z 

4 

4 

m 

w 

CI 

W 

z 

4 

4 

m 

s 

3 

NASA 

PATENT 

ABSTRACTS 

BIBLIOGRAPHY 

A CONTINUING BIBLIOGRAPHY 

(AASA-SP-7039 43 

EIBLIGGRAEHY: A 

1 

Section 1 Abstracts 

JULY 1987 

I)) NASA PAlEtiX AESILEAC'IS 

CCITIhUII6 EIELlCGBAPHP~ 

NB 7-25 023 

LICZIIGN 1: ABS'IEACIS (SUFELEBILI 31) (UASA) 

45 p Avail: HlIS BC 803; klfS standing Unclars 

crder as FB86-911100, t11.5C danestic, 00/82 0082266 
NASA SP-7039(31) 

Section 1 

Abstracts 

NASA 

PATENT 

ABSTRACTS 

BIBLIOGRAPHY 

A CONTINUING BIBLIOGRAPHY 

Section 1 0 Abstracts 

Annotated references to NASA-owned inventions covered by US. patents and applications 

for patent that were announced in Scientific and 

Technical Aerospace Reports (STAR) between 

January 1987 and June 1987. 

Scientific and Technical Information Office 1987 

Washington, DC National Aeronautics and Space Administration 
This document is available from the National Technical Information Service (NTIS), Springfield, 

Virginia 22161, price code A03 
Several thousand inventions result each year from the aeronautical and space research supported by the National 

Aeronautics and Space Administration. The inventions having important use in government programs or significant 

commercial potential are usually patented by NASA. These inventions cover practically all fields of technology 

and include many that have useful and valuable commercial application. 

NASA inventions best serve the interests of the United States when their benefits are available to the public. In 

many instances, the granting of nonexclusive or exclusive licenses for the practice of these inventions may assist 

in the accomplishment of this objective. This bibliography is published as a service to companies, firms, and 

individuals seeking new, licensable products for the commercial market. 

The NASA Patent Abstracts Bibliography (NASA PAB) is a semiannual NASA publication containing comprehensive 

abstracts and indexes of NASA-owned inventions covered by U.S. patents and applications for patent. The citations 

included in NASA PAB were originally published in NASA's Scientific and Technical Aerospace Reports (STAR) 

and cover STAR announcements made since May 1969. 

For the convenience of the user, each issue of NASA PA6 has a separately bound Abstract Section (Section 1) 

and Index Section (Section 2). Although each Abstract Section covers only the indicated six-month period, the 

Index Section is cumulative covering all NASA-owned inventions announced in STAR since 1969. Thus a complete 

set of NASA PA6 would consist of the Abstract Sections of Issue 04 (January 1974) and Issue 12 (January 1978) 

and the Abstract Section for all subsequent issues and the Index Section for the most recent issue. 

The 85 citations published in this issue of the Abstract Section cover the period January 1987 through June 1987. 

The Index Section references over 4600 citations covering the period May 1969 through June 1987. 

ABSTRACT SECTION (SECTION 1) 

This PAB issue incorporates the 1987 STAR category revisions which include 10 major subdivisions divided into 

76 specific categories and one general categoryldivision. (See Table of Contents for the scope note of each 

category under which are grouped appropriate NASA inventions.) This new scheme was devised in 1975 and 

revised in 1987 in lieu of the 34 category divisions which were utilized in PA6 supplements (01) through (06) 

covering STAR abstracts from May 1969 through January 1974. Each entry in the Abstract Section consists of a 

STAR citation accompanied by an abstract and a key illustration taken from the patent or application for patent 

drawing. Entries are arranged in subject category in order of the ascending NASA Accession Number originally 

assigned to STAR to the invention. The range of NASA Accession Numbers within each issue is printed on the 

inside front cover. 

Abstract Citation Data Elements: Each of the abstract citations has several data elements useful for identification 

and indexing purposes, as follows: 

NASA Accession Number 

NASA Case Number 

Inventor's Name 

Title of Invention 

U.S. Patent Application Serial Number 

U.S. Patent Number (for issued patents only) 

U.S. Patent Office Classification Number(s) 

(for issued patents only) 

These data elements are identified in the Typical Citation and Abstract and in the indexes. 

... 

111 
INDEX SECTION (SECTION 2) 

The Index Section is divided into five indexes. These indexes are cross-indexed and are used to locate a single 

invention or groups of inventions. 

Subject Index: Lists all inventions according to appropriate alphabetized technical term and indicates the related 

NASA Case Number, the Subject Category Number, and the Accession Number. 

Inventor Index: Lists all inventions according to alphabetized names of inventors and indicates the related NASA 

Case Number, the Subject Category Number, and the Accession Number. 

Source Index: Lists all inventions according to alphabetized source of invention (i.e., name of contractor or 

government installation where invention was made) and indicates the related NASA Case Number, the Subject 

Category Number, and the Accession Number. 

Number Index: Lists inventions in order of ascending (1) NASA Case Number, (2) US. Patent Application Serial 

Number, (3) U.S. Patent Classification Number, and (4) U.S. Patent Number and indicates the related Subject 

Category Number and the Accession Number. 

Accession Number Index: Lists all inventions in order of ascending Accession Number and indicates the related 

Subject Category Number, the NASA Case Number, the US. Patent Application Serial Number, the U.S. Patent 

Classification Number, and the U.S. Patent Number. 

HOW TO USE THIS PUBLICATION TO IDENTIFY NASA INVENTIONS 

To identify one or more NASA inventions within a specific technical field or subject, several techniques are possible 

with the flexibility incorporated into the NASA PAB. 

(1) Using Subject Category: To identify all NASA inventions in any one of the subject categories in this 

issue of NASA PAB, select the desired Subject Category in the Abstract Section (Section 1) and find the 

inventions abstracted thereunder. 

(2) Using Subject Index: To identify all NASA inventions listed under a desired technical subject index 

term, (A) turn to the cumulative Subject Index in the Index Section and find the invention(s) listed under 

the desired technical subject term. (B) Note the indicated Accession Number and the Subject Category 

Number. (C) Using the indicated Accession Number, turn to the inside front cover of the Index Section to 

determine which issue of the Abstract Section includes the Accession Number desired. (D) To find the 

abstract of the particular invention in the issue of the Abstract Section selected, (i) use the Subject Category 

Number to locate the Subject Category and (ii) use the Accession Number to locate the desired invention 

within the Subject Catgory listing. 

