Application of the Central machine tool. instability or chatter, and 

Limit Theorem. William Viera, Jr. Astro- improving productivity. New tool materials, 

nautics Laboratory. N74-18393 tool coatings, and coolants are reviewed and 

their relevance examined when machining 

- This paper presents an accurate and titanium. 

efficient method of determining the fuel bias 

for a bipropellant liquid rocket that mini- Finally this report can be used as a guide 

mizes outage associated penalties on payload to the reader who is interested in setting up a 

potential. A fuel bias so derived is normally program of machine tool research. 

called "the optimum fuel bias." 

TM X-64831 December 1973 

TM X-64830 January 1974 The George C. Marshall Space Flight 

An Investigation of Chatter and Tool Center High Reynolds Number Wind 

Wear When Machining Titanium. ]an A. Tunnel Technical Handbook. H. S. Gwin. 

Sutherland. Process Engineering Labora- Aero-Astrodynamics Laboratory. 

tory. N74-18130 N74-19890 

The low thermal conductivity of tita- This report is a description of the High 

nium, together with the low contact area Reynolds Number Wind Tunnel at the George 

between chip and tool and the unusually high C. Marshall Space Flight Center and is a 

chip velocities, gives rise to high tool tip handbook for the potential user who may not 

temperatures and accelerated tool wear. be familiar with its operation. ,The following 

Machining speeds have to .be considerably items are presented to illustrate the operation 

reduced to avoid these high temperatures with and capabilities of the facility: facility 

a consequential loss of productivity. Restoring description and specifications, operational and 

this lost productivity involves increasing other performance characteristics, model design 

23 
NASA TECHNICAL MEMORANDUM
 

criteria, instrumentation and data recording 

equipment, data processing and presentation, 

and preliminary test information required. 

TM X-64832 March 1974 

MSFC Sortie Lab Environmental Control 

System (ECS) Phase B Design Study 

Results. A. J. Ignatonis and K. L. 

Mitchell. Astronautics Laboratory. 

N74-20545 

Phase B effort of the Sortie Lab program 

has been concluded. Included herein are the 

results of that effort which pertains to the 

definitions of the environmental control 

system (ECS). Numerous design studies were 

performed in Phase B to investigate system 

feasibility, complexity, weight, and cost. The 

results and methods employed for these 

design studies are included, 

The study has resulted in an autonomous 

Sortie Lab ECS, utilizing a deployed space 

radiator. Total system weight was projected 

to be 1814.4 kg (4000 lbs) including the 

radiator and fluids. ECS power requirements 

were estimated at 950 watts. 

-TM X-64833 February 21,1974 

CMG-Induced LST Dynamics. Sherman 

M:-Seltzer. Astrionics Laboratory. 

N74-221 10 

The nature of the control moment 

gyroscope (CMG) output gimbal bearing 

friction has been the subject of many 

discussions and presentations by various 

investigators. It is important to know the 

precise nature of the torque caused by the 

bearing friction so that its effect on the 

dynamic behavior of the Large Space 

Telescope (LST) and its pointing and control 

system (PCS) can be predicted. The objective 

of the analysis and supporting computer 

simulations reported herein is to study the 

effect of the assumed CMG nonlinearity upon 

the system dynamics in order to develop an 

understanding of the nature and effect of 

variations of numerical values of parameters 

upon the system. The weakness, of the 

mathematical analysis used results from the 

need to restrict the complexity of the model 

studied; however, the design insight obtained 

is valuable. The importance of mathematical 

analysis as a supplement to computer simulations is stressed. Reference is made to several 

current examples where sole reliance on 

computer simulation has led to erroneous 

conclusions. For one particular LST model, 

several digital simulation efforts reported led 

to the erroneous conclusion that vehicle 

dynamics were resulting in limit cycle 

behavior. 

TM X-64834 February 1974 

Auger Measurements on T-027 Samples 

Exposed During the Skylab 2 Mission. 

Palmer N. Peters. Space Sciences Lab­

,oratory. N74-21362 

Auger electron spectroscopy measurements performed op samples flown on Skylab 

2 indicate a low rate of deposition of 

permanent, continuous-film contamination on 

nickel and gold surfaces positioned on the 

antisolar side of the spacecraft. These measurements and supportive evidence indicate 

that for the particular locations and, orientations of these samples permanent films of less 

than 3 nm (30 A) thickness were deposited 

during an exposure of 40 hours at a 

temperature of approximately -32 0 C. 

24 
NASA TECHNICAL MEMORANDUM
 

TM X-64835 March 1974 

Skylab IlIl and IV Science Demonstrations Preliminary Report. Tommy C. 

Bannister. Space Sciences Laboratory. 

N74-22488 

Twelve Marshall Space Flight science 

demonstrations were accomplished on the 

Skylab III and IV missions. These were 

defined in response to crew requests for 

time-gap fillers and were designed to be 

accomplished using onboard equipment. Nine 

of these demonstrations were in the area of 

materials science and space processing. The 

following 12 are described and the preliminary results are given: 

Skylab 1II: Diffusion in Liquids (No 

number), Ice Melting (No number). 

Skylab IV: Liquid Floating Zone 

(TV 101), Immiscible Liquids (TV 102), 

Liquid Films (TV 103), Gyroscope (TV 104), 

Rochelle Salt Growth (TV 105), Deposition 

of Silver Crystals (TV 106), Fluid Mechanics 

Series (TV 107), Neutron Environment 

(TV 108), Orbital Mechanics (TV 110), 

Charged Particle Mobility (TV 117). 

TM X-64836 November 1973 

Asymptotic Solution to the Tangential 

Low Thrust Energy Increase Trajectory. 

Klaus J. Schwenzfeger. AeroAstrodynamics Laboratory. N74-21433 

An approximate analytic solution to the 

low-thrust constant acceleration energy 

increase trajectory using a tangential steering 

program is presented. The solution is based 

on a two-variable asymptotic expansion of the 

equations of motion formulated in regularized 

variables. The high accuracy of the second 

order solution derived is demonstrated by 

comparing it with numerically integrated 

trajectories. 

TMX-64837 April 1974 

Stress Corrosion Cracking Susceptibility 

of 18 Ni Maraging Steel. T. S. Humphries 

and Eli E. Nelson. Astronautics Laboratory. N74-21136 

The stress corrosion cracking (SCC) 

resistance of 18 Ni maraging steel (grades 

200, 250, 300, and 350) has been determined 

in 3.5 percent salt (NaC1) solution, synthetic 

sea water, high humidity, and outside MSFC 

atmosphere. All grades of the maraging steel 

were found to be susceptible to SCC in 

varying degrees according to their strengths, 

with the lowest strength steel (grade 200) 

being the least susceptible and the highest 

strength steel (grade 350), the most susceptible to SCC. 

The SCC resistance of 250 grade 

maraging steel was also evaluated in salt and 

salt-chromate solutions using fracture 

mechanics techniques. The threshold value, 

KISCC, was found to be approximately 44 

MN/m 2 'V-m (40 ksiyn.) or 40 percent of the 

KQ value. 

TM X-64838 February 21, 1974 

A Stokes' Velocity Photographic Method 

for Measuring the Size Distribution of 

Aerosols. Adarsh De~pak. AeroAstrodynamics Laboratory. N74-22344' 

Aerosol particles are allowed to settle in 

a vertical glass-walled vessel, and their settling 

velocity is determined by photographing them 

25 
NASA TECHNICAL MEMORANDUM
 

while the light entering the camera is being 

chopped at a known rate. The settling 

velocity (Vs) of each particle can be determined from the photographs, and by applying 

the Stokes' law, one can calculate the radius 

(r) of each particle. The Stokes' law for a 

sphere (specific gravity pp) settling freely in a 

quiet medium (specific gravity pm and viscosity 77m ) is given by the relation, v. = 

r2 /9 2(pp - pm) g 77m, where g is the acceleration due to gravity. If the volume of the 

photographed region of the illumination is 

known, one can obtain the aerosol number 

density and size distribution. Experiments 

with alumina particles of given size distributions indicate that the method works accurately for aerosols with diameters >2.0 pin specific for particles with 

or > 2 (4pp) 

gravity pp]. One set of a typical experiment with 3.0-mm A1203 particles is presented, which shows that the measured size distribution peaks at approximately 3.0 dm. The 

precise error limits have been.otestablished 

thus far. 

TM X-64839 May 1, 1974 

Retention and Application of Skylab 

Experiment Experiences To Future 

Programs. Nancy Milly and Victor G. 

Gillespie. Quality and Reliability Assurance Laboratory. N74-22474 

This document has been prepared to 

consolidate into one listing certain outstanding problems encountered on Skylab Experiments in order that these experiences and 

associated recommendations might help to 

prevent similar problems on future programs. 

The criteria for selection of the data to be 

utilized in thi document was to identify the 

problem areas within the Skylab Program 

which it was felt would be of major 

significance with respect to future programs. 

Also, the problem had to be unique in that it 

would help identify to a designer/ 

manufacturer an unforeseen or unanticipated 

occurrence which could cause failures, delays, 

or additional cost. This would not include the 

multitude of run-of-the mill anomalies which 

are normally encountered in the design, manufacture and test of an aerospace experiment system. This document addresses only 

those unexpected problems that may occur

due to the nature of aerospace experiment entontent ar operoac eequiment 

environmental and operational requirements. 

TM X-64840 January 1974 

Vehicle Misalignment Prediction and 

Vehicle/Experhnent Pointing Compatibility Assessment. J. D. Hoverkamp. Astronautics Laboratory N74-23199 

A technique for predicting vehicle misalignment, the relationship of vehicle misalign­ ment to the total vehicle/experiment integration effort, and the methodology used in 

performing a vehicle/experiment pointing 

compatibility assessment, are presented. The 

technique is demonstrated in detail by 

describing how it was used on the Skylab 

Program. 

TM X-64841 - February 18, 1974 

SSME/Side Loads Analysis for Flight 

Configuration. Wayne Holland and John 

Harbison. Astronautics Laboratory. 

N74-22509 

This document describes the statistical 

loads analysis for the Space' Shuttle Main 

Engine (SSME) due to transient flow separation during ignition. The salient features of 

the analysis and the dynamic responses (loads 

and accelerations) of the engine are summarized. The results are based upon a 

26 
NASA TECHNICAL MEMORANDUM
 

preliminary structural model of the engine 

and its support structure. This analysis will be 

updated to include an active thrust vector 

control system and the most current representation of the engine and support structure 

backup models. 

TM X-64842 February 1, 1974 

Spectral Irradiance Curve Calculations 

for Any Type of Solar Eclipse. Adarsh 

Deepak and J. E. Merrill. AeroAstrodynamics Laboratory. N74-26266 

This paper describes a simple procedure 

for calculating the eclipse function (EF), 

and hence the spectral irradiance curve (SIC), 

(1-a), for any type of solar eclipse: namely, 

the occultation (partial/total) eclipse and the 

transit (partial/annular) eclipse. The SIC (or 

the EF) gives the variation of the amount (or 

the loss) of solar radiation of a given 

wavelength reaching a distant observer for 

various positions of the moon across the sun. 

The prolem of computing the SIC is 

complicated by the presence of the solar 

limb-darkening. Our scheme is based on the 

theory of light curves of eclipsing binaries, 

the results of which are tabulated in Merrill's 

Tables, and is valid for all wavelengths for 

which the solar limb-darkening obeys the 

cosine law: J = Jc (1 - x + x cos y). As an 

example of computing the SIC for an 

occultation eclipse which may be total, the 

calculations for the March -7, 1970, eclipse are 

described in detail. The calculations for the 

transit eclipses can be carried out in a similar 

manner. 

TM X-64843 April 2, 1973 

A Procedure for Calculation of Boundary 

Layer Trip Protuberances In Overexpanded Rocket Nozzles. Robert H. 

Schmucker. Astronautics Laboratory. 

N74-25804 

A procedure is described for sizing, 

scaling, positioning and performance loss 

calculation of a boufidary layer trip protuberance. The theoretical results are compared 

with some experimental data, 

TM X-64845 June 1974 

MSFC Skylab Operations Support Summary. James R. Martin. Skylab Programs 

Office, 

The Skylab mission began May 14, 1973, 

with the launch -of SL-l and ended February 

8, 1974, with SL-4 splashdown. During this 

time, the Huntsville Operations Support 

Center (HOSC) was the actionee of 1,882 

actions in addition to performing daily 

routine mission support activities. Almost 200 

significant problems were identified during the 

mission that required thorough investigation 

and in cases hardware modification to be 

provided for the next manned mission phase, 

Approximately 1,400 civil service and 

contractor personnel- had permanent access to 

the 10,000 square foot HOSC in Building 

4663 and three adjacent trailers. All other 

support was from remote permanent work 

stations. Around 300 personnel per shift, 3 

shifts per day, were in the HOSC during the 

entire mission. 

This operations report is a summary of 

the actions and problems MSPC encountered, 

together with procedures and staffing required 

to provide the mission support role. This 

report has been prepared as a reference for 

future operations planning as well as an 

evaluation report for the Skylab mission. 

TM X-64846 May 1974 

MSFC Skylab ATM Calibration Rocket 

Project. Skylab Programs Office. 

N74-26319 

27 
NASA TECHNICAL MEMORANDUM
 

This report provides the National Aeronautics and Space Administration (NASA) 

Headquarters, Office of Space Science (OSS), 

Marshall Space Flight Center (MSFC), and 

other interested agencies, with results of the 

Apollo Telescope Mount (ATM) Calibration 

Rocket (CALROC) performances and anomalies encountered. The performance period 

included six CALROC flights during the 

Skylab 2, 3 and 4 missions as well as those 

rocket flights prior to the Skylab mission 

which carried CALROC hardware for test 

purposes. Background material such as project 

purpose, management, launch facilities, 

booster and payload configuration is included 

for better understanding of the CALROC 

payload and its mission objectives. 

Three successful calibration flights with 

the NRL CALROC Scientific Instrument and 

two successful calibration flights with the 

HCO CALROC Scientific Instrument were 

obtained. Both the NRL and HCO data are 

being processed and the curves and/or data 

will be available at NRL, HCO or MSFC in 

late 1974 or early 1975. 

Initial calibration data analyses indicate 

that the data are adequate to excellent and 

that calibration of the Skylab ATM solar 

astronomy data will be successfully achieved. 

TM X-64847 May 1974 

Orbital Operation for Large Automated 

Satellites. J_ L. Lusk and V. Biro. Mission 

Operations Office. N74-26320 

This preliminary study presents orbital 

operations concepts for the shuttle launcher 

Large Automated Satellites (LAS). It includes 

the orbital operations elements and the major 

options for accomplishing each element. 

This study is based on the preliminary 

payload information available in Level I and 

II documents and on orbital operations 

methods used on past programs, both manned 

and unmanned. It includes a definition of 

detailed trade studies which need to be 

performed as satellite design details and 

organization responsibilities are defined. 

The major objectives of this study were 

to define operational methods and requirements for the long duration LAS missions 

which are effective and primarily economical 

to implement. 

TM X-64848 April 1974 

Spacelab Data Management Subsystem 

Phase B. Study. Astrionics Laboratory. 

N74-26334 

The data management subsystem (DMS) 

integrates the avionics equipment into an 

operational system by providing the computations, logic, signal flow, and interfaces needed 

to effectively command, control, monitor, 

and check out the experiment and subsystem 

hardware. Also, the DMS collects/retrieves 

experiment data and other information by 

recording and by command of the data relay 

link to ground. 

The major elements of the DMS are the 

computer subsystem, data acquisition and 

distribution- subsystem, controls and display 

subsystem, onboard checkout subsystem, and 

software. 

This report documents the results of the 

DMS portion of the Spacelab Phase B 

Concept Definition Study and defines MSFC's 

DMS design reference model. The following 

sections provide a detailed description of the 

28'
 
NASA TECHNICAL MEMORANDUM
 

DMS and its major subsystems. Related 

studies and trade-offs are presented in the 

appendices. 

TM X-64849 January 1974 

An Assessment of Separable Fluid Connector System Parameters to Perform a 

Connector System Design Optimization 

Study. Willibald Peter Prasthofer. Astronautics Laboratory. N74-279 I I 

The engineer today is more than ever 

concerned with the optimum solution to 

highly complex problems involving numerous, 

and often conflicting or unspecific demands 

made by stringent requirements in the areas 

of environment, cost, materials, performance, 

date of delivery, reliability, safety, and 

numerous other constraints imposed upon the 

designer. In this paper the key to optimization of design where there are a large number 

of variables, all of which may not be known 

precisely, lies in the mathematical tool of 

dynamic programming developed by Bellman. 

This methodology can lead to optimized 

solutions to the design of critical systems and 

in a minimum amount of time even when 

there are a great number of acceptable 

configurations to be considered. 

To demonstrate the usefulness of 

dynamic programming, an analytical method 

is developed for evaluating the relationship 

among existing numerous connector designs 

to find that configuration which is best 

(optimum). The data utilized in the study 

were generated from the some 900 flanges 

designed for six subsystems of the S-lB stage 

of the Saturn IB space carrier vehicle. The 

algorithm is general .enough to be useful in 

optimizing design and systematizing decisionmaking in a variety of related technical fields 

such as aeronuatics, construction, electronics, 

etc. 


TM X-64850 	 May 30, 1974 

System Safety Checklist Skylab Program 

Report. Skylab Program Office. 

N74-28344 

This document contains over '500 design 

criteria statements applicable to a wide 

variety of flight systems, experiments and 

other payloads, associated ground support 

equipment and facility support systems. The 

document reflects a composite of experience 

gained throughout the aerospace industry 

prior to Skylab and additional experience 

gained during the Skylab Program. It has been 

prepared to provide current and future 

program organizations with a broad source of 

safety-related design criteria and to suggest 

methods for systematic and progressive application of the criteria beginning with preliminary development of design requirements and 

specifications. Recognizing the users obligation to shape the checklist to his particular 

needs, a summary of the historical background, rationale, objectives, development and 

implementation approach, and benefits based 

on Skylab experience has been included. 

TM X-64851 	 April 1974 

Design of a Digital Controller for 

Spinning Flexible Spacecraft. 	 B. C. Kuo, 

S. M. Seltzer, G. Singh, 	 and R. A. 

Yackel. 	Astrionics Laboratory. 

N74-26322 

A new approach to digital control 

system design is applied to the analysis and 

design of a practical onboard digital attitude 

control system for a class of spinning vehicles 

characterized by a rigid body and two 

connected flexible appendages. The approach 

used is to design a continuous-data control 

system that will provide a satisfactory system 

response. Then, using the digital redesign 

method, a digital controller with onboard 

29 
NASA TECHNICAL MEMORANDUM
 

digital computer is designed to provide a A number of general studies that have 

digital control system whose states are similar been proposed for the PPEPL-Shuttle program 

to those of the continuous system at sampling are considered in qualitative detail from both 

instants. The simplicity of application of this the theoretical and practical points of view. 

approach is indicated by example. The The selection of experimental programs was 

example, using spinning Skylab parameters, is restricted to those which may be considered 

used to substantiate the conclusions. active as opppsed to refinements of the 

passive observational programs done preTM X-64852 July 1974 viously. It is concluded that, while these new 

Skylab Thruster Attitude Control Sys- studies were scientifically worthwhile and 

tem. G. F. Wilmer, Jr. Skylab Program could be performed in principle, in most cases 

Office. insufficient attention had been paid to the 

practical details of the experiments. Several 

This report documents the preflight specific areas of study, stressing in particular 

activities and the Skylab mission support the practical feasibility of the proposed 

effort for the Thruster Attitude Control experiments, are recommended. In addition, 

System (TACS). The preflight activities recommendations are made for further theoinclude a description of problems and their retical study, where appropriate. 

solutions encountered in the development, 

qualification, and flight checkout test TM X-64857 June 1974 

programs. The mission support effort is A Standard Particle Sizer - Velocimeter. 

presented as it relates to system performance A. Deepak, R. Ozarski, and I. A. L. 

assessment, real-time problem solving, flight Thomson. Systems Dynamics Laboraanomalies, and the daily system evaluation, tory. 

Finally, the detailed flight evaluation is 

presented for each phase of the mission using This report describes a standard particle 

system telemetry data. sizer-cum-velocimeter designed and build for 

the purpose of providing a standard source of 

The report asserts that the TACS met or aerosols of known size-distribution, moving 

exceeded design requirements and fulfilled its with a known velocity, for the purpose of 

assigned mission objectives, calibrating the continuous wave (CW) CO2 -

Laser Doppler Velocimeters at Marshall Space 

TM X-64856 March 1974 Flight Center. The instrument is 'designed 

Report of the Plasma Physics and with the capabilities of: (1)monitoring the 

Environmental Perturbation Laboratory size-distribution of particles of diameters 

(PPEPL) Working Groups Volume II - larger than 1.0 gm; (2) measuring flow 

Magnetospheric Experiments Working velocities in the range 0.05 - 100.0 cm/sec; 

Group. Program Development. (3) photographing particles of diameters above 

Vol. 1 N74-28169 0.2 pm moving at slow speeds (- Q.I cm/see);
 

Vol. II N74-28170 (4) measuring the size-distribution of particles
 

Vol. III N74-28171 settling in quiet air (or convection velocities
 

30 
NASA TECHNICAL MEMORANDUM
 

of 'less than 0.15 cm/sec); (5) use in the 

laboratory or in the field. 