(3) Using Patent Classification Index: To identify all inventions covered by issued NASA patents (does 

not include applicationsfor patent) within a desired Patent Classification, (A) turn to the Patent Classification 

Number in the Number Index of Section 2 and find the associated invention(s), and (B) follow the instructions outlined in (2)(B), and (D) above. 

iv 
TYPICAL CITATION AND ABSTRACT 

ON MICROFICHE 

NASA SPONSORED 1 1 

ACCESSION NUMBER- N87-15253'# National Aeronautics and Space Administration 

TITLE- WEIGHTLESSNESS SIMULATION SYSTEM AND PROCESS 

INVENTORS-HUBERT C VYKUKAL. inventor (to NASA) 29 Oct 1986 14 p 

Ames Research Center. Moffett Field Calif - CORPORATE SOURCE 

Patent Application 

NASA CASE NUMBER-(NASA-CASE-ARC-I 1646-1 NAS 1 71 ARC-I 1646-1, 

US-PATENT-APPL-SN-924398) Avail NTlS HC A02/MF A01 - PRICE CODE 

us PATENT APPLICATIONS/CSCL 148 

SERIAL NUMBER 

AVAILABILITY SOURCE 

A weightlessness simulator has a chamber and a suit in the 

COSATI CODE /chamber O-rings and valves hermetically seal the chamber A 

vacuum pump connected to the chamber establishes a pressure 

in the chamber less than atmospheric pressure A water supply 

tank and water supply line supply a body of water to the chamber 

as a result of partial vacuum created in the chamber In use, an 

astronaut enters the pressure suit through a port. which remains 

open to ambient atmosphere. thus supplying air to the astronaut 

during use The pressure less than atmospheric pressure in the 

chamber is chosen so that the pressure differential from the inside 

to the outside of the suit corresponds to the pressure differential 

with the suit in outer space NASA 

~ ABSTRACT 

/KEY ILLUSTRATION 

V 
TABLE OF CONTENTS 

Section 1 Abstracts 

AERONAUTICS 

Includes aeronautics (general); aerodynamics; air 

transportation and safety; aircraft communications and 

navigation; aircraft design, testing and performance; aircraft instrumentation; aircraft propulsion and power; aircraft stability and control; and research and support 

facilities (air). 

For related information see also Astronautics. 

01 AERONAUTICS (GENERAL). N.A. 

02 AERODYNAMICS 1 

Includes aerodynamics of bodies, combinations, 

wings, rotors, and control surfaces; and internal flow in 

ducts and turbomachinery. 

For related information see also 34 Fluid Mechanics 

and Heat Transfer 

03 AIR TRANSPORTATION AND SAFETY N.A. 

Includes passenger and cargo air transport operations; 

and aircraft accidents. 

For related information see also 76 Space Transportation and 85 Urban Technology and Transportation. 

04 AIRCRAFT COMMUNICATIONS AND 

NAVIGATION N.A. 

Includes digital and voice communication with aircraft; 

air navigation systems (satellite and ground based); and 

air traffic control. 

For related information see also 77Space Communications, Spacecraft Communications, Command and Tracking and 32 Communications and RadaL 

05 AIRCRAFT DESIGN, TESTING AND 

PERFORMANCE 2 

Includes aircraft simulation technology. 

For related information see also 78 Spacecraft Design, 

Testing and Performance and 39 Structural Mechanics. 

For land transportation vehicles see 85 Urban Technology 

and Transportation. 

06 AIRCRAFT INSTRUMENTATION N.A. 

Includes cockpit and cabin display devices; and flight 

instruments. 

For related information see also 79 Spacecraft Instrumentation and 35 Instrumentation and Photography: 

07 AIRCRAFT PROPULSION AND POWER 2 

Includes prime propulsion systems and systems components, e.g., gas turbine engines and compressors; and 

onboard auxiliary power plants for aircraft. 

For related information see also 20 Spacecraft Propulsion and Powec 28 Propellants and Fuels, and 44 Energy 

Production and Conversion. 

08 AIRCRAFT STABILITY AND CONTROL N.A. 

Includes aircraft handling qualities; piloting; flight controls; and autopilots. 

For related information see also 05 Aircraft Design, 

Testing and Performance. 

vi 

09 RESEARCHANDSUPPORT 

FACILITIES (AIR) 3 

Includes airports, hangars and runways; aircraft repair 

and overhaul facilities; wind tunnels; shock tubes; and 

aircraft engine test stands. 

For related information see also 74 Ground Support 

Systems and Facilities (Space). 

ASTRONAUTICS 

Includes astronautics (general); astrodynamics; 

ground support systems and facilities (space); launch vehicles and space vehicles; space transportation; space 

communications, spacecraft communications, command 

and tracking; spacecraft design, testing and performance; 

spacecraft instrumentation; and spacecraft propulsion and 

power. 

For related information see also Aeronautics 

12 ASTRONAUTICS (GENERAL) N.A. 

For extraterrestrial exploration see 97 Lunar and Planetary Exploration. 

13 ASTRODYNAMICS N.A. 

Includes powered and free-flight trajectories; and orbital and launching dynamics. 

14 GROUND SUPPORT SYSTEMS AND 

FACILITIES (SPACE) N.A. 

Includes launch complexes, research and production 

facilities; ground support equipment, e.g., mobile transporters; and simulators. 

For related information see also 09 Research and Support Facilities (Air). 

15 LAUNCH VEHICLES AND SPACE 

VEHICLES N.A. 

Includes boosters; operating problems of launchkpace 

For related information see also 20 Spacecraft Propulvehicle systems; and reusable vehicles. 

sion and PoweL 

16 SPACE TRANSPORTATION N.A. 

Includes passenger and cargo space transportation, 

e.g.3 shuttle operations; and space rescue techniques. 

For related information see also 03 Air Transportation 

and Safety and 78 Spacecraft Design, Testing and Performance. For space suits see 54 Man/System Technology 

and Life Support. 

17 SPACE COMMUNICATIONS, 

SPACECRAFT COMMUNICATIONS, 

COMMAND AND TRACKING 3 

Includes telemetry; space communications networks; 

astronavigation and guidance; and radio blackout. 

For related information see also 04 Aircraft Communications and Navigation and 32 Communications and 

RadaL 
18 SPACECRAFT DESIGN, TESTING AND 

PERFORMANCE 4 

Includes satellites; space platforms; space stations; 

spacecraft systems and components such as thermal and 

environmental controls; and attitude controls. 

For life support systems see 54 Man/System Technology and Life Support. For related information see also 05 

Aircraft Design, Testing and Performance, 39 Structural 

Mechanics, and 16 Space Transportation. 

19 SPACECRAFT INSTRUMENTATION N.A. 

For related information see also 06Aircraft lnstrumentation and 35 lnstrumentation and Photography. 

20 SPACECRAFT PROPULSION AND 

POWER 6 

Includes main propulsion systems and components, 

e.g. rocket engines; and spacecraft auxiliary power 

sources. 

For related information see also 07Aircraft Propulsion 

and Powec 28 Propellants and Fuels, 44 Energy Production and Conversion, and 15 Launch Vehicles and Space 

Vehicles. 

CHEMISTRY AND MATERIALS 

Includes chemistry and materials (general); composite 

materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and 

materials processing. 

23 CHEMISTRY AND MATERIALS 

(GENERAL) 7 

24 COMPOSITE MATERIALS 8 

Includes physical, chemical, and mechanical properties of laminates and other composite materials. 

For ceramic materials see 27 Nonmetallic Materials. 

25 INORGANIC AND PHYSICAL 

CHEMISTRY 9 

Includes chemical analysis, e.g., chromatography; 

combustion theory; electrochemistry; and photochemistry. 

For related information see also 77 Thermodynamics 

and Statistical Physics. 

26 METALLIC MATERIALS 10 

Includes physical, chemical, and mechanical properties of metals, e.g., corrosion; and metallurgy. 

27 NONMETALLIC MATERIALS 11 

Includes physical, chemical, and mechanical properties of plastics, elastomers, lubricants, polymers, textiles, 

adhesives, and ceramic materials. 

For composite materials see 24 Composite Materials. 

28 PROPELLANTS AND FUELS N.A. 

Includes rocket propellants, igniters and oxidizers; their 

storage and handling procedures; and aircraft fuels. 