The instrument is made up of the laser 

scattering counter (LSC) and the photographic system, each of which can function 

independently or in conjunction for simultaneous monitoring of the same sample of 

particles. The LSC can be easily modified to 

operate in two modes: (1)as a forwardscattering particle sizer-counter or (2) as a 

forward dual-beam velocimeter. The two 

modes 'of operation of the LSC are described 

in detail, though the experimental results of 

its use as a velocimeter are not reported here. 

TM X-64858 May 1974 

Charged Particle Radiation Environment 

for the LST. John W. Watts, Jr., M.,O. 

'Burrell, and J'. J. Wright. Space Sciences 

-Laboratory. N74-28,1'56 

Prelimihary charged particle dose rates 

are presented for the LST orbit. The trapped 

proton component appears to dominate the 

total dose for the expected shielding available. 

Typical dose rates should range from 400 to800, millirads/day. 

TM X-64859 July 1974 

Similitude Requirements for Hypersonic, 

Rarefied, Nonequilibrium Flow. William 

L. Hendricks. Systems Dynamics Laboratory. N74-27758 

Similitude requirements for hypersonic, 

rarefied flow with nonequilibrium chemistry 

and vibration are presented. The full NavierStokes equations with catalytic or noncatalytic walls and with or without slip 

conditions are nondimensionalized. The heat 

transfer coefficient is written in terms of 

fourteen dimensionless parameters and 

reduced to four by making the binary scaling 

assumption. The duplication of, blunt and 

sharp nose heat transfer requires the use of 

air over a geometrically similar model with 

the same free stream velocity,, wall temperature and product of free stream density and 

characteristic length. Estimates of this heat 

transfer coefficient are also presented. 

31 
NASA TECHNICAL NOTES
 

TN D-7211 October 1973 TN D-7416 October 1973 

The Effect of Finite Thrust and Heating Measurements and a Model for ConvecConstraints on the Synergetic Plane tive Velocities in the Turbulent BoundChange Maneuver for a Space Shuttle ary Layer. William C. Cliff and Virgil A. 

Orbiter-Class Vehicle. E. D. Dickmanns. Sandborn. Aero-Astrodynamics LaboraAero-Astrodynamics Laboratory. tory. N74-10319 

N73-32759 

Numerical solutions to the optimal A :physical model is presented whichil 

three-dimensional glide/thrust atmosphere skip describes convective velocities within a flat 

maneuver are obtained using the multiple plate turbulent boundary layer. A production 

shooting iteration scheme. A singular thrust zone concept similar to that which Kline has 

arc, induced by the heating constraints, is reported with his visualization techniques is 

encountered. The synergetic plane change used as a basis for the physical model. The 

maneuver is shown to be superior to an production zone concept employs the idea 

extra-atmospheric one for 556-km (300-nm) that packets of turbulent fluid are generated 

circular orbit plane changes of more than S near the viscous sublayer. These packets are 

degrees. found to be discernible from the mean 

motion and may move either outward from 

TN D-7386 August 1973 the production zone or inward depending on 

Approximations for Neutron Emission their circulation relative to the fluid surroundSpectra from Proton Collisions between ing the packet. The packets are predicted to 

20 and 500 MeV on Nuclei of A > 12. travel with a convective velocity different 

M.0. Burrell- Space Sciences Labora- from the local mean velocity throughout most 

tory. N73-29825 of the boundary layer. The model also 

predicts that the convective velocities will be 

When high-energy protons from solar functions of wave number outside the producproton events or trapped radiation belts ion zone. 

impinge on spacecraft structures, secondary 

particles are emitted. The most pernicious 

secondaries, from either a biological or The model predicts that the convective 

physical standpoint, are the cascade and velocity profile approaches the mean velocity 

evaporation neutrons because of their reaction profile after a finite length or time period. 

with matter leading to radioactive materials in After the finite length, the convective velocthe spacecraft structures. This report presents ities are predicted to become independent of 

an empirically determined cascade and evapo- wave number. The model predicts that the 

ration neutron emission spectra for protons asymptotic growth of the boundary layer will 

of energy between 20 and 500 MeV incident be a- linear function of distance. Experimental 

on all meterials at or above carbon in mass results are presented which agree with the 

number. predictions of the model. 

.32 
NASA TECHNICAL NOTES
 

Correlation concepts are used to measure 

the convective velocity. Convective velocity as 

a function of frequency indicates Taylor's 

hjpotheis to be invalid for the turbuldnt 

boundary layer. 

TN D-7422 December 1973 

Multiple Regression Technique for Pth 

Degree Polynomials With and Without 

Linear Cross Products. John William 

Davis. Aero-Astrodynamibs Laboratory. 

N74-14254 

A multiple regression technique has been 

developed by which the nonlinear behavior of 

specified independent variables can be related 

to a given dependent variable. The polynomial 

expression can be of Pth degree and can 

incorporate N independent variables. Two 

cases are treated such that mathematical 

models can be studied both with and without 

linear cross products. The resulting surface 

fits can be used to summarize trends for a 

given phenomenon and provide a mathemati-

"cal relationship for subsequent analysis. 

To implement this technique, separate 

computer programs have been developed for 

the case without linear cross products and for 

the case incorporating such cross products 

which evaluate the various constants in the 

model regression equation. In addition, the 

significance of the estimated regression equation is considered and the standard deviation, 

the F statistic, the Maximum absolute percent 

error, and the average of the absolute values 

qf the percent of error evaluated, 

The computer programs and their manner of utilization are described. Sample 

problems are included to illustrate the use 

and capability of the technique which show 

the output formats and typical plots cornparing computer results to each set of input 

data. 

TN D-7432 November 1973 

Optimization of Wave Cancellation in 

Variable Porosity Transonic Wind Tunnel 

Flows. John William Davis. AeroAstrodynamics Laboratory. N7-11097 

A technique has been developed which is 

capable of determining the optimum wall 

configuration for a variable porosity perforated wall transonic wind tunnel. The technique is based on a mathematical model 

arrived at by considering the results of theory 

and past experimental investigations. A performance index was determined as a function 

of the significant wind tunnel parameters by 

comparing a formulation of this mathematical 

model, using MSFC 14 inch Trisonic Wind 

Tunnel Experimental results, to interference 

free results. The resulting relationship was 

then used to determine the combination of 

wind tunnel parameters which should yield 

minimum reflected wave interference. 

A theoretical development.of wall porosity requirements for thick wall inclined hole 

test sections is included which follows the 

trends and generally the magnitude of available experimental data. This theory is useful 

in studyingthe present variable porosity case, 

but also should be of value in studies 

concerning the wave cancellation process for 

fixed porosity walls. 

To implement this optimization procedure a multiple regression technique for Pth 

degree polynomials is developed to evaluate 

the mathematical models. This powerful 

general purpose tool, can be used in any 

scientific endeavor where the process can be 

measured or for which experimental data 

exist. Using this regression technique many 

phenomena can be correlated or susp'ected 

laws or relationsips investigated and optimizations determined other than those developed 

in the course of this study. 

33 
NASA TECHNICAL NOTES
 

TN D-7433 October 1973 predictions based upon the work of J.A. 

Contamination Assessment and Control King. Nine cavitation tests run at the nominal 

in Scientific Satellites. Robert J. pump speed over a 5°K temperature range 

Naumann. Space Sciences Laboratory. showed progressively lower net positive sucN73-32738 tion head (NPSH) requirements as temperature was increased. Two-phase operation was 

Techniques for assessment and control of not achieved. The temperature varying NPSH 

the contamination environment for both data were used to calculate thermodynamic 

particulates and condensible vapors in the effects on NPSH, and the results were 

vicinity of spacecraft are developed. An compared to existing data. 

analysis of the deposition rate on critical 

surfaces is made considering sources within 

the line of sight of the surface in question as TN D-7457 October 1973 

well as those obscured from the line of sight. Round-Off Errors in Cutting Plane AlgoThe amount of contamination returned by rithms Based on the Revised Simplex 

collision with the surrounding atmosphere is Procedure. John Edd Moore. Neroestimated. Scattering and absorption from the Astrodynamics Laboratory. N73-33517 

induced atmosphere of gases and particulates 

around the spacecraft are estimated. Finally, This report statistically analyzes corndesign techniques developed for Skylab to putational round-off errors associated with 

reduce the contamination environment to an the cutting plane approach to Isolving linear 

acceptable level are discussed. integer programming problems. Cutting plane 

methods require that the inverse of a 

TN D-7451 October 1973 sequence of matrices be computed. The 

An Experimental Investigation of Two- problem basically reduces to one of miniPhase Liquid Oxygen Pumping. Loren A. mizing round-off errors in the sequence of 

Gross. Astronautics Laboratory. inverses. Two procedures for minimizing this 

N73-33747 problem are presented, and their influence on 

error accumulation is statistically analyzed. 

The results of an experimental program One procedure employs a very small tolerance 

to explore -the feasibility of pumping two- factor to round computed values to zero. The 

phase oxygen (liquid and gas) at the pump other procedure is a numerical analysis 

inlet are reported. Twenty-one cavitation tests technique for "reinverting" or improving 

were run on a standard J-2 oxygen pump at the approximate inverse of a matrix. The 

the MSFC Components Test Laboratory. All results indicate that round-off accumulation 

tests were run with liquid oxygen 5 to I00K can be effectively minimized by employing a 

above the normal boiling point temperature. tolerance factor which reflects the number of 

During ten tests run at approximately 50 significant digits carried for each calculation 

percent of the nominal operating speed, two and by applying the reinversion procedure 

phase conditions were achieved. Vapor vol- once to each computed inverse. If 18 

umes of 40 to 50 percent at the pump inlet significant digits plus an exponent are carried 

were noted before complete pump perform- for each variable during compatations, than a 

ance loss. The results are compared to tolerance value of 0.1 X 10-12 is reasonable. 

34 
NASA TECHNICAL NOTES
 

The prerequisite for reading this report is 

a working knowledge of the simplex method 

and the revised simplex algorithm in particular. 

TN D-7469 November 1973 

Lunar Roving Vehicle Navigation System 

Performance Review. Earnest C. Smith 

and William C. Mastin. Astrionics Laboratory. N74-1 1434 

The design and operation of the Lunar 

Roving Vehicle (LRV) navigation system are 

briefly described. The basis for the premission 

LRV navigation error analysis is explained 

and an example included. The real-time 

mission support operations philosophy is 

presented. The LRV navigation system operation and accuracy during the lunar missions 

are evaluated. 

TN D-7472 November 1973 

Analysis of Axisyinmetrical Vibration of 

a Partially Liquid-Filled Elastic Sphere 

by the Method of Green's Function. 

Rudolf F. Glaser. Astronautics Laboratory. N74-12546 

The longitudinal dynamic behavior of' 

launch vehicles is largely determined by their 

huge liquid propellant masses which are spring 

supported by the elastic tank walls. Throughout much of the powered flight time, these 

masses constitute a high percentage of the 

entire vehicle mass and, therefore, may 

dominate the fundamental modes of the 

vehicle. 

In this report, a spherical container is 

considered. The analysis is based on a 

Galerkin approach, in the course of which a 

second-order differential equation must be 

solved. The solution has been obtained by the_ 

method of Green's function. This method is 

favorable because it displays the manner in 

which the analysis can be extended to 

partially liquid-fidled general shells of revolution. 

The computer programs currently available for partially liquid-filled propellant tanks 

are based on the finite element methods and 

result in analytical models having as many as 

several hundred degrees of freedom. The 

method applied in this report results in a 

model having less than 10 degrees of freedom 

as can be shown by numerical evaluation. 

Therefore, it will be possible to analyze 

propellant tanks using much less computer 

time with comparable accuracy. 

TN D-7500 December 1973 

A Fine Pointing System for the Large. 

Space Telescope. Werner 0. Schiehlen. 

Astrionics Laboratory. N74-14507 

The large Space Telescope (LST) developed by NASA required ultra-high pointing 

stability within 0.005 arc sec rms. A fine 

guidance system is proposed to body-point 

the entire spacecraft within this limit. The 

spacecraft is modeled as a rigid body having 

reaction wheel actuators and subject to 

gravitational and magnetic disturbance 

torques. The fine guidance sensor is cluttered 

with electronic noise. The Disturbance 

Accommodation Standard deviation Optimal 

Controller (DASOC) is designed to be optimal 

with respect to the transient, and the 

steady-state response to noise, whereas the 

steady-state response to deterministic external 

torques is exactly zero. Compared with 

35 
NASA TECHNICAL NOTES
 

- conventional controllers, the fine guidance tions, and heat transfer coefficien ts- on tiie

system with the DASOC offers as much as a base surface. The maximum heating rate was 

factor of 30 improvement in pointing stabil- 'found on the centerline, and the twoity, resulting in an optimal performance of dimensional stagnation point flow solution 

nearly 0.0001 arc see rms. Thus, the required was adequate to estimate the, maximum 

pointing stability can easily be obtained, and heating rate so long as the local Reynolds 

a large margin remains for the compensation number could be obtained. 

of possible deteriorations. 

TN D-7515 December 1973 

TN D-7508 December 1973 A Method of Billing Third Generation 

A New Technique for Calculating Computer Users. Philip N. Anderson and 

Reentry Base Heating. James C. S. Meng. Delano k. Hyter. Computatioil LaboraAero-Astrodynamics Laboratory. tory. 

N74-13507 

Presented in this report is a method for 

.... . charging users for the processing of their 

The laminar base flow field of a applications on third generation digital corntwo-dimensional reentry body has been -- puter" sye's s." or "background purposes, 

studied by Telenin's method. The flow problems and goals in billing on third gendomain was divided into strips along the eration systems are discussed. Detailed 

x-axis, and the flow variations were repre- formulas are derived based on expected 

sented by Lagrange interpolation polynomials utilization and computer component cost. 

in the transformed vertical coordinate. The These formulas are then applied to a specific 

complete Navier-Stokes equations were used computer system (UNIVAC 1108). 

in the near wake region, and the boundary 

layer equations were applied elsewhere. The The method, although possessing some 

boundary conditions consisted of the flat weaknesses noted herein, is presented as a 

plate thermal boundary layer in the forebody definite improvement over use of second 

region and the near wake profile in the generation billing methods. 

downstream region. The resulting two-point 

boundary value problem of 33 ordinary TN D-7590 February 1974 

differential equations was then solved by the Dynamics and Column Densities of Small 

multiple shooting method. The reentry body Particles Ejected from Spacecraft. Robert 

was assumed at zero angle of attack in a J.Naumann. Space Sciences Laboratory. 

Mach 11 free stream with Reynolds number N74-17539 

Re%H ranging from 0.8 X l01 to 1.2 X 101. 

The detailed flow field and thermal environ- Trajectories and relative motions of small 

ment in the base region are presented in-the particles ejected from a spacecraft have been 

form of temperature contours, Mach number analyzed, and modifications to the clearing 

contours, velocity vectors, pressure distribu- times and column densities because of orbital 

36 
NASA TECHNICAL NOTES
 

dynamics have been assessed. It was found TN D-7592 February 1974 

that despite the fact that such particles are Inclusion of Known Integrals in the 

confined by orbital dynamics to move along Optimal Trajectory Problem. Rowland E. 

similar trajectories with the spacecraft rather Burns. Aero-Astrodynamics Laboratory. 

than to continue their free expansion, the N74-16537 

effect is negligible for viewing angles away 

from the orbital path. Small particles are The classical problem of determination 

rapidly swept away by drag and will not of the rocket trajectory which minimizes mass 

contribute significantly to the column density expenditure during motion between two 

when viewing along the velocity vector in a points in the field of a single gravitating body 

420-km earth orbit. However, substantial is analyzed. 

increases in column density can result when 

viewing in a direction qpposite to the velocity The known integrals of the system are 

vector because of drag effects. In the absence incorporated into the adjoint equations, 

of drag, significant column densities can build resulting in a reduction from a seventh-order 

up both in front of and behind the spacecraft adjoint system to a third-order adjoint 

in earth orbit for particles released at a few system. The first case which is treated is that 

meters per second. This effect is much less of planar motion under specific end condipronounced in lunar orbit because the same tions. In this case a regularization of the 

release velocity produces a larger orbital recently derived equations is achieved. 

perturbation for the particle. 

The general three-dimensional case is also 

TN D-7591 February 1974' reduced from a seventh-order adjoint system 

Secondary Electron Background Pro- to a third-order adjoint system. In this case a 

duced by Heavy Nuclei in- a Multiwire regularization has not been found. 

Proportional Counter Hodoscope. S. H. 

Morgan, Jr., J. W. Watts, Jr., H. Schwille, TN D-7607 March 1974 

and U. Pollvogt. Space Sciences Labora- Digital Image Registration Method Based 

tory. N74-17526 Upon Binary Boundaiy Maps. R. R. 

Jayroe, J. F. Andrus, and .C. W. 

The secondary electron background Campbell. Aero-Astrodynamics Laboraproduced by heavy nuclei in a multiwire tory. N74-19035 

proportional counter hodoscope is calculated 

using both a simplified and a more .complete A relatively fast method is presented for 

Monte Carlo model. These results are corn- matching or registering the digital data of 

pared with experimental data from a small imagery from the same ground scene acquired 

multiwire proportional counter hodoscope at different times, or from different multioperated in a 530 MeV/nucleon accelerator spectral images, sensors, or both. In using this 

beam of nitrogen nuclei. Estimates of the method, it is assumed that the digital images 

secondary electron background produced by can be registered by using translations and 

heavy relativistic nuclei are presented along rotations only, that the images are of the 

with the detailed results from calculations of same scale, and that little or-no distortion 

energy deposition in the hodoscope counter exists between images, It is further assumed 

cells. that by working with several local areas of 

37 
NASA TECHNICAL NOTES
 

the image, the rotational effects in the local a. The use of subjective expert 

areas can be neglected. Thus, by treating the opinion obtained through mail questionnaires. 

misalignments of local areas as translations, it Such subjectiye data were required because 

is possible to determine rotational and observed data were not available for one 

translational misalignments for a larger por- particular type of testing considered in the 

tion of the image containing the local areas. optimization procedure. Probabilistic models 

This procedure of determining the misalign- were derived for analyzing the subjective 

ment and then registering the data according opinions. 

to the misalignment can be repeated until the b. Incorporation of new informadesired degree of registration is achieved. The tion with prior data through the use of 

method to be presented is based upon the use Bayesian statistics. Laboratory test results 

of binary boundary maps produced from the were used to determine a prior distribution, 

raw digital imagery rather than the raw digital and flight data were used as new information 

data. for revising the prior distribution. 

The methodology developed was applied 

to several typical aerospace structures to 

illustrate the effect of system characteristics 

TN D-7646 June 1974 such as value of weight, cost of failure, and 

Reliability-Based Econometrics of Aero- cost of testing on the optimum decision. 

space Structural Systems: Design Criteria 

and Test Options. Jerrell M. Thomas and TN D-7681 May 1974 

S. Hanagud. Astronautics Laboratory. Test Tesults from a Breadboard Cryogenic Propellant Conditioning Assembly. 

Henry P. Stinson, Jr. Astronautics Laboratory. N74-23333 

Several new areas in aerospace structural 

reliability were investigated. The more signifi- Cryogenic auxiliary propulsion systems 

cant original contributions were: consist of five major subsystems; propellant 

1. Development of a decision method- tanks, propellant conditioning assemblies, 

ology for selecting a combination of struc- accumulators, propellant distribution systems, 

tural tests and structural design factors for and thrustors. The propellant conditioning 

aerospace systems on the basis of optimized assembly (PCA) converts low pressure liquid 

expected cost. The decision method involves to high pressure gas for use by the thrustors, 

the use of Bayesian statistics and statistical and is one of the most complex subsystems 

decision theory as exemplified by the work of of the cryogenic propulsion system. The 

Pratt, Raiffa, and Schlaifer of the Harvard ability to achieve rapid starts and at the same 

School of Business Administration. time maintain system control are two critical 

2. Development of Procedures for areas of PCA operation. To investigate these 

obtaining and updating data-based probabil- critical areas of operation, a PCA of the 

istic strength distributions for aerospace general type required was designed, fabristructures when test information is available cated, and tested using existing hardware. 

and for obtaining subjective distributions Realistic start times were achieved and system 

when data are not available. Techniques used control was maintained at all operating 

in developing these distributions included: conditions. 

38 
NASA TECHNICAL REPORT
 

TR R-409 September 1973 highest at trace amounts of copper (4850 

The Application of Holography as a cal/gm-atom), but decreases with increasing 

Real-Time Three-Dimensional Motion concentration of copper and levels off to 

Picture Camera. Robert L. Kurtz. Space 2550 callgm-atom at about 25 weight percent 

Sciences Laboratory. N73-31413 copper. The results are explained on the basis 

of electron-solute interaction and a gas model 

A historical introduction to holography of diffusion. 

is presented, as well as a basic description of 

sideband holography for stationary objects. A TR R-417 October 1973 

brief theoretical development of both time- Solute Diffusion in Liquid Metals. B. N. 

dependent and time-independent holography Bhat. Process Engineering Laboratory. 

is also provided, along with an analytical and N73-32032 

intuitive discussion of a unique holographic 

arrangement which allows the resolution of A gas model of diffusion in liquid metals 

front surface detail from an object moving at is presented. In this model, ions of liquid 

high speeds. As an application of such a metals are assumed to behiave like the 

system, a real-time three-dimensional motion molecules in a dense gas. Diffusion coefficient 

picture camera system is discussed and the of solute is discussed with reference .to its 

results of a recent demonstration of the mass, ionic size, and pair potential. The 

world's first true three-dimensional motion model is applied to the case of solute 

picture are given. diffusion in liquid silver. An attempt has been 

made to predict diffusion coefficients of 

TR R-415 September 1973 solutes with reasonable accuracy. 