For related information see also 07Aircraft Propulsion 

and Powec 20 Spacecraft Propulsion and Powec and 44 

Energy Production and Conversion. 

29 MATERIALS PROCESSING 12 

Includes space-based development of products and 

processes for commercial application. 

For biological materials see 55 Space Bology. 

ENGINEERING 

Includes engineering (general); communications and 

radar; electronics and electrical engineering; fluid 

mechanics and heat transfer; instrumentation and photography; lasers and masers; mechanical engineering; quality 

assurance and reliability; and structural mechanics. 

For related information see also Physics. 

31 ENGINEERING (GENERAL) 13 

Includes vacuum technology; control engineering; display engineering; cryogenics; and fire prevention. 

32 COMMUNICATIONS AND RADAR 14 

Includes radar; land and global communications; communications theory; and optical communications. 

For related information see also 04 Aircraft Communications and Navigation and 17 Space Communications, 

Spacecraft Communications, Command and Tracking. For 

search and rescue see 03 Air Transportation and Safet)! 

and 16 Space Transportation. 

33 ELECTRONICS AND ELECTRICAL 

ENGINEERING 15 

Includes test equipment and maintainability; components, e.g., tunnel diodes and transistors; microminiaturization; and integrated circuitry. 

For related information see also 60 Computer Operations and Hardware and 76 Solid-state Physics. 

34 FLUID MECHANICS AND HEAT 

TRANSFER 16 

Includes boundary layers; hydrodynamics; fluidics; 

For related information see also 02Aerodynarnic.s and 

mass transfer and ablation cooling. 

77 Thermodynamics and Statistical Physics. 

35 INSTRUMENTATION AND 

PHOTOGRAPHY 17 

Includes remote sensors; measuring instruments and 

gages; detectors; carneras and photographic supplies; and 

holography. 

For aerial photography see 43 Earth Resources and 

Remote Sensing. For related information see also 06 Aircraft lnstrumentation and 19 Spacecraft Instrumentation. 

36 LASERS AND MASERS 19 

Includes parametric amplifiers. 

For 'related information see also 76 Solid-state 

Physics. 

37 MECHANICAL ENGINEERING 19 

Includes auxiliary systems (nonpower); machine elements and processes; and mechanical equipment. 

38 QUALITY ASSURANCE AND 

RELIABILITY N.A. 

Includes product sampling procedures and techniques; 

and quality control. 

39 STRUCTURAL MECHANICS N.A. 

Includes structural element design and weight 

anaiysisf fatigue; and thermal stress. 

For applications see 05 Aircraft Design, Testing and 

Performance and 18 Spacecraft Design, Testing and Performance. 

vii 
GEOSCIENCES 

Includes geosciences (general); earth resources and 

remote sensing; energy production and conversion; environment pollution; geophysics; meteorology and climatology; and oceanography. 

For related information see also Space Sciences. 

42 GEOSCIENCES (GENERAL) N.A. 

43 EARTH RESOURCES AND 

REMOTE SENSING N.A. 

Includes remote sensing of earth resources by aircraft 

For instrumentation see 35 Instrumentation and Phoand spacecraft; photogrammetry; and aerial photography. 

tography 

44 ENERGY PRODUCTION AND 

CONVERSION 22 

Includes specific energy conversion systems, e.g., fuel 

cells; global sources of energy; geophysical conversion; 

and windpower. 

For related information see also 07Aircraff Propulsion 

and Powec 20 Spacecraft Propulsion and Powec and 28 

Propellants and Fuels. 

45 ENVIRONMENT POLLUTION N.A. 

Includes atmospheric, noise, thermal, and water pollution. 

46 GEOPHYSICS N.A. 

Includes aeronomy; upper and lower atmosphere 

studies; ionospheric and magnetospheric physics; and 

geomagnetism. 

For space radiation see 93 Space Radiation. 

47 METEOROLOGY AND CLIMATOLOGY N.A. 

Includes weather forecasting and modification. 

48 OCEANOGRAPHY N.A. 

Includes biological, dynamic, and physical oceanography; and marine resources. 

For related information see also 43 Earth Resources 

and Remote Sensing. 

LIFE SCIENCES 

Includes life sciences (general); aerospace medicine; 

behavioral sciences; man/system technology and life support; and space biology. 

51 LIFE SCIENCES (GENERAL) N.A. 

52 AEROSPACE MEDICINE N.A. 

Includes physiological factors; biological effects of radiation; and effects of weightlessness on man and animals. 

53 BEHAVIORAL SCIENCES N.A. 

Includes psychological factors; individual and group 

behavior; crew training and evaluation; and psychiatric research. 

54 MANISYSTEM TECHNOLOGY AND 

LIFE SUPPORT N.A. 

Includes human engineering; .biotechnology; and 

For related information see also 76 Space Transportaspace suits and protective clothing. 

tion. 

viii 

55 SPACE BIOLOGY N.A. 

Includes exobiology; planetary biology; and extraterrestrial life. 

MATHEMATICAL AND COMPUTER 

SCIENCES 

Includes mathematical and computer sciences (general); computer operations and hardware; computer programming and software; computer systems; cybernetics; 

numerical analysis; statistics and probability; systems 

analysis; and theoretical mathematics. 

59 MATHEMATICAL AND COMPUTER 

SCIENCES (GENERAL) N.A. 

60 COMPUTER OPERATIONS AND 

HARDWARE 23 

Includes hardware for computer graphics, firmware, 

For components see 33 Electronics and Electrical Enand data processing. 

gineering. 

61 COMPUTER PROGRAMMING AND 

SOFWARE N.A. 

Includes computer programs, routines, algorithms, and 

specific applications, e.g., CAD/CAM. 

62 COMPUTER SYSTEMS 23 

Includes computer networks and special application 

computer systems. 

63 CYBERNETICS N.A. 

lncluaes feedback and control theory, artificial intelligence, robotics and expert systems. 

For related information see also 54 Man/System 

Technology and Life Support. 

64 NUMERICAL ANALYSIS N.A. 

Includes iteration, difference equations, and numerical 

approximation. 

65 STATISTICS AND PROBABILITY N.A. 

Includes data sampling and smoothing; Monte Carlo 

method; and stochastic processes. 

66 SYSTEMS ANALYSIS N.A. 

Includes mathematical modeling; network analysis; 

and operations research. 

67 THEORETICAL MATHEMATICS N.A. 

Includes topology and number theory. 

PHYSICS 

Includes physics (general); acoustics; atomic and 

molecular physics; nuclear and high-energy physics; optics; plasma physics; solid-state physics; and thermodynamics and statistical physics. 

For related information see also Engineering. 

70 PHYSICS (GENERAL) N.A. 

For precision time and time interval (PTTI) see 35 

Instrumentation and Photography; for geophysics, astrophysics or solar physics see 46 Geophysics, 90 Astrophysics, or 92 Solar Physics. 
71 ACOUSTICS N.A. 

Includes sound generation, transmission, and attenuation. 

For noise pollution see 45 Environment Pollution. 

N.A. 

Includes atomic structure, electron properties, and 

72 ATOMIC AND MOLECULAR PHYSICS 

molecular spectra. 

73 NUCLEAR AND HIGH-ENERGY 

PHYSICS N.A. 

Includes elementary and nuclear particles; and reactor 

For space radiation see 93 Space Radiation. 

Includes light phenomena and optical devices. 

For lasers see 36 Lasers and Masers. 

theory. 

74 OPTICS 24 

75 PLASMA PHYSICS N.A. 

Includes magnetohydrodynamics and plasma fusion. 

For ionospheric plasmas see 46 Geophysics. For 

space plasmas see 90 Astrophysics. 

76 SOLID-STATE PHYSICS 25 

Includes superconductivity. 

For related information see also 33 Electronics and 

Electrical Engineering and 36 Lasers and Masers. 

n THERMODYNAMICS AND 

STATISTICAL PHYSICS N.A. 

Includes quantum mechanics; theoretical physics; and 

For related information see also 25 lnorganicand PhysBose and Fermi statistics. 

ical Chemistryand 34 Fluid Mechanics and Heat Transfer: 

SOCIAL SCIENCES 

Includes social sciences (general); administration and 

management; documentation and information science; 

economics and cost analysis; law, political science, and 

space policy; and urban technology and transportation. 

80 SOCIAL SCIENCES (GENERAL) N.A. 

Includes educational matters. 

81 ADMINISTRATION AND 

MANAGEMENT N.A. 

Includes management planning and research. 

INFORMATION SCIENCE N.A. 

Includes information management; information storage and retrieval technology; technical writing; graphic 

arts; and micrography. 

For computer documentation see 61 Computer Programming and Software. 

83 ECONOMICS AND COST ANALYSIS N.A. 

82 DOCUMENTATION AND 

Includes cost effectiveness studies. 

84 LAW, POLITICAL SCIENCE 

AND SPACE POLICY N.A. 

Includes NASA appropriation hearings; aviation law; 

space law and policy; international law; international cooperation; and patent policy. 

85 URBAN TECHNOLOGY AND 

TRANSPORTATION N.A. 

Includes applications of space technology to urban 

problems; technology transfer; technology assessment; 

and surface and mass transportation. 

For related information see 03 Air Transportation and 

Safer): 16 Space Transportation, and 44 Energy Production 

and Conversion. 

SPACE SCIENCES 

Includes space sciences (general); astronomy; astrophysics; lunar and planetary exploration; solar physics; 

and space radiation. 

For related information see also Geosciences. 

88 SPACE SCIENCES (GENERAL) N.A. 

89 ASTRONOMY N.A. 

Includes radio, gamma-ray, and infrared astronomy; 

and astrometry. 

90 ASTROPHYSICS N.A. 

Includes cosmology; celestial mechanics; space plasmas; and interstellar and interplanetary gases and dust. 

For related information see also 75 Plasma Physics. 

91 LUNAR AND PLANETARY 

EXPLORATION N.A. 

Includes planetology; and manned and unmanned 

For spacecraft design or space stations see 18 Spaceflights. 

craft Design, Testing and Performance. 

92 SOLAR PHYSICS N.A. 

Includes solar activity, solar flares, solar radiation and 

sunspots. 

For related information see 93 Space Radiation. 

93 SPACE RADIATION N.A. 

Includes cosmic radiation; and inner and outer earth’s 

radiation belts. 

For biological effects of radiation see 52 Aerospace 

Medicine. For theory see 73 Nuclear and High-Energy 

Physics. - 

GENERAL 

Includes aeronautical, astronautical, and space science related histories, biographies, and pertinent reports 

too broad for categorization; histories or broad overviews 

of NASA programs. 

99 GENERAL N.A. 

Nntet N.A. means that no abstracts wem aasianed to this catworv for this issue. 

Section 2 Indexes 

SUBJECT INDEX 

INVENTOR INDEX 

SOURCE INDEX 

CONTRACT NUMBER INDEX 

NUMBER INDEX 

ACCESSION NUMBER INDEX 

ix 
JULY 1987 (Supplement 32) 

NASA Patent Abstracts Bibliography 

A Semiannual Publication of the National Aeronautics and Space Administration 

02 

AERODYNAMICS 

Includes aerodynamics of bodies, combinations, wings, rotors, and 

control surfaces; and internal flow in ducts and turbomachinery. 

N87-14282'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

HIGH LIFT, LOW PITCHING MOMENT AIRFOILS Patent 

Application 

K. W. NOONAN, inventor (to NASA) 

US-PATENT-APPL-SN-904132) 

CSCL 51A 

Two families of airfoil sections which can be used for 

helicopterhotorcraft rotor blades or aircraft propellers of a particular 

shape are prepared. An airfoil of either family is one which could 

be produced by the combination of a camber line and a thickness 

distribution or a thickness distribution which is scaled from these. 

An airfoil of either family has a unique and improved aerodynamic 

performance. The airfoils of either family are intended for use as 

inboard sections of a helicopter rotor blade or an aircraft propeller. 

The novelty appears to reside in the specific shapes of the airfoil 

profiles which simultaneously permit high maximum lift coefficients 

at Mach numbers up to 0.50, low pitching moment coefficients 

about the quarter chord for lift coefficients from -0.2 to 1.0 at 

Mach numbers up to 0.63. and high drag divergence Mach numbers 

at lift coefficients from 0.0 to 0.30. NASA 

5 Sep. 1986 30 p 

Avail: NTlS HC A03/MF A01 

(NASA-CASE-LAR-13215-1; NAS 1.71:LAR-13215-1; 

N87-16793' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

GEOMETRIES FOR ROUGHNESS SHAPES IN LAMINAR FLOW 

Patent 

BRUCE J. HOLMES, inventor (to NASA), GLENN L. MARTIN, 

inventor (to NASA) (Kentron International, Inc., Hampton, Va.), 

CHRISTOPHER S. DOMACK, inventor (to NASA), CLIFFORD J. 

OBARA, inventor (to NASA), and AHMED A. HASSAN, inventor 

(to NASA) (Arizona State Univ., Tempe) 28 Oct. 1986 9 p 

Filed 10 Nov. 1983 Supersedes N84-12092 (22 - 03, p 320) 

(NASA-CASE-LAR-13255-1; US-PATENT-4,619,423; 

US-PATENT-APPL-SN-550681; US-PATENT-CLASS-244-1 30; 

US-PATENT-CLASS-244-35R; US-PATENT-CLASS-244-200; 

US-PATENT-CLASS-244-204) 

Office CSCL 01A 

Avail: US Patent and Trademark 

A passive interface mechanism between upper and lower skin 

structures, and a leading edge structure of a laminar flow airfoil is 

described. The interface mechanism takes many shapes. All are 

designed to be different than the sharp orthogonal arrangement 

prevalent in the prior art. The shapes of the interface structures 

are generally of two types: steps away from the centerline of the 

airfoil with a sloping surface directed toward the trailing edge and, 

the other design has a gap before the sloping surface. By properly 

shaping the step, the critical step height is increased by more 

than 50% over the orthogonal edged step. 

Official Gazette of the US Patent and Trademark Office 

. . 

I 

. 

1.. 