Thermotransport in Liquid AluminumCopper Alloys. B. N. Bhat. Process Engi- TR R-424 May 1974 

neering Laboratory. N73-31030 Optical Holography Applications for the 

Zero-g Atmospheric Cloud Physics Laboratory. Robert L. Kurtz. Space Sciences 

A thermotransport study was made on a Laboratory. N74-25876 

series of liquid aluminum-copper alloys which 

contained from trace amounts to 33 weight A complete description of holography is 

percent copper. The samples in the form of provided, both for the time-dependent case of 

narrow capillaries were held in known tern- moving scene holography and for the timeperature gradient of thermotransport appa- independent case of stationary holography. 

ratus until the stationary state was reached. Further, a specific holographic, arrangement is 

The samples were analyzed for the concentra- proposed for application to the detection of 

tion of copper along the length. Copper was parricle size distribution in an atmospheric 

observed to migrate to colder regions in all simulation cloud chamber. In this chamber 

the samples. The heat of transport, Q*, was particle growth rate is investigated; therefore, 

determined for each composition from a plot the proposed holographic system must capof concentration of copper versus reciprocal ture continuous particle motion in real time. 

absolute temperature. The value of Q* is the Such a system is described. 

39 
NASA TECHNICAL REPORT
 

TR R-426 April 1974 for long duration flights and is less sensitive 

Low Thrust Space Vehicle Trajectory to errors in the guesses of the unknown 

Optimization Using Regularized Vari- boundary values. 

ables. K. 3. Schwenzfeger. Aero .-. 

Astrodynamics Laboratory. N74-20520 TR R-430 June 1974 

Holographic Nondestructive Tests 

Optimizing the trajectory of a low thrust Performed on Composite Samples of 

space vehicle usually means solving a non- Ceramic-Epoxy-Fiberglass Sandwich 

linear two point boundary value problem. In Structure. Robert L. Kurtz and H. K. 

general, accuracy requirements necessitate Liu. Space Sciences Laboratory. 

extensive computation times. In celestial N74-26367 

mechanics, regularizing transformations of the 

equations of motion are used to eliminate When a hologram storing more than one 

computational and analytical problems that wave is illuminated with coherent light, the 

occur during close approaches to gravitational reconstructed wave fronts interfere with each 

force centers. It was shown in previous other or with any other phase-related wave 

investigations that regularization in the formu- front derived from the illuminating source. 

lation of the trajectory optimization problem This multiple wave front comparison is called 

may reduce the computation time. In this holographic interferometry, and its applicastudy, a set of regularized equations describ- tion is called holographic nondestructive 

ing the optimal trajectory of a continuously testing (HNDT). 

thrusting space vehicle is derived. The computational characteristics of the set are The theoretical 
NASA SPECIAL PUBLICATIONS
 

SP-3080 1973- SP-3078 1973 

Handbook of Infrared Radiation from Tables for Supersonic Flow of Helium 

Combustion Gases. C. B. Ludwig, W. Around Right Circular Cones at Zero 

Malkmus, J. E. Reardon, and J. A. L. Angle of Attack. Joseph L. Sims. 

Thomson. R. Goulard and J. A. L. Aero-Astrodynamics' Laboratory. 

Thomson, eds. Acro-Astrodynamics Lab- N73-27807 

oratory. N73-27208 

41 
CONTRACTOR REPORTS
 

(Abstracts for these reports may be obtained from STAR)
 

(Note: The following eleven reports were 

published but not listed in the FY 1973 

edition of this publication.) 

CR-61389 July 5, 1972 

Further Developments in Cloud Statistics 

for Computer Simulations. NAS8-26846. 

Allied Research Associates, Inc. 

N72-31615 

CR-61390 May 1, 1972 

Saturn Base Heating Handbook, Final 

Report. NAS8-5608. The Boeing Cornpany. N72-30895 

CR-61391 August 1, 1972 

Banding Due to Temperature Oscillations 

in the Unidirectional Solidification of 

Eutectic Alloys. NAS8-21809. Hayes 

International Corporation. N72-30469 

CR-61392 September 1972 

ERISTAR-Earth Resources Information 

Storage, Transformation, Analysis, and 

Retrieval-Final Report. NGTO1-003-044. 

Auburn University. N73-10399 

CR-61393 May 1972 

Evaluation of Human Engineering Design 

Standard (MSFC-STD-267A) in the 

Design of Manned Space Vehicles. Final 

Report, NGLO-008-001. University of 

Alabama in Huntsville. N72-32846 

CR-61-394 September 1972 

Eristar Administrative Report. NGTOI003-044. Auburn University. N73-10400 

CR-61395 September 1972 

1972 NASA-ASEE Summer Faculty 

Fellowship Program - Final Report. 

NGTOI-003-045. Auburn University and 

University of Alabama. N73-10992 

.CR-61396 September 1972 

1972 NASA-ASEE Summer Faculty 

Fellowsnip Program - Research Reports. 

NGTO1-003-045. Auburn University and 

University of Alabama. N73-14938 

CR-61397 September 1972 

High Intensity Portable Flourescent 

Light. NASS-24527. Iota Engineering, 

Inc. N72-31238 

CR-61398 September 1972 

Interrelated Structure of High Altitude 

Atmospheric Profiles. NAS8-2823 1. 

University of Dayton Research Institute. 

N72-32415 

CR-61399 October 1972 

Earth Resources Data Processoi. Final 

Report, NAS8-26797. Engineering 

Mechanics Division, lIT Research Institute. N73-12390 

CR-2196 November 1973 

Decomposition-Aggregation Stability 

Analysis. NAS8-27799. University of 

Santa Clara. N74-10802 

CR-2287 July 1973 

Effect of Shear on Aircraft Landing. 

NAS8-26600. The University of Dayton 

Research Institute. N73-27023 

CR-2288 July 1973 

A Model of Wind Shear and Turbulence 

in the Surface Boundary Layer. NAS8­

26600. The University of Dayton 

Research Institute. N73-27021 

42 
CONTRACTOR REPORTS
 

CR-2289 July 1973 CR-2431 May 1974 

Variations of the Low Level Winds Acoustic Sounding in the Planetary 

During the Passage of a Thunderstorm Boundary Layer. NAS8-28659. UniverGust Front. NAS8-27334. The sity of Oklahoma. N74-23162 

Pennsylvania State University. 

N73-27544 CR-2432 May 1974 

Acoustic Radar Investigations of 

CR2291 July 2973 Boundary Layer Phenomena. NASSAsteroid and Comet Exploration. NASS- 28659. University of Oklahoma. 

27929. University Research Foundation N74-23183 

and University of California. N73-27726 

CR-2438 June 1974 

CR-2304 August 1973 Investigation of the Turbulent Wind 

A Compilation of Studies from Atmos- Field Below 500 Feet Altitude at the 

pheric Variability Experiment (AVE). Eastern Test Range, Florida. NAS8­

NAS8-26751. Texas A&M University. 21140. The Pennsylvania State UniverN73-31577 sity. -N74-28077 

CR-2345 October 1973 CR-120100 January i972 

The Development of a Pseudo-Nyquist Guidelines for Fabrication of Hybrid 

Analysis Technique for Hybrid Sampled- Microcircuits for Shuttle Electronic 

Data Control Systems. NAS8-4016. Hardware. NAS8-26384. North American 

Chrysler Corporation. N73-33847 Rockwell Corp. X74-10025 

CR-2360 December 1973 CR-120101 September 1973 

Survey on Effect of Surface Winds on Investigation of Scaling Characteristics 

Aircraft Design and Operation and for Defining Design Environments Due 

Recommendations for Needed Wind to Transient Ground Winds and Near 

Research. NAS8-28136. Aeronautical Field, Nonlinear Acoustic Fields. NASSResearch Association of Princeton, Inc. 28249. University of Alabama. 

N74-12317 N74-12040 

CR-2361 January 1974 CR-120102 October 10, 1973 

Determination of Critical Nondimen- Space Shuttle Solid Rocket Booster 

sional Parameters in Aircraft Dynamic Performance Evaluation Model. NASSResponse to Random Input. NASS- 29643. The Boeing Company. 

27334. The Pennsylvania State Univer- X74-10029 

sity. N74-16322 

CR-120103 June 10, 1973 

CR-2428 May 1974 A Model Study of the SRB Water Entry, 

Stability Region Maximization by Including Flexibility Effects (Final 

Decomposition-Aggregation Method. Report). NAS8-28618. -Bolt Beranek & 

NAS8-27799. University of Santa Clara. Neuman. X74-10038 

N74-23392 

43 
CONTRACTOR REPORTS
 

CR-120104 September 1973 CR-120110 February 1972 

Development of Modified Poly Space Tug Point Design Study (Vol. II: 

(Peffluoropropyleneoxide) Urethane Sys- Final Report; Operations, Performance, 

terns for use in Liquid Oxygen and in and Requirements). NAS7-200. North 

Enriched 100% Oxygen Atmosphere. American Rockwell Corp. N74-13608 

NAS8-27082. Whittaker Corp. 

N74-11922 CR-120111 February 1972 

Space Tug Point Design Study (Vol. Ill, 

CR-120105 August 1973 Part 2: Final Report, Design DefiniLarge Amplitude Flutter of a Low tions). NAS7-200. North American 

Aspect Ratio Panel at Low Supersonic Rockwell Corp. N74-13610 

Speeds, Comparison of Theory and 

Experiment. NAS8-28577. Princeton CR-120112 February 1972 

University. N74-1 1806 Space Tug Point Design Study (Vol. IV: 

Final Report, Program Requirements). 

CR-120106 October 1973 NAS7-200. North American Rockwell 

Space Shuttle Solid Rocket Booster Corp. N74-13611 

Recovery System Definition (Vol. 1: 

Final Technical Report). NAS8-29622. CR-120113 May 3, 1965 

The Martin Marietta Corp. N74-13579 Thermal Analysis Research and 

Development, Microminiaturization TechCR-120107 October 1973 niques and Circuitry, and its AdaptabilSpace Shuttle Solid Rocket Booster ity to Radar Altimeters. NAS8-11682 

Recovery System Definition (Vol. 1I: (Phase Completion Report). WestingSRB Water Impact Monte Carlo Com- house. 

puter Program, Users Manual). NAS8­

29622. The Martin Marietta Corp. CR-I 20114 February 1972 

N74-13581 Space Tug Point Design Study (Vol. V). 

NAS7-200. North American Rockwell 

CR- 120108 October 1973 Corp. X74-74487 

Space Shuttle Solid Rocket Booster 

Recovery System Definition (Vol. 111: CR-120115 June 1973 

SRB Water Impact Loads Computer Requirements and Concepts for Materials 

Program, Users Manual). NAS8-29622. Science, and Manufacturing in Space 

The Martin Marietta Corp. N74-13580 Payload/Equipment Study. NAS8-28938. 

TRW. X74-10030 

CR-1 20109 February 1972 

Space Tug Point Design Study (Vol. I: CR-120116 July 1973 

Final Report, SA2190 Summary). Requirements and Concepts for Materials 

NAS7-200. North American Rockwell Science and Manufacturing in Space 

Corp. N74-13607 Payload/Equipment Study. NAS8-28938. 

TRW. X74-10031 

44 
CONTRACTOR REPORTS
 

CR-120117 June 1973 CR-I 20123 August 1973 

Requirements and Concepts for Materials Unsteady Aerodynamic Analysis of 

Science and Manufacturing in Space Space Shuttle Vehicles (Part II: Steady 

Payload/Equipment Study. NAS8-28938. and Unsteady Aerodynamics of SharpTRW. X74-10032 Edged Delta Wings). NASS-28130. 

Lockheed Missiles and Space Co. 

CR-120118 July 1973 N74-15530 

Requirements and Concepts for Materials 

Science and Manufacturing in Space CR-I 20124 August 1973 

Payload/Equipment Study (Vol. IIC: Unsteady Aerodynamic Analysis of 

Experiments'Equipment Review). NASS- Space Shuttle Vehicles (Part III: Booster 

28938. TRW. X74-10033 Interference Effects). NAS8-28130. 

Lockheed Missiles and Space Co. 

CR-120119 July 1973 N74-15531 

Requirements and Concepts for Materials 

Science and Manufacturing in Space CR-1 20125 August 1973 

Payload/Equipment Study (Vol. IID: Unsteady Aerodynamic Analysis of 

Payload Equipment). NAS8-28938. Space Shuttle Vehicles (Part IV: Effect 

TRW. X74-10034 of Control Deflections on Orbiter 

Unsteady . Aerodynamics). NAS8-28130. 

CR-120120 June 1973 Lockheed Missiles and Space Co. 

Requirements and Concepts for Materials N74-15532 

Science and Manufacturing in Space 

Payload/Equipment Study (Vol. IE: CR-120126 

Operations Analysis). NAS8-28938. Study on Optical Communication 

TRW. X74-10035 Experimental Facility. NAS8-20304. 

Sylvania. 

CR-120121 July 1973 Vol. I N74-71412 

Requirements and Concepts for Materials Vol. II N74-70842 

Science and Manufacturing in Space 

Payload/Equipment Study (Vol. II. CR-120127 May 31, 1973 

Programmatics). NAS8-28938. TRW. Experimental Investigation of the Critical 

X74-10036 Magnetic Fields of Transition Metal 

Superconductors (Final Report). NAS8-

CR- 120122 June 1973 28900. Clark University. N74-15434 

Alstrom Thin Fuel Concept Evaluation 

(Final Report). NA98-2131 1. ESSI CR-120128 September 1973 

Research and Engineering Co. Cost, Technical, and Programmatic 

X74-10044 Centuer Data Study (Final Report)., 

NAS8-29075. General Dynamics/Convair. 

Vol. I X74-10074 

Vol. II X74-10075 

Appendix X74-10076 

45
 
CONTRACTOR REPORTS
 

CR-120129 September 1973 CR-120138 March 15, 1974 

Warm Gas TVC Design Study (Final Space Laboratory Data Management 

Report). NAS8-28651. Martin Marietta Study. NAS8-14000. IBM. X74-10087 

Corp. N74-16484 

CR-120139 December 1973 

CR-I 20130 November 1973 The Stanford Gyro Relativity ExperiThe Fabrication and Test of a Dual Spin ment. Stanford University. 

Gas Bearing. Reaction Wheel. NAS8­

29013. Martin Marietta Corp. CR-120140 June 1969 

N74-21069 Human Engineering Criteria for Maintenance and Repair of Advanced Space 

CR-I 20131 September 1973 Systems (Vol. I). NAS8-21429. General. 

Feasibility Study of Reaction Control Electric. 

Systems (Final Report). . NAS8-26580. 

Auburn University. N74-16562 CR-120141 June 15, 1969 

Human Engineering Criteria for MainteCR-120132 September 14, 1973 nance and Repair of Advanced Space 

Design Implementation in Model- Systems (Vol. II) NAS8-21429. General 

Reference Adaptive Systems. NAS8- Electric. 

26580. Auburn University. N74-16553 

CR-I 20142 June 15, 1969 

CR-I 20133 September 1973 Human Engineering Criteria for MainteSome Optimal Considerations in Attitude nance and Repair of Advanced Space 

Control Systems. NAS8-26580. Auburn Systems (Vol. III). General Electric. 

University. N74-16552 

CR- 20143 December 15, 1973 

CR-I 20134 November 1973 Design Study of RLIO Derivatives (Vol. 

Investigation of the Jet Noise Prediction 1). NAS8-28989. Pratt and Whitney. 

Theory and Application, Utilizing the X74-10103 

PAO Formulation. NAS8-28588. University of Alabama at Huntsville. CR-i 20144 December 25,2973 

Design Study of RLl0 Derivatives (Vol. 

CR-I 20136 January 29, 1974 II). NAS8-28989. Pratt and Whitney. 

Engine Progress Report (Saturn Engines X74-10105 

O&FS Program). NAS8-25156. 

Rocketdyne. X74-10067 CR-120145 December 15, 1973 

Design Study of RL10 Derivatives (Vol. 

CR-120137 September 1973 11). NAS8-28989. Pratt and Whitney. 

Double Time Lag Combustion Instability X74-10104 

Model for Bipropellant Rocket Engines 

(Final Report). University of Alabama. 'CR-120146 December 15, 1973 

N74-18401 	 Design Study of RL1O Derivatives (Vol. 

III, Part 1). NAS8-28989. Pratt and 

Whitney. X-74-10106 

46 
CONTRACTOR REPORTS
 

CR-120147 December 15, 1973 CR-120155 December 15, 1973 

Design Study of RLI0 Derivatives (Vol. RL1O Derivative, IIA and IIB Space Tug 

IV). NAS8-28989. Pratt and Whitney. Engine Oxygen Heat Exchanger. NAS8­

X74-10108 28989. Pratt and Whitney. X74-10099 

CR-120148 December 16, 1973 CR-120156 December 15, 1973 

Design Study of RL1O Derivatives (Vol. RL1O Derivative, IIA and iB Space Tug 

III, Part 2). NAS8-28989. Pratt and Engine Torch Assembly. NAS8-28989. 

Whitney. Pratt and Whiteney. X74-10100 

CR-120149 February 5, 1973 CR-120157 December 15, 1973 

RL1O Derivative, IIA and lIB Space Tug RLlO Derivative, IIA and liB Space Tug 

Engine Sequenced Valves. NAS8-28989. Engine Plumbing and Miscellaneous 

Pratt and Whitney. X74-10109. Hardware. NAS8-28989. Pratt and 

Whitney. X74-10101 

CR-120150 December 15, 1973 

RLIO Derivative, IIA and IIB Space Tug C-120158 December 15, 1973 

Pressure Operated Valves. NAS8-28989. RL1O Derivative, IIA and IIB Space Tug 

Pratt and Whitney. X74-10094 Engine Systems. NAS8-28989. Pratt and 

Whitney. X74-10102 

CR-120151 December 15, 1973 

RLI0 Derivative, IIA and JIB Space Tug CR-120159 December 22, 1972 

Engine Flight Instrumentation. NAS8- Engineering Model of Improved Diffrac28989. Pratt and Whitney. X74-10095 tion Limited Pulsed Semiconductor Laser 

for Room Temperature Operation. 

CR-120152 December 15, 1973 NAS8-r1974. IBM. X74-10091 

RLIO Derivative, IIA and liB Space Tug 

Engine Turbopump Assembly. NASS- CR-120160 December 28, 1973 

28989. Pratt and Whitney. X74-10096. Evaluation of Shuttle Solid Rocket 

Booster Case Materials. NAS8-27270. 

CR-120153 December 15, 1973 McDonnell-Douglas. N74-20400 

RLIG Derivative, IIA and IB Space Tug 

Engine Thrust Chamber Assembly. CR-120161 February 1974 

NAS8-28989. Pratt and Whitney. Cabin Atmosphere Monitoring System. 

X74-10097 NAS8-30254. Honeywell, Inc. 

CR-120-154 December 15, 1973 CR-120162 October 1973 

RLI0 Derivative, IIA and IIB Space Tug Thermal Conductivity of Hetergeneous 

Engine Extendable Nozzle Assembly. Mixtures and Lunar Soils (Final Report). 

NAS8-28989. Pratt and Whitney. NAS8-26579. Auburn University. 

X74-10098 N74-19579 

47 
CONTRACTOR REPORTS
 

CR-120163 February 1974 CR-120170 November 20, 1973 

Crew Computer Communications Study Software Approach to Automatic 

(Vol. 1, Final Report). NAS8-25701. Patching of Analog Computer. NASSMcDonnell-Douglas. N74-18843 28616. Code Research Corp. N74-19831 

CR-120164 November 1973 CR-120171 December 12, 1973 

Design and Performance of a Large Carbon Monoxide Detector. NASSDiscrete Word Recognition System 29031. Tyco Corp. N74-20012 

(Appendices). NAS8-25701. McDonnellDouglas. N74-18841 CR-120172 August 1973 

Active Cleaning Technique for Removing 

CR-120165 November 1973 Contamination from Optical Surfaces in 

Design and Performance of a Large Space. NASS-26385. The Boeing CornDiscrete Word Recognition System (Vol. pany. N74-20067 

1, Technical Report). NAS8-25701. 