N87-18535"# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

METHOD FOR LAMINAR BOUNDARY LAYER TRANSITION 

VISUALIZATION IN FLIGHT Patent Application 

BRUCE J. HOLMES, inventor (to NASA) and PETER D. GALL, 

inventor (to NASA) 13 Nov. 1986 9 p 

US-PATENT-APPL-SN-929862) 

CSCL 01A 

The invention relates to a method of visualizing laminar 

boundary layer transition in flight and is particularly useful in 

aerodynamic and hydrodynamic testing. Disclosed is a method of 

visualizing laminar to turbulent boundary layer transition, shock 

location, and laminar separation bubbles around a test surface. A 

liquid crystal coating is formulated using an unencapsulated liquid 

crystal operable in a temperature bandwidth compatible with the 

temperature environment around the test surface. The liquid crystal 

coating is applied to the test surface, which is preferably pretreated 

by painting with a flat, black paint to achieve a deep matte coating, 

after which the surface is subjected to a liquid or gas flow. Color 

change in the liquid crystal coating is produced in response to 

differences in relative shear stress within the boundary layer around 

the test surface. The novelty of this invention resides in the use 

of liquid crystals which are sensitive to shear stress to show 

aerodynamic phenomena such a boundary layer transition, shock 

location and laminar separation bubbles around a test surface. 

NASA 

(NASA-CASE-LAR-13554-1; NAS 1.71 :LAR-13554-1; 

Avail: NTlS HC AO2/MF A01 

1 
05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE 

one embodiment the ejectors may be advantageously positioned 

spanwise on the wing while the ductwork is kept to a minimum. 

AIRCRAFT DESIGN, TESTING AND NASA 

05 

PERFORMANCE 

Includes aircraft simulation technology. 

N87-14314' National Aeronautics and Space Administration. 

Langley Research Center, Hampton. Va. 

REMOTE PIVOT DECOUPLER PYLON: WING/STORE FLUTTER 

SUPPRESSOR Patent 

J. M. HASSLER, JR., inventor (to NASA) (General Dynamics/Fort 

Worth, Tex.) 14 Oct. 1986 7 p Filed 10 Jan. 1985 Supersedes 

N85-19981 (22 - 19, p 2996) 

(NASA-CASE-LAR-13173-1; US-PATENT-4,616,793; 

US-PATENT-APPL-SN-690274; US-PATENT-CLASS-244-1 37-A; 

US-PATENT-CLASS-244-1 7.27; US-PATENT-CLASS-244-1 18.1 ; 

US-PATENT-CLASS-89-1.54; US-PATENT-CLASS-248-638) 

Avail: US Patent and Trademark Office CSCL 01C 

A device for suspending a store from an aerodynamic support 

surface, such an an aircraft wing, and more specifically, for 

improving upon singlet pivot decoupler pylons by reducing both 

frequency of active store, alignment, and alignment system space 

and power requirements. Two links suspend a lower pylon/rack 

section and releasable attached store from an upper pylon section 

mounted under the wing. The links allow the lower pylon section 

to rotate in pitch about a remote pivot point. A leaf spring connected 

between the lower section and electrical alignment system 

servomechanism provides pitch alignment of the lower 

section/store combination. The servomechanism utilizes an electric 

servomotor to drive the gear train and reversibly move the leaf 

spring, thereby maintaining the pitch attitude of the store within 

acceptable limits. The damper strokes when the lower section 

rotates to damp large oscillations of store. 

Official Gazette of the US Patent and Trademark Office 

N87-18561*# National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

HIGH PERFORMANCE FORWARD SWEPT WING AIRCRAFT 

Patent Application 

DAVID G. KOENIG, inventor (to NASA), KlYOSHl AOYAGI, inventor 

(to NASA), MICHAEL E. DUDLEY, inventor (to NASA), and SUSAN 

B. SCHMIDT, inventor (to NASA) 24 Nov. 1986 27 p 

1.71:ARC-11636-1) Avail: NTlS HC AO3/MF A01 CSCL 01C 

A high performance aircraft capable of subsonic, transonic and 

supersonic speeds employs a forward swept wing planform and 

at least one first-and-second-solution ejector located on the inboard 

section of the wing. A high degree of flow control on the inboard 

sections of the wing is achieved along with improved 

maneuverability and control of pitch, roll and yaw. Lift loss is 

delayed to higher angles of attack than in conventional aircraft. In 

(NASA-CASE-ARC-1 1 636-1 ; US-PATENT-APPL-SN-933963; NAS 

200 -/ 

07 

AIRCRAFT PROPULSION AND POWER 

Includes prime propulsion systems and systems components, e.g., 

gas turbine engines and compressors; and onboard auxiliary power 

plants for aircraft. 

N87-16828' 

Langley Research Center, Hampton, Va. 

OVER-THE-WING PROPELLER Patent 

JOSEPH L. JOHNSON, JR., inventor (to NASA) and E. RICHARD 

WHITE, inventor (to NASA) (Kentron International, Inc., Hampton, 

Va.) 16 Dec. 1986 9 p Continuation of US-Patent-Appl-SN-661478; 

dated 16 Oct. 1984, abandoned 

US-PATENT-CLASS-244-130) 

Office CSCL 21E 

This invention is an aircraft with a system for increasing the 

lift drag ratio over a broad range of operating conditions. The 

system positions the engines and nacelles over the wing in such 

a position that gains in propeller efficiency is achieved 

simultaneously with increases in wing lift and a reduction in wing 

drag. Adverse structural and torsional effects on the wings are 

avoided by fuselage mounted pylons which attach to the upper 

portion of the fuselage aft of the wings. Similarly, pylon-wing 

interference is eliminated by moving the pylons to the fuselage. 

Further gains are achieved by locating the pylon surface area aft 

of the aircraft center of gravity, thereby augmenting both directional 

and longitudinal stability. This augmentation has the further effect 

of reducing the size, weight and drag of empennage components. 

National Aeronautics and Space Administration. 

(NASA-CASE-LAR-13134-2; US-PATENT-4,629,147; 

US-PATENT-APPL-SN-846462; US-PATENT-CLASS-244-55; 

Avail: US Patent and Trademark 

2 
17 SPACE COMM., SPACECRAFT COMM., COMMAND & TRACKING 

The combination of design changes results in improved cruise 

performance and increased climb performance while reducing fuel 

consumption and drag and weight penalties. 

Official Gazette of the US Patent and Trademark Office 

09 

RESEARCH AND SUPPORT FACILITIES (AIR) 

Includes airports, hangars and runways; aircraft repair and overhaul 

facilities; wind tunnels; shock tubes; and aircraft engine test 

stands. 

N87-14355' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

DOUBLE WINDOW VIEWING CHAMBER ASSEMBLY Patent 

V. W. KELLER, inventor (to NASA), R. B. OWEN, inventor (to 

NASA), B. R. ELKINS, inventor (to NASA), and W. T. WHITE, 

inventor (to NASA) 21 Oct. 1986 6 p Filed 2 May 1985 

Supersedes N85-28951 (23 - 18, p 3063) 

Avail: US Patent and Trademark Office CSCL 14B 

A viewing chamber which permits observatior! of a sample 

retained therein includes a pair of double window assemblies 

mounted in opposed openings in the walls thereof so that a light 

beam can directly enter and exit from the chamber. A flexible 

mounting arrangement for the outer windows of the window 

assemblies enables the windows to be brought into proper 

alignment. An electrical heating arrangement prevents fogging of 

the outer windows whereas desiccated air in the volume between 

the outer and inner windows prevents fogging of the latter. 

Official Gazette of the US Patent and Trademark Office 

(NASA-CASE-MFS-28057-1; US-PATENT-4,618.21 5; 

US-PATENT-APPL-SN-729766; USPATENT-CLASS-350-3 1 9) 

14 

GROUND SUPPORT SYSTEMS AND FACILITIES 

(SPACE) 

Includes launch complexes, research and production facilities; 

ground support equipment, e.g., mobile transporters; and 

simulators. 