McDonnell-Douglas. N74-18840 CR-120173 January 1974 

Universal Stowage Module for Future 

CR-I 20166 March 11, 1971 Space Exploration. NAS8-29777. Martin 

A Saturn Launched X-Ray Astronomy Marietta. N74-20535 

Experiment (Final Report). NAS8­

21015. SCI Electronics, Inc./University CR-I 20174 October 9173 

of Wisconsin. N74-20468 Study of Helium Emissions from Active 

Solar Regions. NA88-27988. Lockheed 

CR-120167 March 11, 1971 Missiles and Space Co. N74-20456 

A Saturn Launched X-Ray Astronomy 

Experiment (Vol. 11, Final Report). CR-120175 December 21, 1973 

NASS-21015. SCI Systems, Inc./ Extended Definition Feasibility Study 

University of Wisconsin. N74-21428 for a Solar Electric Propulsion Stage 

(SEPS) (Vol. I1). NAS8-27360. Rockwell 

CR-I 20168 February 1974 International Corp. X74-10093 

Shuttle Remote Manned Systems 

Requirements Analysis (Vol. I1). NAS8- CR-120176 December 21, 1973 

29904. Martin Marietta Corp. Extended Definition Feasibility Study 

N74-10085 	 for a Solar Electric Propulsion Stage 

(Vol. 1). NAS8-27360. Rockwell InterCR-120169 April 12, 1973 national Corp. X74-10092 

Investigation of Solidification in Zero 

Gravity Environment-M553 Sphere CR-120177 February 20, 1974 

Forming Experiment. NAS8-28734. 	 Analysis of Requirements for Computer 

University of Connecticut. 	 Control and Data Processing Experiment 

Subsystems. NAS8-25471. Systems 

Development Corp. N74-19833 

48 
CONTRACTOR REPORTS 

CR-120178 December 17, 1973 CR-120188 September 1973 

SUMC Reconfiguration Micro-Assemblier. LOX/GOX Sensitivity of FluorelastoNAS8-27202. McDonnell-Douglas. mes. -NAS8-28898. Stanford Research.. 

'N74-19832 N74-21158 

CR-120180 February 1974 CR-120189 December 1973 

Shuttle Remote Manned Systems Investigations of Atmospheric Dynamics 

'Requirements Analysis (Vol. I). NAS8- Using a CW Doppler Sounder Array 

29904. Martin Marietta. X74-10084 (Final Report). NAS8-27794. 

Rocketdyne Corp. 

CR-120181 February 1974 

Shuttle Remote Manned Systems CR-I20190 May 1972 

Requirements Analysis (Vol. 1II). NASS- Design and Systems Analysis of a 

29904. Martin Marietta. X74-10086 Chemical Interorbital Shuttle (Vol. I, 

Executive Summary). NASS-27670. 

CR-120182 December 1973 North American Aviation. N74-21518 

SUMC/MPOS/HAL Interface Study 

(Final Report). NAS8-29607. Inter- CR-120191 December 1973 

metrics, Inc. N74-20839 Combustion of Metals in Oxygen (Phase 

2, Bulk- Burning Experiments). National 

CR-120183 March 27, 1974 Bureau of Standards. X74-73740 

Linear Test Bed (Vol. II, Final Report). 

NAS8-25156. Rocketdyne. N74-19893 CR-120192 February 1974 

Environmental Design Criteria. NAS8­

CR-I 20184 August 30, 1972 25750. University of Alabama. 

Linear Test Bed (Vol. 1, Final Report). N74-21431 

NAS8-25156. Rocketdyne. N74-19892 

CR-120193 December 1973 

CR-I 20185 December 1, 1973 Turbopumps for Cryogenic Upper Stage 

Research Study on Materials Processing Engines (Final Report). NAS8-27794. 

in Space, Experiment M512 (Final Rocketdyne. N74-21070 

Report). NAS8-28729. Lockheed Missiles 

and Space Co. N74-21068 CR-I 20194 August 31, 1973 

Investigations of the Medical ApplicaCR-420186 September 1973 tions of the Unique Biocarbons DevelGeneral Perturbation Techniques for oped by NASA (Final Project Report). 

Satellite Orbit Prediction. NAS8-28433. NAS8-28620, NAS8-28117. Ranchio Los 

Computer Sciences. N74-10139 Amigos Hospital. N74-20729 

CR-I 20187 September 5, 1973 CR-120195 January 7, 1974 

The Development and Evaluation of Space Shuttle Solid Rocket Booster 

Lubrication Systems for Reusable Space Performance Evaluation Model. NAS8-

Vehicles. NAS8-26282. General Electric. 29643. The Boeing Co. N74-73809 

X74-10140 

49 
CONTRACTOR REPORTS
 

CR-120196 April 1967 CR-120202 October 1973 

Nutator Experimental Program Test Plan. Transient Boiling Heat Transfer in SatuNASS-20378. Bendix Corp. N74-72951 rated Liquid Nitrogen and Fl13 at 

Standard and Zero Gravity. NAS8­

CR-120197 February 1974 20228. University of Michigan. 

Updated Qptical Read/Write Memory N74-21585 

System Components. NAS8-26672. 

Radiation Corp. N74-20841 CR-120203 June 1, 1973 

Technical Manual Maintenance InformaCR-120198 December 1973 tion and Part Index, S-IC Intertank 

Effects of Periodic Plume Pulsing on the Umbilical Carrier and Flight Plate. 

Flow Field Generated by Plume Induced NAS8-5608. The Boeing Company. 

Flow Separation. NAS8-28180. Univer- N74-72944 

sity of Alabama. X74-10089 

CR-120204 December 21, 1973 

CR-120199 July 31, 1973 Design of a Modular Digital Computer 

Dynamic Analysis of a Synthesis of an System. NAS8-27926. Hughes Aircraft. 

Attitude Control System for a Spacecraft N74-20840 

to Rendezvous with Comets and Asteroids (Vol. II, Dynamic Analysis of CR-120205 February 1974 

CARD Vehicle). NAS8-28110. Auburn Conical Isogrid Adapter Structural Test 

University. X74-10116 Results. NAS8-29859. General Dynamics. 

N74-22528 

CR-120200 June 31, 1973 

Dynamic Analysis of a Synthesis of an CR-120206 November 30, 1973 

Attitude Control System for a Spacecraft Specification and Programs for.Computer 

to Rendezvous with Comets and Aster- Software Validation (Final Report). 

oids (Vol. VI, Docking Dynamics of NAS8-28084. Information Research 

Spacecraft with Flexible Appendages). Associates. N74-21831 

NAS8-281 10. Auburn University. 

X74-10177 CR-120207- December 1973 

Photoheliograph Backup ATM lntegral 

CR-120201 July 31, 1973 tion Study (Final Report). NAS8-28082. 

Dynamic Analysis of a Synthesis of an Ball Brothers Corp. X74-10132 

Attitude Control System for a Spacecraft 

to Rendqzvous with Comets and Aster- CR-120208 January 18, 1974 

oids (Vol. V, The Synthesis of an Skylab 2 Ground Winds Data Reduction 

Optimal Spacecraft Attitude Control and Statistical Analysis (Final Report). 

Moment Gyros and Quarternious). NAS8-26703. Baganoff Associates, Inc. 

NAS8-281 10. Auburn University. N74-22495 

X74-10118
 

50 
CONTRACTOR REPORTS
 

CR-120209 October 1973 	 CR-120217 December 1973 

-Liquid Hydrogen Turbopump Rapid Advanced Control Concepts (Final 

Start Program. NAS8-27608. North Report). NAS8-29193. Northrop Service 

American Rockwell Corp. N74-21067 Inc. N74-23385 

CR-120210 CR-120218 January 1974 

Double Time Lag Combustion Instability Manipulator System :Man Machine InterModel for Bipropellant Rocket Engine face Evaluation Program. NAS8-28298. 

(Final Report). NCA8-63. University of Essex Corp. 

Alabama. 

CR-120219 	 January 1974 

CR-120211 January 12, 1970 REST Report Earth Orbiter Teleoperator 

A-Study of the Effect of a Boundary Visual System Evaluation Program. 

Layer Along a Nozzle Wall on the Plume NAS8-28298. Essex Corp. 

Flow Field- NAS8-20082. Lockheed 

Missiles and Space Co. X74-73734 CR-120220 January 1974 

Telecoperator Docking Simulation. 

CR-120212 January 15, 1974 NAS8-28298. Essex Corp. 

Augmented Rigs (Phase 2 Report). TRW 

Systems Group. N74-23042 CR-120221 October 1972 

A Survey of Compatibility of Materials 

CR-120213 April 30, 1973 with High Pressure Oxygen Service (Final 

Development of an Externally Powered Report). NASA Order No. H-92180A. 

Prosthetic Hook for Amputees. NASS- N74-25647 

27020. Rancho Los Amigos Hospital Inc. 

N74-21732 CR-120222 February 9, 1972 

Study on Processing Immiscible Materials 

CR-120214 March 1974 in Zero Gravity. NAS8-28267. TRW. 

Active Control of a Primary Mirror of an N74-74324 

Orbiting Telescope with Thermal 

Citation (Final Report). NAS8-28019. CR-120223 September 1973 

University of Alabama. N74-22099 	 Multifunction Display System (Final 

Report). NAS8-27564. Bendix Corp. 

CR-120215 September 1973 N74-25924 

Comparison of Thruster Configuration in 

Altitude Control Systems. NAS8-26580. CR-120224 May 1974 

Auburn University. 	 Design, Processing, and Testing of LSI 

Arrays for Space Station. NAS12-2207. 

CR-120216 February 4, 1974 RCA Laboratories. 

Applications of Saturn Apollo Automated Data System Capabilities to CR-120226 October 1972 

Problems and Environmental Impacts of Measurement Component Technology 

Urban Transportations. NAS8-28955. (Vol. I, Cryogenic Pressure Measurement 

Louisiana State University. N74-23480 Technology, High Pressure Flange Seals, 

51 
CONTRACTOR REPORTS
 

Hydrogen Embrittlement of Pressure CR-i 20234 May 1974 

Transducer Material, Close Coupled Booster Aerodynamic Heating - Test 

Versus Remote Transducer Installation Support (Final Report). NAS8-28115. 

and Temperature Compensation of Pres- Remisch, Inc. N74-25541 

sure Transducers). NAS7-200. North 

American Rockwell. N74-27185 CR-120235 June 18, 1974 

Research Study on Materials Processing 

CR-1 20227 October 1972 in Space, M566 Experiment. NAS8-

Measurement Component Technology 28724. United Aircraft Research Labora­

(Vol. II, Cryogenic Flow Measurement tories. N74-26981 

and Cryogenic Liquid Detection Measurement Technology). NAS7-200. North CR-120236 January 1974 

American Rockwell. 'N74-27186 Control Trajectory and Loads Optimization. NAS8-28299. Honeywell, Systems 

CR-I 20228 October 1972 & Research Center. 

Measurement Component Technology 

(Vol. III, Cryogenic Temperature Meas- CR-120237 May 1974 

urement and High Temperature Strain LST Secondary Mirror Articulation 

Gage Technology). NAS7-200. North Mechanism (Final Report). NAS8-29723. 

American Rockwell. N74-27187 Perkin-Elmer Corp. N74-27876 

CR-120229 November 19, 1973 CR-120238 May 1974 

Astrionics Systems Designers Handbook Space Station Data Flow (Final Report). 

(Vol. I). NASS-14000. IBM. N74-27365 NAS8-26798. IBM. 

CR-120230 November 19, 1973 CR-120239 February 1974 

Astrionics Systems Designers Handbook Flexible Body/Water Interaction During 

(Vol. 11). NASS-14000. IBM. Water Impact (Final Report). NASSN74-27366 29665. Universal Analytics, Inc. 

CR-120232 May 31, 1974 CR-120240 April 5, 1971 

Design, Fabrication and Test of Light- An Adaptive Control Bibliography. 

weight Shell Structure. NAS8-29979. NAS8-26580. Auburn University. 

Martin Marietta Corp. N74-27408 

CR-120241 April 1974 

CR-I 20233 May 1974 Multi KW DC Power Distribution System 

Neutral Line and Magnetic Field Gra- Study Program. NAS8-28726. TRW Sysdient Plots from Magnetograph Data. tems Group. 

NAS8-26376. Teledyne Brown 

Engineering. 

52 
CONTRACTOR REPORTS
 

CR-120242 May 1966 Residential Heating and Cooling System 

Inviscid Analysis of the Plume Created (Final Report). NAS8-25986. Lockheed 

by Multiple Rocket Eagines (Part 1). Missiles and Space Co. 

NAS8-20101. General Dynamics-Convair. 

CR-120250 October 1973 

CR-120243 December 1973 Radiation Pyrometer for Gas Turbine 

Space Vehicle Engine and Heat Shield Blades (Final Report). NAS8-28953. 

Environment Review (Vol. 1, Engineering Solar Division, International Harvester 

Analysis) (Final Report). NAS8-27802. Co. 

Brown Engineering. 

CR-120251 Novembcr 1973 

CR-120244 January 31, 1974 G-189A Analytical Simulation of the 

Space Tug Storable Engine Study (Vol. Integrated Waste Management Water SysIV, Project Planning) (Final Report). tern Using Radioisotopes for Thermal 

NAS8-29806. Aerojet Liquid Rocket Co. Energy. NAS8-28982. McDonnell 

Douglas Corp. 

CR-120245 January 31, 1974 

Space Tug Storable Engine Study (Vol. CR-120252 December 21, 1973 

III, Engine/Tug Interface and Opera- Extended Definition Feasibility Study 

tional Requirements). NAS8-29806. for a Solar Electric Propulsion Stage 

Aerojet Liquid Rocket Corp. SEPS Concept Definition (Vol. II, Concept and Feasibility Analysis Part 3: 

CR-120246 May 1, 1974 Earth Orbital SEPS). NAS8-27360. 

Research Study on Stabilization and Rockwell International. 

Control. Design of the Large Space 

Telescope Control System. NAS8-29853. CR-120253 June 4, 1971 

Systems Research Lab. Study of Alternate Space Shuttle Concepts (Vo l, LI, Appendix B) (Final 

CR-120247 March 1, 1974 Report). NAS8-26362. Lockheed. 

Design of the Large Space Telescope 

Control System. NAS8-29853. Systems CR-120254 November 15, 1971 

Research Lab. Alternate Concepts Study Extension 

(Vol. II, Concept Analysis and DefiniCR-120248 March 15, 1974 tion, Part 2, One and One-Half Stage 

Development of a Method for Fabri- System). NAS8-26362. Lockheed Missiles 

cating Metallic Matrix Composite Shapes and Space Co. 

by a Continuous Mechanical Process. 

NAS8-27010. Commonwealth Scientific CR-120255 November 15, 1971 

Corp. Alternate Concepts Study Extension 

(Vol. I1, Concept Analysis and DefiniCR-120249 April 1974 tion, Part 3, SRM Boosters). NAS8-

The Development of a Solar Powered 26362. Lockheed Missiles and Space Co. 

53 
CONTRACTOR REPORTS
 

CR-120256 November 15, 1971 CR-120263 April 1974 

Alternate Concepts Study Extension Compiler Writing System Detail Design 

(Vol III: Cost Analysis). NAS8-26362. Specification (Vol. I, Language Spec.). 

Lockheed Missiles and Space Co. NAS8-27202. McDonnell-Douglas Corp. 

N74-27659 

CR-120257 March 16, 1974 

Long Duration Life Tests of Slip Ring CR-120264 April 1974 

Capsule Assemblies for Inertial Guidance Compiler Writing System Detail Design 

Platforms (Final Report). NAS8-29199. Specification (Vol. II, Component SpeciLitton Poly-Scientific. fication). NAS8-27202. McDonnellDouglas Corp. N74-27660 

CR-120258 June 20, 1974 

Development of Methodologies and Pro- CR-120265 September 21, 1972 

cedures for Identifying STS Users and Report on Skylab - M552 Samples. 

Uses (Final Report, Phase I). NAS8- NAS8-28725. Battelle Memorial Inst. 

30533. Stanford Research Inst. 

N74-27456 CR-120266 July 15, 1973 

Materials Processing in Space MS12 to 

CR-120259 June 30, 1974 NASA, Phase B. NAS8-28725. 

Space Shuttle Transportation System 

Techniques for User/Use Development CR-I 20267 

(Final Report). NAS8-30529. Battelle Development of Life Test Methodology 

Columbus Laboratories. N74-28327 for Long Life Mechanical Components, 

Phase I, Development of Methodology,. 

CR-I 20260 November 25, f971 Phase I;, Demonstration of Methodology. 

Alternate Concepts Study Extension NAS8-27438. Battelle Columbus Labs. 

(Vol. Il, Concepts Analysis and Definition, Part 1, 040A System). NAS8- CR-120268 'March 1974 

26362. Lockheed Missiles and Space Co. Interim User's Manual for Boundary 

Layer Integral Matrix Procedure Version 

CR-I 20261 April 1974 J. NAS8-29667. Acurex Corp. 

Users Manual Dynamics of Two Bodies 

Connected by an Elastic Tether Six CR-120269 January 31, 1974 

Degrees of Freedom Forebody and Five Study of Design and Control of Remote 

Degrees of Freedom Decelerator. NAS8- Manipulators Modeling Manipulator Arms 

29144. Goodyear Aerospace Corp. with Distributed Flexibility for Design 

and Control. NAS8-28055. Massachusetts 

CR-I 20262 September 1, 1971 Institute of Technology. 

Alternate Space Shuttle Concepts Study 

Interim Review Presentation. NASS- CR-120270 July 30, 1973 

26362. Lockheed Missiles and Space Co. Design Process Development Manufacture 

54 
CONTRACTOR 

Test and Evaluation of Boron Aluminum 

for Space Shuttle Components. NAS8-

27735. McDonnell-Douglas Corp. 

CR-120271 December 21, 1973 

Extended Definition Feasibility Study 

for a Solar Electric Propulsion Stage 

SEPS Concept Definition (Vol. Ii, Concept and Feasibility Analysis, Part 2, 

SEPS Design). NAS8-27360. Rockwell 

International. 

CR-120272 March 1974 

Holographic Optical Elements, Fabrication and Testing. NAS8-28949. Radiation Div., Electro Optics Operation. 

CR-120273 December 1973 

Research Study on Material Processing 

Space Skylab Experiment M553 Sphere 

Forming. NAS8-28723. A. D. Little, Inc. 

CR-120274 January 31, 1974 

Space Tug Storable Engine Study (Vol. 

V, Program Cost Estimates) (Final 

Report). NAS8-29806. Aerojet Liquid 

Rocket Co. 

CR-120275 December 31, 1972 

Design and Fabricate a Pair of Rancho 

Anthropomorphic Manipulator (Final 

Report). NAS8-28361. Rancho Los 

Amigos Hospital, Inc. N74-27568 

CR-120276 April 1974 

Development of a Miniature Solid Propellant Rocket Motor for Use in Plume 

Simulation Studies. NAS8-26701. 

Calspan Corp. 

CR-120277 November 1973 

Design Evaluation and Recommendation 

Effort Relating to the Modification of a 

REPORTS 

Residential 3 Ton Absorption "Cycle 

Cooling Unit for Operation with Solar 

Energy. NAS8-25996. Arkla Industries. 

Inc. 

CR-120278 September 1973 

Application of Remote Sensing to 

Hydrology. NAS8-24000. IBM Corp. 

N74-27811 

CR-120279 February 1974 

Design Manufacture Development Test 

and Evaluation of Boron Aluminum 

Structural Components for Space Shuttle 

(Vol. III, Shear Beam Component Test 

and Analysis). NAS8-27738. General 

Dynamics Corp. 

CR-120280 November 1, 1973 

External Tank Project New Technology 

Plan. NAS8-30300. Martin Mrietta 

Corp. 

CR-120281 April 1974 

Filter Studies in HEL and CAl 1. NASS28021. Lockheed. 

CR-120282 December 6, 1973 

Development and Implementation of the 

Algorithms for -the PCS Program (Final 

Report). NAS8-29899. M&S Computing, 

Inc. 

CR-120283 April 23, 1973 

Study for Identification of Beneficial 

Uses of Space, Phase I (Final Report), V. 

2, BK. 1, Technical Report - Introduction, Methodology, Results. NAS8­

28179. General Electric, Space Div. ; 

CR-120284 April 23, 1973 

Study for Identification of Beneficial 

Uses of Space, Phase I (Final Report) V. 

55 
CONTRACTOR REPORTS
 

2, BK. 2, Technical Report - Introduc- for the HEAO Program. NAS8-28265. 

tion, Methodology, Results. NAS8- Bedford Engineering Corp. N74-27684 

28179. General Electric Space Div. 

CR-120292 March 1974 

CR-120285 November 1, 1973 Laboratory Demonstration Model Active 

Study for Identification of Beneficial Cleaning Technique Device (Final 

Uses of Space, Phase 11 (Final Report, Report). NAS8-28270. Boeing Aerospace 

Vol. 1, Executive Summary). NAS8- Co. 

28179. General Electric Space Div. 

N74-28446 CR-120293 July 1972 

Manipulation of Particles by Weak 

CR-120286 November 1, 1973 Forces in Zero G Environment, a Report 

Study for Identification of Beneficial on a 'Study Carried Out for the Space 

Uses of Space, Phase II (Final Report, Systems Products Department of GE. 

Vol. 11, BK. 1, Technical Report). NAS8-28179. General Electric Corp. 

NAS8-28179. General Electric Space Div. 

N74-28447 CR-120294 April 1974 

Design and Fabrication of Prototype 

CR-120287 November 1, 1973 System for Early Warning of Impending 

Study for Identification of Beneficial Bearing Failure. NAS8-25706. MechanUses of Space, Phase 11, (Final Report, ical Technology, Inc. 

Vol. 11, BK. 2, Technical Report -

Appendices). NAS8-28179. General CR-i 20295 May 1974 

Electric Space Div. Computer Automation of Ultrasonic 

Testing (Final Report). NAS8-28652. 