N87-15253'# National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

WEIGHTLESSNESS SIMULATION SYSTEM AND PROCESS 

Patent Application 

HUBERT C. VYKUKAL, inventor (to NASA) 29 Oct. 1986 14 p 

US-PATENT-APPL-SN-924398) 

CSCL 14B 

A weightlessness simulator has a chamber and a suit in the 

chamber. O-rings and valves hermetically seal the chamber. A 

vacuum pump connected to the chamber establishes a pressure 

in the chamber less than atmospheric pressure. A water supply 

tank and water supply line supply a body of water to the chamber 

as a result of partial vacuum created in the chamber. In use, an 

astronaut enters the pressure suit through a port, which remains 

open to ambient atmosphere, thus supplying air to the astronaut 

during use. The pressure less than atmospheric pressure in the 

chamber is chosen so that the pressure differential from the inside 

to the outside of the suit corresponds to the pressure differential 

with the suit in outer space. NASA 

(NASA-CASE-ARC-1 1646-1; NAS 1.71 :ARC-1 1646-1; 

Avail: NTlS HC AO2/MF A01 

17 

SPACE COMM., SPACECRAFT COMM., COMMAND 

& TRACKING 

Includes telemetry; space communications networks; 

astronavigation and guidance; and radio blackout. 

N87-16863' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

SINGLE FREQUENCY MULTITRANSMITTER TELEMETRY 

Patent 

VICTOR A. CARRENO, inventor (to NASA) 23 Dec. 1986 11 p 

Filed 28 Feb. 1983 Supersedes N83-20995 (21 - 11, p 1652) 

3 
18 SPACECRAFT DESIGN, TESTING AND PERFORMANCE 

(NASA-CASE-LAR-13006-1; US-PATENT-4,631,538; 

US-PATENT-APPL-SN-470113; US-PATENT-CLASS-340-870.1 8; 

US-PATENT-CLASS-340-825.5; US-PATENT-CLASS-371 -63; 

US-PATENT-CLASS-375-88) 

Office CSCL 09F 

The invention relates to a single frequency multitransmitter 

telemetry system that will deliver a substantial amount of data at 

low cost. The invention consists essentially of a plurality of sensor 

transmitter units at different locations, with individual signal 

conditioning and logic, which send sampled data signals to a single 

receiver. The transmitters operate independently on the same 

frequency in a frequency shift keying modulation system and are 

not synchronized to the receiver. The problem of reception of 

data from more than one transmitter simultaneously is solved by 

discarding the data - when there is overlap of data from two or 

more transmitters, the data is discarded and when there is no 

overlap the data is retained. The invention utilizes a unique overlap 

detection technique to determine if data should be retained or 

discarded. When data is received from a transmitter, it goes into 

a shift register. 

Official Gazette of the US Patent and Trademark Office 

toggle links which in the unfolded position of the members are 

nested against one of the members in substantial alignment and 

over-center for securely locking the joint in the unfolded position. 

Avail: US Patent and Trademark Official Gazette of the US Patent and Trademark Office 

' 

N87-14413'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

SYNCHRONOUSLY DEPLOYABLE DOUBLE FOLD BEAM AND 

PLANAR TRUSS STRUCTURE Patent Application 

M. D. RHODES, inventor (to NASA) and J. M. HEDGEPETH, 

inventor (to NASA) 22 Aug. 1986 14 p 

US-PATENT-APPL-SN-899683) 

CSCL 84G 

A deployable structure that synchronously deploys in both length 

and width is disclosed which is suitable for use as a structural 

component for orbiting space stations or large satellites. The 

structure is designed with maximum packing efficiency so that 

large structures may be collapsed and transported in the cargo 

bay of the Space Shuttle. The synchronous deployment feature 

allows the structure to be easily deployed in space by two 

astronauts, without a complex deployment mechanism. The 

structure is made up of interconnected structural units, each 

generally in the shape of a parallelepiped. The structural units are 

constructed of structural members connected with hinged and fixed 

connections at connection nodes in each corner of the 

parallelepiped. Diagonal members along each face of the 

parallelepiped provide structural rigidity and are equipped with 

mid-length, self-locking hinges to allow the structure to collapse. 

The structure is designed so that all hinged connections may be 

made with simple clevis-type hinges requiring only a single degree 

of freedom, and each hinge pin is located along the centerline of 

its structural member for increased strength and stiffness. NASA 

(NASA-CASE-LAR-13490-1; NAS 1.71:LAR-13490-1; 

Avail: NTlS HC A02/MF A01 

18 

SPACECRAFT DESIGN, TESTING AND 

PERFORMANCE 

Includes satellites; space platforms; space stations; spacecraft 

systems and components such as thermal and environmental 

controls; and attitude controls. 

N87-14373' National Aeronautics and Space Administration. 

Lyndon B. Johnson Space Center, Houston, Tex. 

FOLDABLE SELF-ERECTING JOINT Patent 

T. E. PELISCHEK. inventor (to NASA) 7 Oct. 1986 8 p Filed 

9 Mar. 1984 Supersedes N84-32424 (22 - 22, p 3542) 

(NASA-CASE-MSC-20635-1; US-PATENT-4,615,637; 

US-PATENT-APPL-SN-588039; US-PATENT-CLASS-403-85; 

US-PATENT-CLASS-403-1 02; US-PATENT-CLASS-403-1 19; 

US-PATENT-CLASS-403-1 46; US-PATENT-CLASS-403-1 63; 

US-PATENT-CLASS-1 6-294; US-PATENT-CLASS-I 6-370) Avail: 

US Patent and Trademark Office CSCL 228 

The invention relates to a foldable self erecting joint which 

may be used to deploy the tetratruss frame of the proposed shuttle 

launched triangular space station. The frame must be folded into 

the payload bay of the space shuttle orbiter. To deploy the frame 

the tubes are automatically unfolded and once in position should 

remain safely. A pair of hinged, tubular members in which the 

hinging is located at corresponding portions of the members are 

used. The opposite edge portions are connected by spring-based 

4 
18 SPACECRAFT DESIGN, TESTING AND PERFORMANCE 

N87-15259'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

SPACE SPIDER CRANE Patent Application 

IAN 0. MACCONOCHIE, inventor (to NASA), JACK E. 

PENNINGTON, inventor (to NASA), CHARLES F. BRYAN, JR., 

inventor (to NASA), MARTIN M. MIKULAS, JR., inventor (to NASA), 

and REBECCA L. KINKEAD, inventor (to NASA) 30 Sep. 1986 

18 P 

US-PATENT-APPL-SN-913432) Avail: NTlS HC AO2/MF A01 

CSCL 84G 

A space spider crane for the movement, placement, and/or 

assembly of various components on or in the vicinity of a space 

structure is described. As permanent space structures are utilized 

by the space program, a means will be required to transport cargo 

and perform various repair tasks. A space spider crane comprising 

a small central body with attached manipulators and legs fulfills 

this requirement. The manipulators may be equipped with constant 

pressure gripping end effectors or tools to accomplish various 

repair tasks. The legs are also equipped with constant pressure 

gripping end effectors to grip the space structure. Control of the 

space spider crane may be achieved either by computer software 

or a remotelv situated human oDerator. who maintains visual contact 

intersection of the track systems to change from longitudinal to 

transverse travel. The MRMS provides a near-uniform traversing 

velocity with minimal dynamic loading on the system. NASA 

(NASA-CASE-LAR-13411-15B; NAS 1.71:LAR-13411-1; 

via television cameras mounted on the space spider crane. One 

possible walking program COnSiStS Of a parallel motion walking 

program whereby the small central body alternatively leans foNyvai and backward relative to end effectors. 

~87.18595*# 

Lyndon B, 

LOCKING HINGE Patent ADDliCatiOn 

National Aeronautics and Space Administration. 

space center, Houston, Tex, 

21 

CLARENCE J. WESSELSKll'inventor (to NASA) 

16 P 

US-PATENT-APPL-SN-924397) Avail: NTlS HC AO2/MF A01 

CSCL 228 

The space station configuration currently being studied utilizes 

structures which require struts to be hinged in the middle in stowed 

configuration and locked into place in the deployed configuration. 

Since there are hundreds of hinges involved, it is necessary that 

they have simple, positive locking features with a minimum of 

joint looseness or slack. The instant invention comprises two similar 

housings hinged together with a spring loaded locking member 

which assists in making the lock as well as breaking it. The instant 

invention comprises a bracket hinge and bracket members with a 

spring biased and movable locking member. The locking or latch 

member has ear parts received in locking openings where wedging 

surfaces on the ear parts cooperate with complimentary surfaces 

on the bracket members for bringing the bracket members into a 

tight end-to-end alignment when the bracket members are in an 

extended position. When the locking member is moved to an 

1 unlocking position, pivoting of the hinge about a pivot pin 

automatically places the locking member to retain the locking 

member in an unlocked position. In pivoting the hinge from an 

extended position to a folded position, longitudinal spring members 

are placed under tension over annular rollers so that the spring 

tension in a folded position assists in return of the hinge from a 

folded position to an extended position. Novelty lies in the creation 

of a locking hinge which allows compact storage and easy assembly 

of structural members having a minimal number of parts. NASA 

29 Oct. 1986 

(NASA-CASE-MSC-21056-1; NAS 1.71 :MSC-21056-1; 

N87-15260'# National Aeronautics and Space Administration. 

Lyndon B. Johnson Space Center, Houston, Tex. 

MOBILE REMOTE MANIPULATOR SYSTEM FOR A 

TETRAHEDRAL TRUSS Patent Appllcation 

CLARENCE J. WESSELSKI, inventor (to NASA) and WILLIAM C. 

SCHNEIDER. inventor (to NASA) 5 Sep. 1986 25 p 

US-PATENT-APPL-SN-904134) 

CSCL 228 

The mobile remote manipulator system (MRMS) was initially 

developed for transit about the trusses of the delta space station; 

however, it can be utilized just as easily for transit about the 

trusses of the dual keel station. The MRMS is comprised of a 

mobile platform B having a rail system formed of transversely 

disposed T-shaped tracks, which engage with guide pins located 

at the nodes of the trusses. The guide pins form a arid and the 

(NASA-CASE-MSC-20985-1; NAS 1.71 :MSC-20985-1; 

Avail: NTlS HC AO2/MF A01 

5 

31 32 

tracks are so designed as to permit Gavel in either of two orthogonal 

directions. For travel the MRMS is provided with retractable, 

reversible chain drive systems, which selectively engage sprockets 

on the guide pins for either longitudinal or transverse travel. The 

MRMS IS also provided with direction changing means at the 

5 
18 SPACECRAFT DESIGN, TESTING AND PERFORMANCE 

N87-18596'# National Aeronautics and Space Administration. 

Lyndon 8. Johnson Space Center, Houston, Tex. 

SPACE STATION ERECTABLE MANIPULATOR PLACEMENT 

SYSTEM Patent Application 

MARGARET E. GRIMALDI, inventor (to NASA) 13 Nov. 1986 

13 P 

(NASA-CASE-MSC-21096-1; NAS 1.71 :MSC-21096-1; 

US-PATENT-APPL-SN-929865) Avail: NTlS HC A02/MF A01 

CSCL 228 

A habitable space station has been proposed for low Earth 

orbit, to be constructed from components which will be separately 

carried up from the Earth and thereafter assembled. A suitable 

manipulating system having extraordinary manipulative capability 

is required. The invention is an erectable manipulator placement 

system for use on a space station and comprising an elongate, 

lattice-like boom having guide tracks attached thereto, a 

carriage-like assembly pivotally mounted on and extending from 

said dolly. The system further includes a turntable base pivotally 

interconnected with the proximal end of the boom and positioned 

either on a part of a transferring vehicle, or on another payload 

component being carried by said transferring vehicle, or on the 

space station. Novelty resides in the use of a turntable base having 

a hinged boom with a dolly translatable therealong to carry the 

arm-like assembly, thus providing an additional 3 degrees of 

freedom to the arm. NASA 

N87-18597'# National Aeronautics and Space Administration. 

Lyndon 6. Johnson Space Center, Houston, Tex. 

EXPANDABLE PALLET FOR SPACE STATION INTERFACE 

ATTACHMENTS Patent Application 

CLARENCE J. WESSELSKI, inventor (to NASA) 13 Nov. 1986 

18 P 

(NASA-CASE-MSC-21117-1; NAS 1.71:MSC-21117-1; 

US-PATENT-APPL-SN-929875) 

CSCL 228 

The present invention is directed to a foldable expandable pallet 

having a basic square configuration. Each pallet is comprised of a 

plurality of struts joined together by node point fittings to make a 

rigid structure. The struts have hinge fittings which are spring 

loaded to permit collapse of the module for stowage transport to 

a space station in the payload bay of the space shuttle, and 

deployment on orbit. Dimensions of the pallet are selected to 

provide convenient, closely spaced attachment points between the 

node points of the relatively widely spaced trusses of a space 

station platform. A pallet is attached to a truss at four points: one 

close fitting hole; two oversize holes, and a slot which allows for 

thermal expansion/contraction and for manufacturing tolerances. 

Applications of the pallet include its use to attach rotary joints. 

Avail: NTlS HC AO2/MF A01 

Also, the pallet can serve as a splint with gridded plates; as 

instrument mounting bases; and as a roadbed for a Mobile Service 

Center (MSC). The novelty resides in providing closely spaced 

attachment points for mounting small components to the space 

station beams with widely spaced attachment points. The foldable 

expandable pallet removes the constraint that the main structure 

must have closely spaced node points for attachment purposes. 

Author 

I 

20 

SPACECRAFT PROPULSION AND POWER 

Includes main propulsion systems and components, e.g., rocket 

engines; and spacecraft auxiliary power sources. 

N87-10174'# National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

COAXIAL TUBE TETHER/TRANSMISSION LINE FOR MANNED 

NUCLEAR SPACE POWER Patent Application 

D. J. BENTS, inventor (to NASA) 

1.71:LEW-14338-1) Avail: NTlS HC AO2/MF A01 CSCL 108 

A spacecraft comprising a platform, a power system and a 

power transmission line adapted to transmitting high voltage 

electrical power in a space environment is disclosed. The 

transmission power line tethers the suborbiting platform to the 

power system located in a superorbital position relative to the 

platform. NASA 

18 Aug. 1986 15 p 

(NASA-CASE-LEW-14338-1; US-PATENT-APPL-SN-897239; NAS 

6 
23 CHEMISTRY AND MATERIALS (GENERAL) 

N87-14420' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

LOW LOSS INJECTOR FOR LIQUID PROPELLANT ROCKET 

ENGINES Patent 

G. L. VONPRAGENAU, inventor (to NASA) 11 Nov. 1986 10 p 

in an annular chamber surrounding the cylindrical chamber. 