CR-i 20288 September 24, 1973 General Dynamics/Convair Aerospace 

Report on Skylab M551 . Samples. Div. 

NAS8-28725. Battelle Memorial Institute. CR-120296 June 1974 

Immiscible Alloys - Ground Based 

CR-120289 February 1974 Studies. NAS8-27809. University of 

Improved Integrated Real Time Con- Alabama in Huntsville. 

tamination Monitor. NAS8-28987. 

General Dynamics. CR-l 20297 April 1974 

Manned Earth Observatory: Mission 

CR-I 20290 February 1974 Requirements and Preliminary Design 

Summary of Solid Rocket Motor Plume (Final Report, Vol. I, Executive Sum-_ 

Flowfield and Radiation Analysis. mary). NAS8-28013. TRW. 

NAS8-28609. Lockheed. 

CR-I 20298 April 26, 1974 

CR-120291 January 1974 Manned Earth Observatory: Mission 

Photomultiplier Tube Reliability Study Requirements and Preliminary Design 

56 
CONTRACTOR REPORTS
 

(Final Report, Vol. 1I, Study Results). CR-120307 June 2, 1971 

NAS8-28013. TRW. Study of Alternate Space Shuttle Concepts, Col. tII, Program Planning Data. 

CR-120200 December 1973 NAS8-26362. Lockheed Missiles and 

Study and Design of Cryogenic Pro- Space Co. 

pellant Acquisition Systems, Vol. I, 

Design Studies. NAS8-27685. CR-1 20308 February 1974 

McDonnell-Douglas. Crew/Computer Communications Study, 

Vol. 111, Appendices. NAS8-25701. 

CR-120301 December 1973 McDonnell-Douglas Co. 

Study and Design of Cryogenic Propellant Acquisition Systems, Vol. It, CR-1 20309 April 1974 

Supporting Experimental Program. Space Tug Thermal Control Equipment 

NAS8-27685. McDonnell-Douglas. Thermal Requirements Characteristics 

and Constraints, Catalogue Users Guide. 

CR-120302 February 23, 1973 NAS8-29670. Martin Marietta Corp. 

Nigh Bit Rate Mass Data Storage Device 

(Final Report). NAS8-28959. Leach CR-1 20310 April 1974 

Corp. N74-2766 1 Space Tug Thermal Control Equipment 

Thermal Requirements Characteristics 

CR-120303 April 1974 and Constraints, Catalogue. NAS8-29670. 

Vacuum Distillation/Vapor Filtration Martin Marietta Corp. 

Water Recovery. NAS8-27467. General 

American Transportation Corp. CR- 2031 1 May 1974 

Draw Forming of Scale Shuttle External 

CR-1 20304 September 1973 Tank Dome Gore. NAS8-30666. 

Ku Band Receiver Development (Final McDonnell-Douglas Astronautics Co. 

Report). NAS8-28719. ITT. 

CR-I 20312 May 1974 

CR-I 20305 December 21, 1973 A Fast-Initializing Digital Equalizer with 

Extended Definition Feasibility Study On-Line Tracking for Data Communicafor a Solar Electric Propulsion Stage tions. NAS8-20172. University of 

SEPS Concept Definition, Vol. III, Alabama. 

Program Planning Data. NAS8-27360. 

Rockwell International. CR-120313 July 9, 1974 

Further Analysis of Field Effects on 

CR-120306 June 4, 1971 Liquids and Solidification. NAS8-28664. 

Study of Alternate Space Shuttle Con- Boeing Aerospace Co. 

cepts, Vol. 11, Appendix A, Task I 

Droptank Impact and Dispersion Study. CR-1 20314 June 1973 - June 1974 

NAS8-26362. Lockheed Missiles and Analytics of Crystal Growth in Space. 

Space Co. NAS8-29847. University of Southern 

California. 

57 
CONTRACTOR REPORTS
 

CR-I 20315 January 25, 1974 Potential Contaminants in Limestone 

Saturn S-IB Stage Final Flight Report Aquifiers (Final Report). NAS8-30216. 

Applicable to Skylab 4. NAS8-4016. University of Alabama. 

Chrysler Corp. 

CR-120323. September 24, 1973 

CR-I 20316 January'15, 1974 Study on the Effect of Contamination 

SL-4 SA-208 Launch Vehicle Postflight on the Performance of X-Ray Telescope 

Trajectory, Part 4. NAS8-4016. Chrysler (Final Report). NAS8-28083. Visidyne, 

Corp. Inc. 

CR-120317 November 30, 1973 CR-120324 November 1973 

Analysis of the Relativistic Orbiting Mathematical Research on Spline FuncGyroscope Experiment (Final Report). tions. NAS8-27181. University of 

NAS8-29900. University of Alabama. Alabama, 

CR-120318 November 27, 1973 CR-120325 January 1970 

Specification Cost Implementation Study Dual Mode Manned Automated Lunar 

Program for NASA/MSFC. NAS8-29741. Roving Vehicle Design Definition Study. 

Metek Calmec. NAS8-24528. Bendix Corp.. 

CR-120319 March 1974 CR-120326 February 1974 

Water Impact Analysis of Space Shuttle Parachute Dynamics and Stability Anal-


Solid Rocket Motor by the Finite ysis (Final Report). NAS8-28607.
 

Element Method (Final Report). NAS8- Honeywell, Inc.
 

29195. Marc Analysis Research Corp.
 

CR-I 20327 April 1974 

CR-120320 February 1974 Multiple IMU System Software Design 

Attitude Control Concepts for Precision and Coding, Vol. 1II. NAS8-27624. The 

Pointing Nonrigid Spacecraft (Final Charles Stark Draper Lab. 

Report). NAS8-28358. University of 

California. CR-l 20328 October 1973 

Actuator Digital Interface Unit AIU 

CR-120321 November 1, 1973 (Final Report). NAS8-26755. Electron 

Research Study on Stabilization and Communication Inc. 

Control Modern Sampled-Data Control 

Theory, Continuous and Discrete CR-120329 December 15, 1973 

Describing Function Analysis of the LST Study of Effects of Uncertainties on 

System. NAS8-29853. Systems Research Comet and Asteroid Encounter and 

Lab. Contact Requirements (Final Report,-

Part 1, Guidance and Navigation 

CR-120322 November 21, 1973 Studies). NAS8-27664. Auburn 

Study to Define Points of Entry for University. 

58 
CONTRACTOR REPORTS
 

CR-120330 May 3, 1974 CR-124289 October 23, 1964 

Study of Effects of Untertainties on Saturn V Laboratory Maintenance 

Comet and Asteroid Encounter and Instruction Got LTE. NAS8-11561. IBM. 

Contact Guidance Requirements (Final 

Report, Part 2, Tumbling Problem CR-i 24290 June 1973 

Studies). NAS8-27664. Auburn Univer- Investigation into the High-Temperature 

sity. Strength Degradation of FiberReinforced Resin Composites during 

CR-120331 January 1, 1974 Ambient Aging. NAS8-27435. Convair. 

Research Study on Stabilization and Div. N73-26583 

Control Modern Sampled Data Control 

Theory (Final Report). NAS8-29853. CR-124291 October 23, 1964 

Systems Research Lab. Saturn V Launch Vehicle Digital Computer and Launch Vehicle Data Adapter 

CR-I 20332 January 1974 Test Equipment. NAS8-11561. IBM. 

Process Development of Beam-Lead N73-73587 

Silicon-Gate COS/MOS Integrated Circuits (Final Report). NAS8-26594. RCA. CR-124292 March 5, 1965 

'Saturn V Launch Vehicle Digital ComCR-I 20333 October 1973 puter and Launch Vehicle Data Adapter 

Carbon Thin Film Thermometry (Final Test Equipment. NAS8-11561. IBM. 

Report). NASA Order H-92167-A. N73-73588 

National Bureau of Standards. 

CR-124293 March 5, 1965 

CR-120334 September 1973 Saturn V Launch Vehicle Digital ComDesign Testing and Delivery of an puter and Launch Vehicle Data Adapter 

Interactive Graphics Display Subsystem Test Equipment. NAS8-11561. IBM. 

(Final Report). NAS8-28436. Vanzetti N73L73586 

infrared & Computer Systems, Inc. 

CR-I 23294 May 9, 1973 

CR-120335 February 22, 1974 Study of Liquid Solid Transition for 

Vessel Pressure Gas Storage Arde PIN Materials Processing in Space. NASSD3870 (Revision "A, NASA PIN 28664. Boeing Co. N73-27596 

20M33152). NASS-29186. Arde, Inc. 

CR-124295 September 15, 1972 

CR-124288 July 1, 1973 Field Repair of Coated Columbium 

Marshall System for Aerospace System Thermal Protection Systems. NAS8-

Simulation (MARSYAS), User's Manual. 26121. McDonnell-Douglas Corp. 

NAS8-21805. Computer Sciences Corp. N73-27809 

N73-26252 

59 
CONTRACTOR REPORTS
 

CR-124296 April 24, 1973 CR-124304 June 1973 

Vibration Testing of the RFW 017770-1 Cost Analysis of Oxygen Recovery SysSTS Circuit Breaker Panel. NAS9-6555. tems. NAS8-28377. McDonnell-Douglas 

McDonnell Douglas Corp. N73-73578 Corp. N73-27075 

CR-124297 February 1973 CR-l24305 June 1973 

Turbopumps for Cryogenic Upper Stage Cost Analysis of Life Support Systems. 

Engines. NAS8-27794. Rocketdyne Corp. NAS8-28377. McDonnell-Douglas Corp. 

N73-73362 N73-27072 

CR-124298 CR-I 24306 June 1973 

Space Shuttle Attitude Control System Cost Analysis of Atmosphere Monitoring 

ACS Thruster Penetration Heating. Systems. NAS8-28377. McDonnellNAS8-27683. General Dynamics Corp. Douglas Corp. N73-27076 

CR-124299 May 30, 1973 CR-i 24307 June 25, 1973 

Active Standby Servovalve Actuator Design of a Terminal Pointer Hand 

Development. NAS8-27838. Hydraulic Controller for Teleoperator Applications. 

Research Man. Co. N73-27418 NAS8-28760. URS/Matrix Co. 

N73-27419 

CR-124300 June 1973 

Acoustic Processing Method for MS/MS CR-i 24308 

Experiments. NAS8-29030. Interand Analysis of Propellant Feedline DynamCorp. N73-28671 ics. NAS8-25919. Southwest Research 

Institute. N73-29188 

CR-124301 March 23, 1973 

Study and, Development of a Cryogenic CR-124309 June 1973 

Heat Exchanger for Life Support Sys- Atom Beam Surface Interaction Studies. 

tems. NAS8-28099. Airesearch Manu- NAS8-28071. University of Alabama in 

facturing Co. N73-27071 Huntsville. N73-28850 

CR-124302 June 1973 CR-124310 January 31, 1973 

Cost Analysis of Carbon Dioxide Con- Application of RLl0 Engine for Space 

centrators. NAS8-28377. McDonnell- Tug Propulsion. NAS8-293,14. P&W'Airc. 

Douglas Corp. N73-27073 X73-10395 

CR-124303 June 1973 CR-124311 February 26, 1965 

Cost Analysis of Water Recovery Sys- Laboratory Maintenance Instructions. 

tems. NAS8-28377. McDonnell-Douglas Saturn V Launch Vehicle Data Adapter 

Corp. N73-27074 Simplex Models. NAS8-11561. IBM. 

N73-73558 

60 
CONTRACTOR REPORTS
 

CR-124312 February 8, 1973 CR-124321 April 1973 

An Efficient Numerical Technique for Shuttle Orbital Applications and 

Calculating Thermal S Reading Resist- Requirements SOAR. NAS8-28583. 

ance. NAS8-28516. General Electric Co. McDonnell-Douglas Corp. X73-10409 

CR-124313 February 26, 1965 CR-124322 June 1973 

Laboratory Maintenance Instructions. Performance of Statistical Energy AnalySaturn V Launch Vehicle Data Adapter sis. NAS8-28435. McDonnell-Douglas 

Simplex Models. NAS8-11561. IBM. Corp. N73-28890 

N73-73559 

CR-124323 April 10, 1973 

CR-124314 May 9, 1973 Hardware Design Integrity Review. SCI. 

Development of Isothermal Rigs. NAS8- X73-77948 

-28574. TRW. N73-28500 

CR-124324 April 1972 

CR- 124315 May 1973 Shuttle Orbital Applications and 

Shuttle Orbital Applications and Requirements SOAR. NAS8-28583. 

Requirement SOAR. NAS8-28583. McDonnell-Douglas Corp. X73-10405 

McDonnell-Douglas Corp. X73-10406 

CR-1 24325 April 1973 

CR-124316 April 1973 Shuttle Orbital Applications and 

Shuttle Orbital Applications and Requirements SOAR. NAS8-28583. 

Requirements. NAS8-28583. McDonnell- McDonnell-Douglas Corp. X73-10408 

Douglas. X73-10407 

CR-124326 April 1973 

CR-124317 April 1973 Shuttle Orbital Applications and 

Shuttle Orbital Applications and Requirements SOAR. NASS-28583. 

Requirements SOAR. NAS8-28583. McDonnell-Douglas Corp. 

McDonnell-Douglas Corp. X73-10404 

CR-I 24327 April 1973 

CR-124318 April 1973 Shuttle Orbital Applications and 

Shuttle Orbital Applications and Requirements SOAR. NAS8-28583. 

Requirements SOAR. NAS8-28583. McDonnell-Douglas Corp. X73-10400 

McDonnell-Douglas Corp. X73-10402 

CR-124328 April 1973 

CR-124319 April 1973 Shuttle Orbital Applications and 

Shuttle Orbital Applications and Requirements SOAR. NAS8-28583. 

Requirements SOAR. NAS8-28583. McDonnell-Douglas Corp. X73-10403 

McDonnell-Douglas Corp. X73-10401 

CR-124329 June 1973
 

CR- 124320 April 1973 Convection in Skylab M512 Experiments 

Shuttle Orbital Applications and M551, M552, and M553. NAS8-27015. 

Requirements. NAS8-28583. McDonnell- Lockheed. N73-28852 

Douglas Corp. X73-10410 

61 
CONTRACTOR REPORTS
 

CR-124330 June 1973 CR-124338 May 31, 1973 

Development of Multiple User Amtram Mission Requirements for a Manned 

on the Data Craft DC 6024. NAS8- Earth Observatory. NAS8-28013. TRW. 

26756. Teledyne Brown Engineering Co. N73-28848 

N73-28052 

CR-124339 May 31, 1973 

CR-124331 May 31, 1973 Mission Requirements for a Manned 

Cost Analysis of Atmosphere Monitoring Earth Observatory. NAS8-28013. TRW 

Systems. NAS8-28377. McDonnell- Systems Group. N73-28849 

Douglas Corp. N73-28622 

CR-124340 May 31, 1973 

CR-124332 April 30, 1973 Mission Requirements for a Manned 

Detection of Lack of Fusion Using Earth Observatory. NAS8-28013. TRW 

Opaque Additives. NAS8-28708. Systems Group. N73-28847 

McDonnell-Douglas Corp. N73-27420 

CR-124341 November 1, 1971 

CR-124333 July 13, 1973 A Method for Determining the Response 

Development of a Width-Modulated Pulse of Space Shuttle to Atmospheric TurbuRebalance Electronics Loop for Strap- lence. NAS8-26363. General Dynamics. 

down Gyroscopes. NAS8-27296. Univer- N73-29876 

sity of Tennessee. N73-28649 

CR-i 24342 June 1973 

CR-I24334 May 31, 1973 Apollo Telescope Mount SEC Camera 

Investigation of Uses of Molographic -Tube Spares Program. NAS8-29063. 

Optical Elements. NAS8-28949. Harris- Westinghouse. N73-28087 

Electro Optics Center of Radiation. 

N73-28555 CR-I 24343 May 30, 1973 

Design Study of the Television System 

CR-124335 March 1973 for the Large Space Telescope. NGRActive Cleaning Technique Device. 31-001-276. Princeton University. 

NAS8-28270. Boeing Co. N73-30696 X73-10447 

CR-124336 May 21, 1971 CR-124344 December 6, 1971 

High Energy Astronomy Observatory Alternate Concepts Study Extensions. 

Missions A and B Phase C/D Appendix NAS8-26362. Lockheed Missiles and 

7: Orbit Adjust Stage Data. NASS- Space Co. N73-33829 

26492. Lockheed. X73-78696 

CR-124345 November 15, 1971 

CR-124337 May 31, 1973 Alternate Concepts Study Extension. 

Statistical Determination of Space NAS8-26362. Lockheed Missiles and 

Shuttle Component Dynamic Magnifica- Space Co. N73-30844 

tions Factors. NAS8-28650. Boeing Co. 

N73-30842 

62 
CONTRACTOR REPORTS
 

CR-124346 May 1973 CR-124353 February 15, 1973 

Prediction of Fluctuating. Pressure Envi- Design and Fabrication of a Dynamically 

ronment Associated with Plume Induced Scaled Space Shuttle Ground Wind 

Separated Flow Fields. NAS8-26919. Loads. NAS8-26838. McDonnell-Douglas 

Wyle Lab. N73-28922 Corp. X73-10514 

CR-124347 June 1973 CR-124354 May 21, 1973 

Prediction of Space Shuttle Fluctuating Study of Single Crystals of Metal Solid 

Pressure Environments Including Rocket Solutions. NAS8-29077. Eagle-Pitcher 

Plume Effects. NAS8-26919. Wyle Lab. Industries Inc. N73-29532 

N73-29885 

CR-124355 June 1973 

CR-124348 June 1973 A Comparison of a Coaxial Focused 

Measurements of the Michigan Airglow Laser Doppler System in Atmospheric 

Observatory From 1971 to 1973 at Ester Measurements. NAS8-26234. Colorado 

Dome Alaska. NAS8-20592. Michigan State University. N73-3P627 

University. N73-30351 

CR-124356 April 1973 

CR-124349 1973 Development of Guidelines for the 

Research Study on Antiskid Braking Definition of the Relevant Information 

Systems. NAS8-27864. Boeing Co. Content in Data Classes. NAS8-28264. 

N73-28449 State University of New York. 

N73-29990 

CR-124350 March 1, 1967 

Mobility Dynamics Analysis and Test of CR-1 24357 

the Lunar Scientific Survey Module. Model 8414 Low Thrust Throtleable 

NAS8-20073. Brown Engineering. Engine Performance Evaluation Program 

N73-73568 (Final Report). NAS8-20086. Bell Aerosystem Corp. X73-78174 

CR-124351 June 29, 1973 

Design of Dynamic Model for Investi- CR-124358 June 1973 

gating Ground Wind Effects on Space Segregation Effects During Solidification 

Shuttle Vehicle. NAS8-26901. Rowkwell in Weightless MELTS (Final Report). 

International Corp. X73-10507 NAS8-28891. Grumman Aerospace Corp. 

N73-30510 

CR-124352 June 1,973 

Time Exposure Studies on Stress Corro- CR-124359 November 1972 

sion Cracking of Aluminum 2014-T6, Study of Electro Optic Materials Tech2219-T87, 2014-T651, 7075-T651, and nology (Final Report). NAS8-27681. 

Titanium 6A1-4V. NGR-19-011-009. Georgia Institute of Technology. 

Grambling College. N73-29531 X73-1,0455 

63 
CONTRACTOR REPORTS
 

CR-124360 CR-124368 May 31, 1973 

Multiple Shape Beam Antenna Study. Mission Requirements for a Manned 

NAS8-28832. TRW Systems Group. Earth Observatory Task 1 Experiment 

Selection Definition and Documentation. 

CR-124361 March 1973 NAS8-20813. TRW System Group. 

Definition of a Sellar Tracking Attitude N73-31751 

Reference System Experiment for a 

Communication Navigation Research CR-124369 October 1972 

Laboratory. NAS8-28806. Hughes Air- The Effects of Elevated Temperatures on 

craft Corp. X73-10448 the Structural Properties of Fiber Composite Materials Suitable for Use in. 

CR-1 24362 March 1973 Space Shuttle and Other Space Vehicles. 

Definition of Stellar Tracking Attitude NCA8-65. University of Tennessee. 

Reference System Experiment for a N73-30541 

Communication Navigatib)n Research 

Laboratory. NAS8-28806. Hughes Air- CR-124370 June 29, 1973 

craft Corp. X73-10496 Aerolastic Effects on Space Shuttle 

Dynamics (Final Report). NAS8-26363. 

CR-124363 February 1973 General Dynamics Corp. N73-31781 

Multiple Shaped Beam Antenna Study. 

NAS8-28832. TRW Systems Group. CR-124371 1972 

X73-10491 	 SUMC Multiprocessing Operating System 

MPOS Requirements Document. NAS8­

CR-1 24364 29072. RCA Corp. N73-30147 

Phase Array Antenna Comparison 

Studies. NAS8-21481. Martin Marietta CR-124372 April 17, 1973 

Corp. X73-78699 Design, Fabrication, Testing, and 

Delivery of a Feasibility Model LamiCR-124365, January 1973 nated Ferite. NAS8-27596. Ampex Corp. 

Preparation of Composite Materials in California. N73-30149 

Space. NAS8-27806. General Dynamics. 

N73-30,542 CR-124373 June 15, 1973 

Vacuum Jacketed Ducting Technology 

CR-124366 February 1973 Investigation (Interin Report). NAS8-

Methodology for a Decision on the 27504. General Dynamics Corp. 

Static Test of Large Vehicles. NASS- X73-10497 

26918. Technology Incorporated. 

N73-30866 CR-1 24374 1973 

Active Cleaning Techniques for 

CR-124367 May 16, 1973 Removing Contamination From Optical 

Space Shuttle Damper System for Surfaces in Space. NAS8-26385. Boeing 

Ground Wind Load Tests. NAS8-28613. Aerospace Corp. N73-30697 

Applied Dynamics Research Corp. 

N73-30845 

64
 
CONTRACTOR REPORTS 

CR-124375 August 1, 1973 CR-124383 May 30, 1973 

Electro-Optical Processing of Phased Combined Loading Criteria Influence on 

Array Data. NASS-28737. Carnegie Structural Performance. NAS8-26919. 

Mellon University. N73-30121 Conviar. X73-10506 

CR-124376 May 13, 1973 CR-124384 1973 

Bellows Flow Induced Vibration and Zero Leakage Separable and SemipermaPressure Loss (Final Report). NAS8- nent Ducting Joints. NAS8-2815.9. 

21133. Southwest Research Institute. Wilpac Man. Co. 

X73-10492 

CR-124385 June 15, 1973 

CR-124377 January 1972 Space Processes for Extended Low-G 

Space Base Preliminary Nuclear Safety Testing. NAS8-28615. Convair, Call--._ 

Analysis. NAS8-26283. General Electric. fornia. N73-31752 

X73-80704 

CR-124386 1973 

CR-1 24378 January 1973 Zero Leakage Separable and SemipermaSpace Shuttle Nuclear System Transpor- nent Ducting Joints. NAS8-28159. 

tation. NAS8-20283. General Electric. Wilpac Mart. Co. N73-31780 

CR-124379 April 1973 CR-124387 Januiary 1973 

Shuttle Orbital Applications and Development of Methods for the 

Requirements SOAR Phase 2, Vol. 1, Dynamic Analysis of Flexible BodyJ_ 

Book 1, System Analysis and Require- Water Interaction During Water Impact. 

ments. NAS8-28583. McDonnell-Douglas NAS8-2852. Universal Analytics, Inc. 

Corp. X73-10526 

CR-124380 July 19, 1973 CR-124388 May 1973 

Design and Development of Pressure and Development of Advanced Materials 

Repressurization Purge System for Composites for Use on Insulations for 

Reusable Space Shuttle Multilayer Insu- LH2 Tanks. NAS8-25973. McDonnelllation Systems. NAS8-27419. General Douglas Astronautics Co. N73-31532 

Dynamics California. N73-31782 

CR-124389 May 1973 

CR-124381 June 1973 Development of High Temperature 

On Particle Track Detectors. NASS- Silicone Adhesive Formulations for 

26758. University of San Francisco. Thermal Protection System Applications. 

N73-31415 NAS8-28113. General Electric Corp. 

N73-31533 

CR-124382 June 1973
 

Floating Point System Quantization CR-124390 July 31, 1973 

Errors in Digital Control Systems, SSME Structural Computer DevelopNAS8-28262. Auburn University. ment. NAS8-29821. The Boeing Co. 

N73-31145 N73-31805 

65 
CONTRACTOR REPORTS
 

CR-124391 July 31, 1973 ConditionerlMonitor Unit and BreadSSME Structural Computer Program board State of Charge Indicator. NAS8-

Development. NA88-29821. The Boeing 28426. Chrysler Corp. X73-10475 

Co. N73-31806 : 

CR-124399 July 1973 

CR-124392 July 31, 1973 Study of an lnstrument for Sensing 

SSME Structural Computer Program Errors in a Telescope Wavefront. NASSDevelopment. NAS8-29821. The Boeing 27863. University of Arizona. 

Co. N73-31807 N73-32366 

CR-124393 CR- 124400 August 1973 

Computer Enhancement of Radiographs. Investigation of High Performance InsulaNAS8-28521. Mead Technology Labs., tion Application Problems. NAS8-21400. 

Dayton, Ohio. N73-31414 McDonnell-Douglas Corp. N73-32824 

CR-124394 June 31, 1973 CR-124401 August 1973 

Properties of Materials in High Pressure Test Fixture Design for Boron AlumiHydrogen at Cryogenic Room and Ele- num and Beryllium Test Panels. NAS8­

vated Temperatures. NASS-26191. P&W 29901. Teledyne Brown Engineering 

Corp. N73-31804 Corp. N73-32337 

CR-124395 November 15, 1966 CR-124402 July 31, 1973 

Definition of Experiment Program in Development of Life-Test Methodology 

Space Operations Techniques and Sub- for Long-Life Mechanical Components 

systems Independent Manned Manipula- Phase 1: Development of Mathodology. 

tor IMM. NAS8-20316. LTV Aerospace NAS8-27438. Battelle. X73-10493 

Corp. X73-79500 

-CR-124403 August 1973 

CR-1 24396 August 1973 Methods of Treating Complex Space 

Research Study of Materials Processing Vehicle Geometry for Charged Particle. 

in Space Experiment M512. NAS8- NAS8-28177. Science i Applications 

28729. Lockheed Missiles and Space Co. Incorp. N73-3255.1 

N73-32368 

CR-124404 August 11, 1973 

CR-124397 June 1973 Criteria for Structural Test. NAS8-

Vacuum Distillation Vapor Filtration 29070. Boeing Aerospace Corp. 

Water Recovery for Phases I and 2. N73-32799 

NAS8-27467. Gen. Amer. Trans. Corp. 

N73-32367 CR-124405 September 1973 

Solid State, S-Band Amplifier. NAS8­

CR-124398 June 1973 28763. ITT Defense Communications. 

Program Report for a Breadboard N73-32115 

Rechargeable Silver Zinc Battery 

66 
CONTRACTOR REPORTS
 

CR-124406 August 1973 CR-124413 August 1973 

Design Manufacture, Development Test Life Sciences Payload Definition and 

and Evaluation of Boron Aluminum Integration Study. NASS-29150. General 

Structural Components for Space Dynamic Corp. N73-32768 

Shuttle. NAS8-27738. General Dynamics. 

X73-10011 CR-124414 August 1973 

Life Sciences Payload Definition Study. 

CR-124407 June 15, 1973 NAS8-29150. General Dynamic Corp. 

Development of a Method for Fabrica- N73-32767 

ting Metalic Matrix Composite Shapes 

by a Continuous Mechanical Process. CR-124415 July 8, 1973 

NAS8-27010. Commonwealth Scientific Evaluation of MSFC STD 486 Threaded 

Corp. N73-31370 Fasteners, Torque Limits for Use in the 

Construction of Aerospace Vehicles. 

CR-124408 August 1973 NASS-5608. The Boeing Company. 

Design Manufacture Development Test N73-32764 

and Evaluation of Boron Aluminum 

Structural Components for Space CR-124416 June 1973 

Shuttle. NAS8-27738. General Dyanmics. A Study of Numerical Methods of 

X74-10012 	 Solution of the Equations of Motion of 

a Controlled Satellite Under the InfluCR- 124409 August 3 1, 1973 ence of Gravity Gradient Torque. NAS8-

Development of Flight Experiment Work 28833. Mississippi State University. 

Performance and Workstation Interface N73-32762 

Requirements. NAS8-28359. Matrix 

Corp. N73-32733 CR-I 24417 June 4, 1971 

Study of Alternate Space Shuttle ConCR-124410 October 1973 cepts. NAS8-26362. Lockheed Missiles 

Influence of Gaseous Hydrogen on and Space Co. N73-32772 

Metals. NAS8-25579. Rocketdyne. 

N73-32428 CR-I 24418 June 28, 1973 

Study of Alternate Space Shuttle Con-' 

CR-124411 August 1973 cepts. NAS8-26362. Lockheed Missiles 

Life Sciences Payload Definition and and Space Co" N73-32775 

Integration Study. NAS8-29150. General 

Dynamic Corp. N73-32765 CR-124419 April 19, 1973 

Aerodynamic 	 Characteristics of 

CR-124412 August 1973 Lockheed Delta-Body Orbiter and StageLife Sciences Payload Definition and and-One-Half Launch Vehicle. NASSIntegration Study. NAS8-29150. General 26362. Lockheed Missiles and Space Co. 

Dynamics. N73-32766 N73-32770 

67 
CONTRACTOR REPORTS
 

CR-124420 July 11, 1970 in Clean Metallic Thin Films by a 

Executive Review Presentation Alternate Gaseous Environment (Final Report). 

Space Shuttle Concepts. NAS8-26362. NGR-01-007-004. 

Lockheed Missiles and Space Co. 

N73-73949 CR-i 24428 July 18, 1973 

Omni-Axis Secondary Injection Thrust 

CR-124421 June 18, 1971 Vector Control System. NAS8-28887. 

Study of Alternate Space Shuttles Con- E-Systems Inc. N73-32761 

cepts (Final Report). NAS8-26362. 

Lockheed Missiles and Space Co. CR-i 24429 August 1973 

N73-32774 	 Analytical Study of the Large Orbital 

X-Ray Telescope Imaging System. 

CR-122422 June 4, 1971 NAS8-29855. University of Montivallo. 

Study of Alternate Space Shuttle Con- N73-32338 

cepts, Vol. 11 - Part 11 Concept Analysis 

and Definition. NAS8-26362. Lockheed CR-124430 June 1973 

Missiles and Space Co. N73-32773 Payload Carrier Simulator Man Systems 

Program Integration. NAS8-28512. 

CR-124423 June 1973 University of Alabama. N73-32018 

Development of Techniques and Associated Instrumentation for High Tern- CR-124431 October 18, 1973 

perature Emissivity Measurements. Shuttle Orbital Applications and 

NAS8-26304. Lockheed Missiles and Requirements-Supplementary Tasks 

Space Co. N73-32339 (SOAR-IIS, Final Report). NAS8-28583.. 

McDonnell-Douglas 	Corp. N73-32771 

CR-124424 June 15, 1973 

A Study of Computer Output Microfilm CR-124432 June 1971 

Equipment and Technology (Final Synthesis of Ninhydrin Analogs for Use 

Report). NAS8-28467. N73-32763 in the Identification of Amino Acids 

(Final Report). NGR-01-006-001. 

CR-124425 April 20, 1973 Oakwood College. 

Design, Fabrication, Testing, and 

Delivery of Shuttle Heat Pipe Leading CR-1 24433 June 1973 

Edge Test Modules (Vol. 1). NAS8- A Study of the Potential, of Remote 

28656. McDonnell Douglas Corp. Sensors in Urban Transportation 

Planning Feasibility Study of the AppliCR-124426 June 1967 cation of Saturn Apollo Automated Data 

Nutator Experimental Test 'Program. Capabilities to Problems of the EnvironNAS8-20378. Bendix Corp. N73-73942 mental Impacts of Urban Transportation. 

NAS8-29012. Louisiana State University. 

CR- 124427 August 1972 N73-32846 

Basic Grant Title: 	The Strains Produced 

68 
CONTRACTOR REPORTS
 

CR-124434 July 12, 1973 NAS8-28657. The Bendix Corp. 

Study of Bonding Methods of Aluminum N74-19512 

Bedm Leaded Devices on Microcircuit 

Ceramic Substrates (Final Report). CR-124442 August 1973 

NAS8-27865. Electron Communications Updated Optical, Read Write Memory 

Inc. N73-32369 System Components (Final Report). 

NAS8-26672. Electro Optics Corp. 

CR-124435 N73-32399 

The Preliminary Design of an Aerodynamic Thermal Simulation System. CR-124443 June 1973 

NAS8-26416. Research Inc. N73-33153 'Crystal Growth in Fused Solvent Systems. NAS8-28118. General Electric 

CR- 124436 Corp. N73-32587 

Preliminary Design of an Aerodynamic 

Thermal Simulation . System. NAS8- CR-124444 May 1973 

26416. Research Inc. N73-33154 Wing Tip Vortex Measurements with 

Laser Doppler Systems. NAS8-25896. 

CR-124437 Remtech Incorporated. N73-32924 

Final Report for the Preliminary Design 

of an Aerodynamic Thermal Simulation CR-124445 January 1973 

System. NAS8-26416. Research Inc. A Study of Power Conditioning and 

N73-33155 Power Distribution and Components 

(Final Report). NAS8-26752. Auburn 

CR-124438 September 15, 1973 University. N73-31989 

Analysis of Requirements for Computer 

Control and Data Processing Experiment CR-124446 June 19, 1973 

Subsystems. NAS8-2546 1. Systems Reduction of Truncation Errors in Model 

Development Corp. N73-33122 Analysis (Final Report). NAS8-28167. 

General Electric Corp. N73-32484 

CR-124439 May 1973 

Growth of a Single Crystal Ribbon in CR-i 24447 September 15, 1973 

Space. NAS8-27807. Texas Instruments Analyses of Requirements for Computer 

Incorporated. N73-32588. Control and Data Processing Experiment 

Subsystems: Image Data Process'ig Sysr. 

CR-124440 September 21, 1973 tem (IDAPS) Software Description 7094 

Study and Design of a Laser Communi- Version. NAS8-25471. System Developcations System for Space Shuttle (Final ment Corp. N73-33123 

Report). NAS8-26245. ITT Gilfillan Inc. 

N73-32400 CR-124448 June 1973 

Passivation of Pigment Particles for 

CR-I 24441 Thermal Control Coatings. NAS8-21270. 

Advanced C and D Techniques and Stanford Research University. 

Applications Study (Final Report). N73-33457 

69 
CONTRACTOR REPORTS
 

CR-124449 August 1973 Doppler Systems. NAS8-25921. 

Review of Mechanical Vibration Tests Lockheed Missiles and Space Co. 

Conducted on Control Moment Gyros X73-10559 

and Life Test Fixtures. Michigan Technology Institute. N73-33365 CR-124457 September 1973 

Development Fabrication and Evaluation 

CR-124450 June 1973 of Composite Thermal Engine Insulation. 

Investigation of Vibrational Energy NAS8-29061. AVCO. N73-33458 

Transfer in Connected Structures (Final 

Report). NAS8-28171. Northrop Corp. CR-124458 May 1973 

N73-33878 Feasibility Study of a High Temperature 

Radiation Furnace for Space ApplicaCR-124451 September 1973 tions (Final Report). NAS8-28059. 

Pipe Thermal Conditioning Panel. NAS8- Weiner Associates Inc. N73-33905 

28639. McDonnell-Douglas Corp. 

N73-33898 CR-124459 September 1973 

Development of Porcelain Enamel Passive 

CR-124452 September 31, 1973 Thermal Control Coatings ' (Final 

Development of Flight Experiment Work Report). NAS8-27439. Hughes Aircraft. 

Performance and Workstation Interface N73-33459 

Requirements. NAS8-28359. Matrix 

Corp. N73-33830 CR-124460 July 1973 

Application of Diffusion Bonding to 

CR 1124453 September 1973 Electronic Interconnection of Flatback 

Heat Pipe Thermal Conditioning Panel. Leads. NAS8-28269. Hughes Aircraft 

NAS8-38659. McDonnell-Douglas Corp. Corp' N73-33429 

N73-33899 

CR-124461 September 12, 1973 

CR-124454 September 1963 IMC P/M BT 1107V-l LMC P/N BT 

Mathematical Research on Spline Func- 381OV-6. NAS8-29672. IMC Magnetics 

tions. NAS8-27181. University of Corp. 

Alabama. N73-33516 

CR-124462 September 30, 1973 

CR-12445 5 June 1973 Life Support System Cost Study 

CIT Photoheliograph Functional Verifica- Addendum to Cost Analysis of Carbon 

Ition Unit Rest Program. NAS8-29151. Dioxide Concentrators. NAS8-28377. 

Ball Brothers Research Corp. McDonnell-Douglas Corp. N73-33052 

N73-33364 

CR-124463 October 1973 

CR-124456 June 1973 Universal Stowage Module for Future 

Development of Theory and Experiments Space Exploration. NAS8-29777. 

to Improve Understanding of Laser N73-33832 

70 
CONTRACTOR REPORTS
 

CR-124464 September 1973 CR-424472 June 8, 1973 

Research of Metal Solidification in Zero Stratoscope LL Integrating Television 

(1c) G State (Final Report). NAS8- Camera (Final Report). NAS8-27687. 

28604. Grumman Aerospace Corp. Princeton University. N74-10417 

N74-10527 

CR-124473 February 1, 1973 

CR-124465 August 24, 1973 Insulation Commonality Assessment 

Device Fabrication BL54L68 with (Phase I, Vol. II). NAS7-200. North 

'Quartz Overcoat (Final Report). NASS- American Rockwell Space Division. 

28096. Texas Instruments. X73-10558 N74-10798 

CR-124466 August 24, 1973 CR-I 24474 July 1973 

Digital Hydraulic Valving System. Design and Mathematical Analysis of a 

NAS8-28166. HLM Inc. N74-16138 Three-Mirror X-Ray Telescope Based on 

ATM S-056 X-Ray Telescope Hardware. 

CR-124467 November 1968 NAS8-27301. University of Montevallo, 

Electromagnetic Interference Test Plan Alabama. N74-12186 

for the Saturn S-i I System. NAS7-200. 

North American Rockwell Corp. CR-124475 June 21, 1973 

N73-74515 	 Low-Cost Payload Design Concepts 

Study (Final Report). Vol. II Mission 

CR-124468 May 1973 Requirements Analysis and Subsystem 

Feasibility Study of a High Temperature Spacecraft Selection. NAS8-28960. 

Radiation Furnace for Space Applica- Lockheed Missiles and Space Co. 

tions (Summary Report). NAS8-28059. 

Weiner Associates, Inc. CR-124476 June 21, 1973 

Low-Cost Payload Design Concepts. 

CR-124469 May 31, 1973 Study (Final Report). Vol. IIl Design of 

Evaluation of Stress Corrosion Cracking Refurbishable Standard Subsystems for 

Susceptibility Using Fracture Mechanics Shuttle Automated Spacecraft. NAS8-

Techniques (Final Report, Part 1). 28960. Lockheed Missiles and Space Co. 

NA88-21487. Alcoa Lab. N74-10835 

CR- 124477 

CR-	 24470 June 1973 Low-Cost Payload Design Concepts 

The Second Order Gravitational Red Study (Final Report). Design Data and 

Shift. NGR-09-015-205. Smithsonian Specifications for Low-Cost Standard 

Institute. N74-10350 Subsystems (LMSC Engineering Memos). 

NAS8-28960. Lockheed Missiles and 

CR-124471 February 1, 1973 Space Co. 

Insulation Commonality Assessment 

(Phase 1). NAS7-200. North American CR-124478 June 21, 1973 

Rockwell Space Division. N74-10797 Low-Cost Payload Design Concepts 

71 
CONTRACTOR REPORTS
 

Study Vol. IV - Risk Acceptance and Experiments Laboratory. NAS8-27861. 

Logistics Approaches for Shuttle Auto- McDonnell-Douglas Astronautics Co. 

mated Payloads. NAS8-28960. Lockheed N73-12270 

Missiles and Space Co. 

CR-128999 	 October 1972 

CR-124479 June 21, 1973 The Composite Sequential Clustering 

Low-Cost Payload Design Concepts Technique for Analysis of Multispectral 

Study (Final Report). Vol. VI - Effects Scanner Data. NAS8-27364. Northrop 

of Design Technology on Low-Cost Services, Inc. N73-12633 

Modularized Shuttle Payloads. NAS8­

28960. Lockheed Missiles and Space Co. CR-129000 August 1972 

Rocket Ascent 	 G-Limited MomentCR- 124480 June 21, 1973 Balanced Optimization Program 

Low-Cost Payload Design Concepts (RAGMOP) (Final Report). NAS8S 

Study (Final Report). NAS8-28960. 27621. Northrop Services, Inc. 

Lockheed Missiles and Space Co. N73-21815 

CR-124481 May 1973 CR-129001 February 1973 

Thermal Engineering Research (Final A Feasibility Study of Using Remotely 

Report). University of Alabama. Sensed Data for Water Resource Models. 

N74-12569 NAS8-28590. Colorado State University. 

N73-23479 

CR-128995 October 1972 

Runway Crosswinds and Headwind CR-129002 June 1973 

Reversals at Cape Kennedy, Florida. Zero-Gravity Cloud Physics LaboratoryNAS8-21810. Northrop Services, Inc. 'Candidate Experiments Definition amd 

N73-10617 	 Preliminary Concept Studies. NAS8­

27861. McDonnell-Douglas Astronautics 

CR-128996 October 6, 1972 Company. N73-29674 

Memory Interface Simulator: A Computer Design Aid. NAS8-21805. Com- CR-129003 June 1973 

puter Sciences Corporation. N73-11185 Assessment of Possible Environmental 

Effects of Space Shuttle Operations. 

CR-128997 September 1, 1972 NAS8-28294. University of Michigan. 

Optimum Spaceborne Computer System 

Design By Simulation. NAS8-21805. CR-129004 May 22, 1973 

Computer Sciences Corporation. Atmospheric Effects on Remote Sensing 

N73-11184 of Non-Uniform Temperature Sources. 

NAS8-28722. University of South 

CR-128998 November 1972 Alabama. N73-25413 

Feasibility Study of a Zero-Gravity 

(Orbital) Atmospheric Cloud Physics 

72 
CONTRACTOR REPORTS
 

CR-129005 	 May 24, 1973 Studies: A Review of the Literature. 

Multivariate Normal Integration (Final NAS8-29036. Mississippi State UniverReport). NAS8-29286. Appalachian State sity. N73-29989 

University. 

CR-129012 	 September 1973 

CR-129006 June 1973 TERRASTAR (Final Report). NGTNASA/MSFC Multilayer Diffusion 01-003-044. Auburn University. 

Models and Computer Program for N74-12674 

Operational Prediction of Toxic Fuel 

Hazards. NASS-29033. H. E. Cramer CR-129013 September 1973 

Company, Inc. N73-28050 Zero-Gravity Cloud Physics LaboratoryExperiment Program Definition and PreCR-I 29007 July 1973 liminary Laboratory Concept Studies. 

Use of 4-D Atmospheric Models in the NAS8-27861. McDonnell-Douglas 

Simulation of Radiometric Measure- Astronautics Company. 

ments. NAS8-28720. Environmental 

Research and Technology, Inc. CR-129014 November 1973 

N73-27546 	 A Simulator for the Space Ultrareliable 

Modular , Computer (SUMC). NASSCR-l 	29008 July 1973 21805. Computer Sciences Corporation. 

An Empirical Analysis of the Distribution of Overshoots in a Stationary CR-129015 April 28, 1970 

Gaussian Stochastic Process. NAS8- Scattering from Condensates in Tur29286. Appalachian State University. bulent Jets (Final Report). NAS8-21035. 

IIT Research Institute. N74-12088 

CR-129009 May 1, 1973 

S-II Stage 1/25 Scale Model Base Region CR-129016 April 15, 1970 

Thermal Environment Test. Vol. 1: Test Crossed Beam Instrument Mark IL OperaResults, Comparison with Theory and tional Manual (Final Report). NAS8-

Flight Data. NAS7-200. Rockwell Inter- 21035. IIT Research Institute. 

national Corporation. N73-29883 

CR-129017 	 April 1973 

CR-129010 May 1, 1973 Three-Dimensional Laser Doppler 

S-Il Stage 1/25 Scale Model Base Region Velocimeter Turbulence Measurements in 

Thermal Environment Test. Vol. II: Test a Pipe Flow. NAS8-25896. REMTECH 

Data Tabulation, Statistical Analysis Incorporated. N74-17020 

Results, and Heating Rate Contours. 

NAS7-200. Rockwell International CR-129018 February 26, 1970 

Corporation. N73-29144 Application of Crossed Beam Technology 

to 	 Direct Measurements of Sound 

CR-129011 June 1973 Sources in Turbulent Jets (Part 1) (Find 

Remote Sensing Applications for Trans- Report). NAS8-21035. IIT Research 

portation and Traffic Engineering Institute. N74-16380 

73 
CONTRACTOR REPORTS
 

CR-129019 December 1973 CR-429024 April 1973 

Calculation of Eddy Viscosity in a Extension of a Simplified Computer 

Compressible Turbulent Boundary Layer Program for Analysis of Solid-Propellant 

with Mass Injection and Chemical Rocket Motors (Final Report). NCA8-

Reaction (Final Report). NCA8-68; Mod. 61S1, NCA8-61S2, and NCA8-61S3. 

7. 	University of Alabama Huntsville. Auburn University. N74-20436 

Vol. I N74-17017 

Vol. 11 N74-17018 CR-129025 October 1972 

Design and Performance Analysis of 

CR-129020 February 1974 Solio-Propellant Rocket Motors Using a 

Modern Control Concepts in Hydrology. Simplified Computer Program (Final 

NAS8-28655." Colorado State University. Report). NCA8-61. Auburn University. 

N74-19040 N74-20437 

CR-129021 January 1974 CR-129026 March 29, 1974 

Statistical Analysis of Flight Times for Photolysis of Spacecraft Contaminants 

Space Shuttle Ferry Flights. NAS8- (Final Report). NAS8-29197. PBR Elee21810. Northrop Services, Inc. tronics, Inc. N74-20900 

N74-17542 

CR-129027 May 1974 

CR-19022 March 1973 Stochastic Model of Temporal Changes 

Estimation of Peak Winds from Hourly of Wind Spectra in the Fr.te Atmosphere. 

Observations. NAS8-21810. Northrop NAS8-21810. Northrop Services, Inc. 

Services, Inc. N74-19235 N74-22286 

CR-129023 April 1974 CR-129028 May 1, 1974 

Feasibility of Remote Evaporation and Atmospheric Effects on Remot Sensing 

Precipitation Estimates. NAS8-28590. of Non-Uniform Temperature Sources 

Colorado State University. N74-21235 (Final Report). NAS8-28722. University 

of South Alabama. N74-25878 

74 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author" indicates non-MSFC author.)
 

ALLEN, ROBERT E., DR. S&E-ASTN-MTM 

Utilization of Cryobiology for Space 

Electrophoresis. May 15, 1974. Presentation at the Society for Cryobiology 1 th 

International Meeting, London, England. 

AUSTIN, ROBERT W S&E-SSL-SG 

(co-author) 

An Efficient Readout System for Multiwire Proportional Counter Hodoscopes. 

November 29, 1973. Publication in 

Nuclear Instruments and Methods. 

BAILEY, GEORGE A., JR. S&E-ASTR-RM 

MSFC's Efforts in Microelectronics. 

February 1, 1974. Presentation at the 

Conference on Microelectronic Facilities. 

Albuquerque, New Mexico. 

BANNISTER, TOMMY C. S&E-SSL-TR 

(co-author) 

Natural Convection in Low-G Environments. August 20, 1973. Presentation at 

the AIAA Space Processing Meeting, 

Washington, D.C. 

Heat Flow and Convection Experiments 

Aboard Apollo 17. February 27, 1974. 

Publication in SCIENCE Magazine. 

BROWN, S. CLARK S&E-AERO-YT 

(co-author) 

Cloud Cover Impact on Skylab Earth 

Resources Experiment Package (EREP). 

July 19, 1973. Presentation at the ASP/ 

ACSM Fall Conference, Orlando, Florida. 

BHALLA, A. S., DR 

See Kroes, Roger L., Dr. 

BHALLA, R. S., DR. 

See Kroes, Roger L., Dr. 

BURKE, HARLAN D. 

See Cofield, Kester L. 

BURNS, ROWLAND E.', DR. S&E-AERO-GA 

Incorporation of Known Integrals into 

the Optimal Trajpctory Problem. July 

27, 1973. Presentation at the AIAA 12th 

- Aerospace Sciences Meeting, Washington, 

D.C. 

BUTCHER, ERIC C. S&E-AERO-YS 

The Effect of the S. Current on the 

Determination of the Effective Recombination Coefficient. October 25, 1973. 

Publication in the Journal of Atmospheric and Terrestrial Physics. 

CAMPBELL, C. W. 

See Jayroe, R. R. 

CARUSO, S. V. S&E-ASTR-RMH 

(co-authors) 

Evaluation of Electrically Insulative 

Adhesives for use in Hybrid Microcircuit 

Fabrication. August 28, 1973. Publication in the Proceedings (IEEE) on Parts, 

Hybrids, and Packaging. 

CARUSO, SALVADORE V. S&E-ASTR-RMH 

The Development and Evaluation of 

Adhesives for Use in Hybrid Microelectronic Packaging. December 20, 1973. 

Presentation at the 1974 Government 

Microcircuit Applications Conference, 

Boulder, Colorado. 

CHANG, FENG-CHENG S&E-ASTR-RP 

The Complete Solution to the Second 

Order Linear Differential Equation with 

Given Initial Conditions. January 8, 

1974. Publication in the Journal of the 

Franklin Institute. 

75 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author" indicates non-MSFC author.)
 

The Inverse of the Genei-alized Vandermonde Matrix Through the Partial 

Fraction Expansion. January 8, 1974. 

Publication in the IEEE Transactions on 

Automatic Control. 

CHANG, FENG-CHENG S&E-ASTR-RP 

(co-author) V 

Note on the Transfer Wave Matrix. 

January 8, 1974. Presentation at the 

1974 IEEE Region 3 Conference, Gainesville, Florida. 

On the Matrix Related to the Partial 

Fraction Expansion of a Proper Rational 

Function. January 8, 1974. Publication 

in the Proceedings of IEEE. 

Operations on Power Series and Higher 

Derivatives of Function. January 8, 

1974. Presentation at the 1974 IEEE 

International Symposium on Circuits and 

Systems Theory, San Francisco, 

California. 

CHUBB, W. B. S&E-ASTR-SGD 

Skylab in Review (View Graph Presentation). October 3, 19,73. Presentation at 

the SAE Conference Aerospace Control 

and Guidance Systems, Orlando, Florida. 

CLIFF, WILLIAM C. S&E-AERO-AF 

(co-author) 

Measurement Capabilities of a One 

Dimensional LDV System. July 9, 1973. 

Publication in Physics of Fluids. 

I 

"COFIELD, KESTER 1. S&E-ASTR-IRI 

'DOUGLAS, JOSEPH D. S&E-ASTR-IM 

LEWTER, BILLY J. S&E-ASTR-IME 

BURKE, HARLAN D. S&E-ASTR-IR 

DAVIS, ALONZA S&E-ASTR-ST 

(co-authors) 

Design Characteristics of a Skylab Soft 

X-Ray Telescope. February 20, 1974. 

Presentation at the SPIE Meeting. 

CLONTS, SAMUEL E. S&E-ASTN-PLB 

(co-authdr) f 

G-189A Analytical Simulation of the 

Rite Integrated Water-Waste Management 

System. April 8, 1974. Presentation at 

the Fourth Intersociety Conference on 

Environmental Systems, Seattle, 

Washington. 

CORCORAN, WILLIAM L. PD-TUG-C 

KLINE, RICHARD GAC 

Flexibility Characteristics of Earth 

Storable Propellant Orbit-to-Orbit 

Vehicles. October 30, 1973. Presentation 

at the JANNAF Propulsion Symposium, 

Las Vegas, Nevada. 

COTHRAN, CHARLES A. S&E-ASTN-PJ 

(co-author) 

Radiation from an Array of Gray Circular Fins of Trapezoidal Profile. November 2, 1973. Publication in the International Journal of Heat and Mass 

Transfer. 

CRABTREE,L.W. S&E-ASTR-EPN 

(co-author) 

ATM Solar Array In-Flight Performance 

Analysis. May 6, 1974. Presentation at 

the In tersociety Energy Conversion 

Engineering Conference, San Francisco, 

California. 

76 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author" indicates non-MSFC author.)
 

CUMMINGS, ROBERT E. S&E-EA 

JAYROE, ROBERT R., JR. S&E-EA 

Unsupervised Classification Techniques as 

Components of a Data and Information 

System. September 7, 1973. Presentation 

at the Symposium on Management and 

Utilization of Remote Sensing Data, 

Sioux Falls, South Dakota. 

DALINS, ILMARS S&E-SSL-N 

(co-author) 

Sticking Probabilities for the Adsorption 

of Hydrogen on Clean NI(I 11), NI(l 00), 

NI Sheet and Evaporated NI Films. 

October 9, 1973. Publication in Surface 

Science. 

DANIELS, GLENN E. S&E-AERO-YT 

Marshall Space Flight Center's Natural 

Environmental Program. January 21, 

1974. Presentation at the Cost Effectiveness in Environmental Sciences, 20th 

Annual Meeting of. Institute of Environmental Sciences, Washington, D.C. 

DARBRO, W.A. S&E-SSL-PM 

INGRAM, STANLEY L. S&E-SSL-PM 

Unidentified Flying Objects Over the 

Tennessee Valley. January 21, 1974. 

DAVIS, ALONZA 

See Cofield, Kester L. 

DECHER, RUDOLF S&E-SSL-N 

Progress on the Stanford Gyro Experiment. June 3, 1974. Presentation at 

Fifth Cambridge Conference on 

Relatively. 

DELOACH, A.C. 

See Milligan, J.E. 

DOUGLAS, JOSEPH D. 

See Cofield, Kester L. 

DOWNEY, JAMES A., III PD-LST-MGR 

General Concept Considerations and 

Mission Profiles. January 10, 1974. 

Presentation at the AIAA 12th Aerospace Sciences Meeting, Washington, D.C. 

EDWARDS, THOMAS R. S&E-SSL-PA 

Time Lapse Reproduction of Image Thru 

Interactive Graphics. May 29, 1974. Presentation at the 1974 Summer Computer 

Simulation Conference, Houston, Texas. 

Two Dimensional Convolute Integers for 

Optical Image Data Processing and Surface Fitting Part 1. January 24, 1974. 

Publication in the Journal of Optical 

Society of America. 

Two Dimensional Regression for Equal 

Interval Data. February 4, 1974. Presentation at the Alabama Academy of 

Sciences, Birmingham, Alabama. 

FACEMIRE, BARBARA R. S&E-SSL-TR 

(co-author) 

Convection Reflection. September 17, 

1973. Publication in the Journal of Fluid 

Mechanics. 

Thermal Mapping of Convection with 

Liquid Crystals. May 29, 1,974. Publication in the International Journal of Heat 

and Mass Transfer. 

77 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author" indicates non-MSFC author.)
 

FICHTL, GEORGE H. S&E-AERO-YA 

Aeronautical and Aerospace Vehicle Air 

Flow Measurement Needs and Profiles. 

February 12, 1974. Presentation at the 

National Bureau of Standards Meeting on 

Flow Measurements, Gaithersburg, 

Maryland. 

FICHTL, GEORGE S&E-AERO-YA 

(co-authors) 

A Boundary Lhyer Analysis of Atmospheric Motion Over a Semielliptical SUtrface Obstruction. January 8, 1974. 

Publication in the Journal of Boundary 

Layer Meteorology, Dordrecht, Holland. 

Non-Stationary Atmospheric Boundary 

Layer Turbulance Simulation. June 18, 

1974. Presentation at the AIAA Conference, Palo Alto, California. 

FIELD, E.L. SL-AL/MDA 

Skylab 1973. November 7, 1973. Publication in Shamrock, U. of Missouri. 

FIELDS, STANLEY A. S&E-SSL-TR 

Observations of Kohoutek (1973). 

February 4, 1974. Presentation at the 

Alabama Academy of Sciences, Birmingham, Alabama. 

FOUNTAIN, JAMES A S&E-SSL-TE 

WEST, EDWARD A. S&E-SSL-TE 

Thermal Measurements on Lunar Simulants in Support of Core Tube Studies. 

January 9, 1974. Presentation at the 

Fifth Lunar Science Conference, 

Houston, Texas. 

FOUNTAIN, JAMES A. 

See Wamsteker, Willem, Dr. 

FROES, ROGER, DR. 

See Wamsteker, Willem, Dr. 

GARRETT, HARRISON S&E-ASTR-C 

WALLS, BOBBY F. S&E-ASTR-G 

(co-author) 

A Strapdown Laser Gyro Navigator. 

February 28, 1974. Presentation at the 

National Aerospace and Electronics 

(NAECON) 74 Conference, Dayton, 

Ohio. 

GATES, DANIEL W. S&E-SSL-TT 

(co-author) 

Improved ZN2 TI 04 Thermal Control Pigmerit. February 20, 1974. Presentation 

at the 78th Annual Meeting of the 

American Ceramic Society, Chicago, 

Illinois. 

GLAESE, JOHN R. S&E-AERO-DOI 

Pointing Control System Requirements. 

February 5, 1974. Presentation at the 

LST Industry Briefing, MSFC, Alabama. 

GOLDSBY, WILLIAM D. PD-DO-P 

Integrated Mission Planning. August 28, 

1973. Presentation at the Second Conference on Payload Interfaces with 

Shuttle or Tug, Long Beach, California. 

GOODRUM, JOHN C. PD-TR 

Skylab - Logisticsin Space. August 14, 

1973. Presentation at the Eight Annual 

International Convention of the Society 

of Logistics Engineers, Hunt Valley, 

Maryland. 

78 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author" indicates non-MSFC author.)
 

GREENWOOD, TERRY F. S&E-AERO-AT 

SEYMOUR, DAVID C. S&E-AERO-AT 

Base Heating Predictions for the Space 

Shuttle. January 28, 1974. Presentation 

at the JANNAF 8th Plume Technology 

Meeting, Colorado Springs, Colorado. 

GREGG, CECIL C. PD-OD-DLR 

Space Tug Payload Requirements. 

August 28, 1973. Presentation at the 

Second Conference on Payload Interfaces 

with Shuttle or Tug, Long Beach, California. 

GRINER, C. S. S&E-ASTN-MEV 

JOHNSTON, M. H. S&E-ASTN-MEV 

Applications of, Auger Spectroscopy to 

Failure Analysis. December 12, 1973. 

Presentation at the Symposium on 

Applied Vacuum Science and Technology, AVS, Tampa, Florida. 

GUTTMAN, CHARLES H. PD-SA-P 

(co-author) 

SEP Stage for Earth Orbital Missions. 

July 17, 1973. Presentation at the AIAA 

10th Electric Propulsion Conference, 

Lake Tahoe, Nevada. 

HAMBY, HERMAN G. S&E-EA-DIR 

Water Resources Identification, Envirouimental Quality Monitoring, Mapping and 

Geology. March 19, 1974. Presentation 

at the Data Processing Management 

Assoc., Huntsville, Alabama. 

HEAMAN, J. P. S&E-AERO-AE 

Program for Analysis of Transducer Calibrations. February 20, 1974. Presentation at the 41st Meeting of the Supersonic Tunnel Association, Los Angeles, 

California. 

Operation of a Ludwieg Tub Wind 

Tunnel Using a Mini-Computer for Data 

Acquisition and Reduction. February 27, 

1974. Presentation at the 20th Instrument Society of America Aerospace 

Ins trumentation Symposium, 

Albuquerque, New Mexico. 

HENSEN, B.B. S&E-AERO-YS 

SMITH, ROBERT E. S&E-AERO-YS 

WEST, G. S. S&E-AERO-YS 

(co-authors) 

Ionospheric Wave-Like Disturbances Due 

to Tornadoes. March 6, 1974. Presentation at the 55th Annual AGU Meeting, 

Washington, D.C. 

HILL, C. KELLY 

See Vaughan, 0. H. 

HINTZE, GEOFFREY C. S& E-COMP-SD 

(co-author) 

An Interpretive Approach to Syntax 

Error Analysis and Correction. January 

24, 1974. Presentation at the ACM MidSoutheast Chapter Conference, Huntsville, Alabama. 

HODGES, BOBBY S&E-COMP-SD 

Compiler Writing System. September 12, 

1973. Presentation at the Workshop on 

Exploratory Development, SETE, 

Orlando, Florida. 

HODGES, BOBBY S&E-COMP-SD 

(co-authors) 

Simulation as a Computer Design Aid. 

July 25, 1973. Presentation at the 

AIAA/NASA/ASTM/IES Seventh Space 

Simulation Conference, Los Angeles, 

California. 

79 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author" indicates non-MSFC author.)
 

Applications of Interactive Man/ 

Computer Techniques to Spacecraft 

Experiment Control and Clinical Nuclear 

Medicine. April 23, 1974. Presentation at 

the 18th Annual Human Factors Society 

Meeting, Huntsville, Alabama. 

Spacecraft Experiment Control Utilizing 

Interactive Techniques. February 12, 

1974. Presentation at the Southeastern 

Regional ACM, Nashville, Tennessee. 

Support Software for Micro Program 

Development. May 29, 1974. Presentation at the ACM 7th Annual Workshop 

on Microprogramming, Palo Alto, 

California. 

HOPSON, GEORGE D. S&E-ASTN-PL 

LITTLES, JERROL W. S&E-ASTN-PL 

PATTERSON, WILLIAM C. S&E-ASTN-PL 

Flight Operations and Performance of 

Skylab Life Support and Environmental 

Control Systems. Presentation at the 

XXV International Astronautical 

Congress, Amsterdam, Netherlands. 

HUFFAKER, ROBERT M. S&E-AERO-AF 

CO2 Laser Doppler Systems for the 

Measurement of Atmospheric Winds and 

Turbulence. February 5, 1974. Publication in Atmospheric Technology. 

HUGGINS, CARL T. S&E-ASTR-IA 

(co-authors) 

Man/Machine Interface Considerations 

for a Teleoperator Spacecraft Control 

Station. August 31, 1973. Presentation 

at the 17th Annual Human Factors 

Society Convention, Washington, D.C. 

HUGHES, JAMES E. SP-EM-SE 

Design Concepts for Space Shuttle Main 

Engine. October 3, 1973. Presentation at 

the 1973 JANNAF Propulsion Meeting, 

Las Vegas, Nevada. 

HUNT, ROBERT M. 

See Shipman, David L. 

INGRAM, STANLEY L. 

See Darbro, W. A. 

JAYROE, R, R. S&E-AERO-YF 

CAMPBELL, C. W. S&E-AERO-YF 

(co-author) 

Digital Image Registration Method Based 

Upon Binary Boundary Maps. February 

27, 1974. Publication in the IEEE Transactions on Computers. 

JAYROE, ROBERT R. 

See Cummings, Robert E. 

JOHNSTON, J. D. S&E-ASTR-GCI 

(co-authors) 

Long-Duration Life-Tests of Slip Ring 

Capsule Assemblies for Inertial Guidance 

Platforms. December 4, 1973. Presentation at the 7th International Conference 

on Electric Contact Phenomena, Paris, 

France. 

JOHNSTON, M. H. S&E-ASTN-MEV 

The Gravitational Influence on Nucleation, Solidification and Deformation 

Processes in Tin Single Crystals. January 

31, 1974. Publication in Metallurgical 

Transactions. 

80 
MSFC PAPERS CLEAREI) FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author" indicates non-MSFC author.)
 

JOHNSTON, M. H. 

See Griner, C. S. 

KIDRON, A- S&E-PE-MW 

PARKS, P. G. S&E-PE-MW 

Welding of Aluminum 2219 Alloy with 

M934 Filler Wire. July 3, 1973. Publication in the Welding Journal. 

KRANZER, D. S&E-ASTR-R 

Spatial Dependence of the Carrier Lifetime in Thin Films of Silicon on 

Sapphire. February 21, 1974. Publication 

in the Applied Physics Letters. 

KRAUSE, FRITZ R. S&E-AERO-DIR 

Potential Mesoscale Mapping of Cloud 

Top State from Space. December 3, 

1973. 

Differential Spectroscopy of Air Quality 

Targets and Potential Mesoscale Mapping 

of Cloud Top State from Space. 

February 20, 1974. Presentation at the 

Third Annual Remote Sensing of Earth 

Resources Conference, Tullahoma, 

Tennessee. 

Potential Moisture Balance Surveys of 

Storms. July 3, 1973. Publication in the 

Journal of Atmospheric Sciences. 

Pure and Doped B-AGI. May 13, 

KROES, ROGER L., DR. S&E-SSL-TR 

BHALLA, A. S., DR. S&E-SSL-TR 

BHALLA, R. S., DR. S&E-SSL-TR 

Study of Optical Emission and Absorption on 


1974. Presentation at the Electro-


chemical Society, San Francisco, 


California. 


KROSS, DENNIS A. S&E-ASTN-ADL 

(co-author) 

Scaling of Water Impact Data for Space 

Shuttle Solid Rocket Boosters. October 

9, 1973. Presentation at the 44th Shock 

and Vibration Symposium, Houston, 

Texas. 

KURTZ, ROBERT L. S&E-SSL-PO 

PERRY, LAWRENCE M. S&E-SSL-PO 

A Holographic Motion Picture Camera 

Which Records Front Suface Detail 

from a Moving Scene in Real Time.'July 

9, 1973. Publication in Applied Optics 

Journal. 

KURTZ, ROBERT L. S&E-SSL-PO 

Real-Time Holographic Motion Picture 

Camera Capable of Recording ,ront Surface Detail from a Random Velocity 

Vector. May 14, 1974. Publication in 

Applied Optics. 

Holography and Its Applications. July 

18, 1973. Presentation at the Technical 

Seminar Series, Athens, Alabama. -

Holographic Camera System. July 25, 

1973. Publication in Delta. 

Composite Mobile Holographic NonDestructive Test System. July 18, 1973. 

Presentation at the Conference on 

Acoustical/Optical Non-Destructive Testing of Structural Bonds for Army 

Missiles, Redstone Arsenal, Alabama. 

LACY, LEWIS L. S&E-SSL-NP 

Ultrasonic Absorption in Supereonducting Single Crystals of NBIpxMOx. 

81 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author" indicates non-MSFC author.)
 

January 14, 1974. Publication in LT-13, 

Vol. 3 (bOOk) Plenum Publishing 

Company. 

LACY,LEWIS L. S&E-SSL-NP 

(co-author) 

The Electrical Properties of Zero-Gravity 

Processed Immiscibles. January 24, 1974. 

Presentation at the AIAA 12th Aerospace Sciences Meeting, Washington, D.C. 

Calculation of the Temperature and the 

Purity Dependence of Sound Attenuation of Superconducting NB. July 9, 

1973. Publication in Physical Review B. 

LAIACONA, FELIX S&E-ASTN-MMM 

(co-author) 

Low-Cost Methods for Fabrication of 

Aluminum-Boron Shapes. January 14, 

1974. Presentation at the 19th National 

SAMPE Symposium Exhibition. 

LEWTER, BILLY J. 

See Cofield, Kester L. 

LIN, TONY C. S&E-AERO-AA 

(co-author) 

Viscous Flow Over Spinning Cones at 

Angle of Attack. June 5, 1974. Publication in AIAA Journal. 

LITTLES, JERROL W. 

See Hopson, George D. 

LOMBARDO, J.A. S&E-ASTN-PP 

McCARTY, J. P. S&E-ASTN-PP 

Chemical Propulsion Challenge - The 

Old and the New. September 18, 1973. 

Publication in the AIAA Student Journal, New York. 

LOOSE, JACK D. S&E-ASTN-PTC 

McCOY, KENNETH E. S&E-ASTN-PTC 

(co-author) 

Heat Pipe Thermal Conditioning Panel. 

March 18, 1974. Presentation at the 

SAE/ASME/AIAA 4th Intersociety Conference on Environmental Systems, 

Seattle, Washington. 

LUNDQUIST, CHARLES A. S&E-SSL-DIR 

(1) Skylab Experiments on Metals; (2) 

Skylab Experiments on Semiconductors 

and Alkali Halides; (3) ASTP Multipurpose Furnace Experiments. April 12, 

1974. Publication in the proceedings of 

ESRO Space Processing Symposium. 

LYSAGHT, JAMES 0. S&E-ASTN-E 

Structural Systems. February 5, 1974. 

Presentation at the LST Industry Briefing, MSFC, Alabama. 

McCARTY, J. P. 

See Lombardo, J.A. 

McCOY, KENNETH E. 

See Loose, Jack D. 

MeDONOUGH, GEORGE F. S&E-EA-DIR 

Energy, The Environment and the Role 

of Technology. April 30, 1974. Presentation at the AIAA Conference, Huntsville, 

Alabama. 

Water Resources Identification, Environmental Quality Monitoring, Mapping and 

Geology. January 21, 1974. Presentation 

at the National Water Resources Conference, American Society of Civil 

Engineers, Los Angeles, California. 

82 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors.-Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author" indicates non-MSFC author.)
 

McILWAIN, M. C. S&E-QUAL-ARA 

(co-author) 

Computer Automated Ultrasonic Weld 

Inspection System. February 12, 1974. 

Presentation at the WESTEC Spring Conference, Los Angeles, California. 

MARSHALL, WILLIAM R. PD-DO-DIR 

Payload Interface Support. August 28, 

1973. Presentation at the Second conference on Payload Interfaces with 

Shuttle or Tug, Long Beach, California. 

MICHLOVIC, JOSEPH E. S&E-SSL-TE 

Skylab Observations of Comet Kohoutek. October 3, 1973. Publication in Sky 

and Telescope. 

MILLIGAN, J. E. S&E-SSL-T 

DELOACH, A.C. S&E-SSL-T 

(co-authors) 

Observations of .the X-Ray Flare of 16 

June 1973 from Skylab ATM S056 and 

Correlation with Magnetic Fields. 

November 5, 1973. Presentation at the 

141st Meeting of the American Astronomical Society, Tucson, Arizona. 

Solar X-Ray Flare Observations by the 

S-056 X-Ray Telescope on Skylab. 

November 5, 1973. Presentation at the 

141st Meeting of the American Astronomical Society, Tucson, Arizona. 

MITCHELL, ROYCE E. SP-EM-SE 

Shuttle Booster Recovery. September 14, 

1973. Presentation at the 1973 JANNAF 

Propulsion Meeting, Las Vegas, Nevada. 

MOORE, F. B S&E-ASTR-DIR (co-authors) 

Free-Flying Teleoperators for Space 

Missions. October 18, 1973. Presentation 

at the 6th IFAC Symposium on Automatic Control in Space, Zekkadzor 

(Armenia), USSR. 

MULLOY, LAWRENCE B. SP-ET-D 

Space Shuttle External Tank Propellant 

Feed and Pressurization System. September 11, 1973. Presentation at the 1973 

JANNAF Propulsion Meeting, Las Vegas, 

Nevada. 

NAUMANN, ROBERT J. S&E-SSL-P 

Contamination Problems with Spacecraft. 

February 1, 1974. Presentation at the 

American Chemical Society, Huntsville, 

Alabama. 

Can We Afford Emission Standards. 

January 8, 1974. Publication as a Letter 

to Science Magazine. 

NICOLAS, DAVID P. S&E-ASTR-RM 

The Role of the Sem in Microcircuit 

Failure Analysis. January 8, 1974. Presentation at Progress Toward Scanning 

Electron Microscopy/1974, Chicago, 

Illinois. 

Microcircuit Failure Analysis Using the 

Sem. March 6, 1974. Presentation at the 

IEEE Southeastcon. 

Role of Sem in Microcircuit Failure 

Analysis. January 22, 1974. Presentation 

at the 7th Annual SEMv Symposium, 

Chicago, Illinois. 

83 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author-" indicates non-MSFC author.)
 

Use of Scanning Electron Microscope 

(SEM) in Microcircuit Failure Analysis. 

September 18, 1973. Presentation at the 

International Society for Hybrid Microelectronics (ISHM), Redstone Arsenal. 

OLIVIER, JEAN R. PD-LST 

LST Design Considerations. January 10, 

1974. Presentation at the AIAA 12th 

Aerospace Sciences Meeting, Washington, 

D.C. 

ORAN, W. A. S&E-SSL-NP 

STONE, N. H. S&E-SSL-NP 

(co-authors) 

Electronic Temperature and Current 

Observations in the Wake of Bodies in a 

Streaming Plasma. May 14, 1974. Publication in Planetary Space Science. 

Laboratory Simulation of Space Aerodynamic Phenomena: Satellite Wake 

Studies. June 3, 1974. Presentation at 

the 9th International Rarefied Gas 

Dynamics Symposium 1974, Gottingen, 

West Germany. 

Parametric Study of Near-Wake Structure 

of Spherical and Cylindrical Bodies in 

the Laboratory (Part 1). July 9, 1973. 

Publication in Planetary Space Science. 

The Effects of Body Geometry on the 

Structure in the Near Wake Zone of 

Bodies in Flowing Plasma. December 12, 

1973. Publication in the Journal of Geophysical Research. 

Does a Two-Stream Flow Describe the 

Structure Observed in the Wake of a 

Large Spacecraft. May 14, 1974. Publication in E.O.S., a publication of the 

AGU. 

Laboratory Simulation Indication of an 

Electron Temperature Enhancement in 

the Wake of Bodies in a Streaming 

Plasma. November 5, 1973. Presentation 

at the Fall Meeting of the AGU, Los 

Angeles, California. 

PALUDAN, CHARLES T. N. S&E-EA 

The NASA-Marshall Space Flight Center 

Earth Resources Survey Program. March 

20, 1974. Presentation at the Chamber 

of Commerce of Brewton, Alabama. 

Land-Use Survey with NASA Multispectral Imagery. January 10, 1974. Presentation at the Conference on Uses of 

ERTS Data, Stillwater, Oklahoma. 

Studying Earth Resources from Orbit. 

November 9, 1973. Presentation at the 

Huntsville Syncon Committee for the 

Future, Inc., Huntsville, Alabama. 

The NASA Earth Resources Survey 

Program and Its Application to Resource 

Management Problems. October 29, 

1973. Presentation at the American Institute of Aeronautics and Astronautics, St. 

Louis, Missouri. 

Application of NASA Technology to 

Land-Use Studies. September-24, 1973. 

84 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Coauthor" indicates non-MSFC author.)
 

Presentation at the Winter Meeting, 

Kentucky-Tennessee Section, Society of 

American Foresters, Lexington, 

Kentucky. 

High Altitude Photography and Natural 

Resource Planning. January 24, 1974. 

Publication by the Society of American 

Foresters Program Proceedings of the 

Kentucky-Tennessee Section, Lexington, 

Kentucky. 

PARKS, P. G., 

See Kidron, A. 

PATTERSON, WILLIAM C. 

See Hopson, George D. 

PERRY, LAWRENCE M. 

See Kurtz, Robert L. 

POLSTORFF, WK. 

See Vintz, Frank L. 

PRYOR, DON S&E-ASTN-PPT 

Investigation of Extendible Nozzle Concepts. October 29, 1973. Presentation at 

the JANAF Propulsion Conference, Las 

Vegas, Nevada. 

ROBINSON, WILLIAM J. S&E-SSL-SG 

(co-author) 1 

The NASA Effort in High Efficiency 

Free-Space Microwave Power Transmission. March 7, 1974. Presentation at 

the International Microwave Power Institute Symposium, Milwaukee, Wisconsin. 

RUFF, RUDOLPH C. S&E-SSL-TR 

(co-author) 

External Field Effects on Diffusion and 

Solidification Derived from the Free 

Volume Model. February 19, 1974. Publication in the Journal of Applied 

Physics. 

SCHOCK, RICHARD W. S&E-ASTN-AAD 

A Discussion of Sortie Lab -Structural 

Subsystem Trade Studies. September 5, 

1973. Presentation to Large Structures 

for Manned Spacecraft, their Mathematical Analysis, Constructions and Test 

Conference, Frascati, Italy.-

SCHOCKEN, KLAUS, Dr. S&E-SSL-T 

The Attenuation of X-Rays in a Comet. 

October 9, 1973. Publication -in ICARUS 

- International Journal of Solar System 

Studies. 

The Parameters in the Energy Spectrum 

of X-Ray Emitting Supernova Remnants. 

July 9, 1973. Presentation at the Astronomical Society of the Pacific, San 

Francisco, California. 

SCHWENZFEGER, KLAUS J. S&E-AERO-G 

Contribution to Regularization in 

Optimal Trajectory Problems. October 

24, 1973. Publication in AIAA Journal. 

SELTZER, SHERMAN M. S&E-ASTR-A 

(co-author) 

Design of a Digital Controller for Spinning Flexible Spacecraft. July 25, 1973. 

Presentation at the AIAA Guidance and 

Control Conference, Key Biscayne, 

Florida. 

85 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author" indicates non-MSFC author.)
 

Stability Study of the Large Space Telescope (LST) System with Non-Linear 

CMG Gimbal Friction. May 9, 1974. 

Presentation at the AIAA Mechanics and 

Control of Flight Conference, Anaheim, 

California. 

SEYMOUR, DAVID C. 

See Greenwood, Terry F. 

SHIPMAN, DAVID L. A&PS-CP-S 

HUNT, ROBERT M. S&E-ASTN-A 

Structural Monitor System for Space 

Vehicles. August 14, 1973. Presentation 

at the 44th Shock and Vibration Symposlum, Houston, Texas. 

SHRIVER, EDWARD L. S&E-SSL-PA 

(co-author) 

Recent Developments in the Field of 

Micrometeoroid Simulation. September 

11, 1973. Presentation at the 24th International Astronautical Federation Congress, Baku, USSR. 

SMITH, ROBERT E. S&E-AERO-YS 

(co-author) 

An Emission Mechanism and Propagation 

Attenuation Rate for PC-I Micropulsations. August 15, 1973. Publication in 

the Journal of Atmospheric and Terrestrial Physics. 

SMITH, ROBERT E. 

See Hensen, B. B. 

SPENCER, HARRY L., JR. S&E-ASTR-EBC 

-(co-author) 

Coaxial Components Standardization. 

February 20, 1974. Presentation at the 

NEPCON Southeast '74, Orlando, 

Florida. 

STONE, N. H. 

See Oran, W. A. 

SWENSON, GARY R. S&E-AERO-YS 

(co-authors) 

A Study of O+2 (p-2 D) Emissions in 

Electron Aurora. April 8, 1974. Presentation at the 55th Annual AGU Meeting, 

Washington, D.C. 

TAYLOR, KENNETH R. PS-MP-T 

(co-author) 

Space Processing Payloads for Spacelab. 

February 15, 1974. Presentation at the 

Processing in Space Symposium, MSFC, 

Alabama. 

Requirements and Concepts for Space 

Processing Payloads. March 21, 1974. 

Presentation at the- ESRO Space Processing Symposium, Frascati, Italy. 

Space Processing Payloads for the Space 

Shuttle Era. January 10, 1974. Presentation at the AIAA 12th Aerospace 

Sciences Meeting, Washington, D.C. 

THOMAS, D.T. S&E-COMP-SD 

Automatic Information Extraction for 

Land Use and Agriculture Applications. 

September 14, 1973. Presentation at the 

Management and Utilization of Remote 

Sensing Data, American Society of 

Photogrammetry, Sioux Falls, SD. 

THOMAS, JERREL M. S&E-ASTN-S 

Decision Theory in Structural Reliability. 

April 24, 1974. Presentation at the 1975 

Annual Reliability and Maintainability 

Symposium, Washington, D.C. 

86 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author" indicates non-MSFC author.)
 

A Survey of Decision Methods in 

Reliability of Aerospace Structures. 

February 19, 1974. Publication in the 

Proceedings of the Silver Jubilee Meeting 

of the AERO 

lore, India. 

Society of India, BangaTHOMPSON, J. R. 

(co-author) 

Skylab Initial Crew 

S&E-ASTR-ITS 

Systems Report. 

March 27, 1974. Presentation at the 

45th Annual Scientific Meeting, Aerospace Mdical Association, Washington, 

D.C. 

THOMPSON, ZACK S&E-ASTR-SG 

(co-author) 

A Method for Compensating On-Off 

Relay Control System. February 12, 

1974. Presentation at the 1974 IEEE 

Southeastern Conference, Orlando, 

Florida. 

Unmanned Docking. February 20, 1974, 

Presentation at the IEEE Region Ill Conference, Orlando, Florida. 

TRAUBOTH,H. S&E-COMP-SA 

Real-Time Computer Systems. February 

5, 1973. Presentation at the University 

of Notre Dame, Notre Dame, In. 

MARSYAS - A New System for the 

Digital Simulation and Analysis of 

Physical Processes. July 18, 1973. Presentation at an Invited Seminar Talk, 

Berkeley, California. 

TRAUBOTH,H. S&E-COMP-SA 

(co-author) 

A Higher Level Language for an 

Automated Telemetry Test Facility and 

the Implementation Using New Software 

Production Techniques. September 20, 

1973. Presentation at the XXVIIth 

Meeting of AGARD Avionics Panel, 

Athens, Greece. 

MARSYAS as a Simulation and Analysis 

Tool for Aerospace Control Systems. 

March 8, 1974. Presentation at the Sixth 

IFAC Symposium on Automatic Control 

in Space. Tsachcadzar, USSR. 

VAUGHAN, O.H. S&E-AERO-Y 

HILL, C. KELLY S&E-AERO-Y 

Drop Coalescence in Zero-G Environ-­

ment of Skylab IV. June 17, 1974. 

Publication in Bulletin of American 

Meteorological Society, Boston, Mass. 

VINZ, FRANK L. S&E-COMP-S 

POLSTORFF, W.K. S&E-COMP-S 

General Purpose Simulation at -Marshall 

Space Flight Center. April 10, 1974. 

Presentation at the AIAA Working 

Group on Flight Simulation Facilities, 

Marietta, Georgia. 

WALLS, BOBBY F. 

See Garrett, Harrison 

WALSTEKER, WILLEM S&E-SSL-TE 

Minor Planets and Related Objects: 

Five-Color Photometry of Four 

Asteroids. June 3, 1974. Publication in 

the Astronomical Journal. 

WAMSTEKER, WILLEM, DR. S&E-SSL-T' 

FROES, ROBER, DR. S&E-SSL-T 

FOUNTAIN, JAMES A. S&E-SSL-T 

On the Surface Composition of 10. 

March 7, 1974. Publication in ICARUS, 

87 
MSFC PAPERS CLEARED FOR PRESENTATION
 

(Available only from authors. Dates are clearance dates.)
 

(Only MSFC authors listed. "Co-author" indicates non-MSFC author.)
 

International Journal for Solar System 

Studies. 

WANG, F.C. S&E-AERO-AF 

(co-author) 

Structure of Turbulent Jets and Wakes. 

April 8, 1974. Publication in the ALAA 

Journal. 

WATTERS, HARRY H. S&E-ASTN-SM 

The Fidelity of Man-Environment 

Research Settings. September 17, 1973. 

Presentation at the 28th Annual Conference, California Council, American 

Institute of Architects, Monterey, California. 

WEST, EDWARD A. 

See Fountain, James A. 

WEST, G. S. 

See Henson, B. B. 

WYMAN, CHARLES L. S&E-ASTR-RP 

(co-author) 

A Systematic Study of Arilanatic TwoMirror Telescopes: Part II, January 31, 

1974. Publication in Applied Optics. 

A Systematic Study of Aplanati<, Two 

Mirror Telescopes with Application to 

the Large Space Telescope: Part 1. 

December 6, 1973. Publication in 

Applied Optics. 

YATES, I. C., JR. S&E-PE-A 

(co-author) 

Preparation and Metallurgical Properties 

of Materials. Low Gravity Processed Immiscible November 21, 1973. Presentation at the AIAA Aerospace Sciences -

Meeting, Washington, D.C. 

YOST, VAUGHN H. S&E-PE-MWP 

Drop Tower and Research Rockets for 

Space Processing. April 19, 1974. Presentation at - the AIAA/ASME Thermophysics. and Heat Transfer Conference, 

Boston, Massachusetts. 

88