Propellant gas flows through the annular chamber and is heated 

by the heat exchanger material. 

Official Gazette of the US Patent and Trademark Office 

(NASA-CASE-MFS-25989-1; US-PATENT-4,621,492; 

US-PATENT-APPL-SN-690273; US-PATENT-CLASS-60-258; 

US-PATENT-CLASS-60-746; US-PATENT-CLASS-239-1 32.5; 

US-PATENT-CLASS-239-425; US-PATENT-CLASS-239-403) 

Avail: US Patent and Trademark Office CSCL 21H 

A low pressure loss injector element is disclosed for the main 

combustion chamber of a rocket engine which includes a lox post 

terminating in a cylindrical barrel. Received within the barrel is a 

lox plug which is threaded in the lox post and includes an 

interchangeable lox metering sieve which meters the lox into an 

annular lox passage. A second annular gas passage is coaxial 

with the annular lox passage. A cylindrical sleeve surrounds the 

annular gas passage and includes an interchangeable gas metering 

seive having metering orifices through which a hot gas passes 

into the annular passage. The jets which emerge from the annular 

lox passage and annular gas passage intersect in a recessed 

area away from the combustion area. Thus, mixing and combustion 

stability are enhanced. 

Official Gazette of the US Patent and Trademark Office 

14 

23 

CHEMISTRY AND MATERIALS (GENERAL) 

N87-16875' National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

HEAT EXCHANGER FOR ELECTROTHERMAL DEVICES Patent 

RALPH J. ZAVESKY, inventor (to NASA), JAMES S. SOVEY, 

inventor (to NASA), MICHAEL J. MIRTICH, inventor (to NASA), 

CHARALAMPUS MARINOS, inventor (to NASA), and PAUL F. 

PENKO, inventor (to NASA) 2 Sep. 1986 7 p Filed 31 Jul. 

1984 Supersedes N84-32425 (22 - 22, p 3542) 

US-PATENT-CLASS-21 9-275) Avail: US Patent and Trademark 

Office CSCL 21H 

An improved electrothermal device is disclosed. An 

electrothermal thruster utilizes a generally cylindrical heat 

exchanger chamber to convert electricity to heat which raises the 

propellant temperature. A textured, high emissivity heat element 

radiatively transfers heat to the inner wall of this chamber that is 

ion beam morphologically controlled for high absorptivity. This, in 

turn, raises the temperature of a porous heat exchanger material 

(NASA-CASE-LEW-14037-1; US-PATENT-4,608,821; 

US-PATENT-APPL-SN-636463; US-PATENT-CLASS-60-203.1 ; 

7 

N87-14432'# 

Lewis Research Center, Cleveland, Ohio. 

PROCESSES FOR THEIR SYNTHESIS Patent Applicatjon 

W. B. ALSTON. inventor (to NASA) and R. F. GRATZ, inventor 

(to NASA) 29 Oct. 1986 24 p 

(NASA-CASE-LEW-14345-1; NAS 1.71 :LEW-14345-1; 

US-PATENT-APPL-SN-924474) 

CSCL 990 

Synthetic procedures are described for tetraalkyls, tetraacids 

and dianhydrides substituted 1,1,1 -irriaryl-2,2,2-trifluoroethanes 

which comprises: (1) 1.1 -bis(dialkylaryl)-1 aryl-2.2,2-trifluoroethane; 

(2) 1,l-bis(carboxyary1)-1 aryl-2,2,2-trifluoroethane; or (3) cyclic 

dianhydride or diamine of 1,l -bis(dialkylaryl)j-1 aryl-2,2,2-trifluoroethanes. The synthesis of (1) is accomplished by the condensation 

reaction of an aryltrifluoromethyl ketone with a dialkylaryl compound. 

The synthesis of (2) is accomplished by oxidation of (1). The synthesis 

dianhydride of (3) is accomplished by the conversion of (2) to its 

corresponding cyclic dianhydride. The synthesis of the diamine is 

accomplished by the similar reaction of an aryltrifluorornethyl ketone 

with aniline or alkyl substituted or disubstituted anilines. Also, other 

derivatives of the above are formed by nucleophilic displacement 

reactions. NASA 

National Aeronautics and Space Administration. 

SUBSTITUTED l,l,l-TRIARYL-2,2,2-TRlFLUOROETHANES AND 

Avail: NTlS HC A02/MF A01 
23 CHEMISTRY AND MATERIALS (GENERAL) 

N87-14433'# National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

NEW CONDENSATION POLYlMlDES CONTAINING 

l,l,l-TRIARYL-2,2,2-TRlFLUOROETHANE STRUCTURES Patent 

Application 

W. B. ALSTON and R. F. GRATZ, inventors (to NASA) 29 Oct. 

1986 27 p 

US-PATENT-APPL-SN-934470) 

CSCL 07A 

The invention relates to a condensation polyimide containing a 

1,1,1 -triaryl-2,2,2-trifluoroethane structure and other related 

condensation polyimides. The process for their preparation, which 

comprises polymerization of a cyclic dianhydride with a diamine is 

also covered. NASA 

(NASA-CASE-LEW-14346-1; NAS 1.71 114346-1; 

Avail: NTlS HC AO3/MF A01 

N87-15275*# National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

PREPARATION OF B-TRICHLOROBORAZINE Patent 

Application 

SALVATORE R. RICCITIELLO. inventor (to NASA), MING-TA S. 

HSU, inventor (to NASA), and TIMOTHY S. CHEN, inventor (to 

NASA) 28 Aug. 1986 11 p Sponsored by NASA 

US-PATENT-APPL-SN-901496) 

CSCL 07A 

A method of preparing B-trichloroborazine is disclosed. 

Generally, the method includes the combination of gaseous boron 

trichloride and excess gaseous ammonia at ambient temperature 

or below, under anhydrous conditions in a polar organic solvent, 

heating the reaction mixture to 100 to 140 C for a time effective 

to produce the trichloroborazine, cooling and removing the 

ammonium chloride formed, removing the solvent at ambient 

pressure, and recovering the B-trichloroborazine. A preferred 

solvent in the process is anhydrous toluene. Yields of 

B-trichloroborazine of about 40 percent are obtained. This process 

provides both a laboratory and larger-scale preparation from 

gaseous components. B-trichloroborazine is useful in a number of 

chemical reactions including the formation of high temperature 

inorganic polymers. NASA 

(NASA-CASE-ARC-1 1643-1-SB; NAS 1.71:ARC-11643-1-SB; 

Avail: NTlS HC AO2/MF A01 

24 

COMPOSITE MATERIALS 

Includes physical, chemical, and mechanical properties of laminates 

and other composite materials. 

spectrum from cryogenic temperature to about 900 C in a 

chemically reactive environment. The composites are comprised 

of silver, barium fluoride/calcium fluoride eutectic, and bonded 

chromium carbide. NASA 

IN HELIUM , , IN HYDROGEN 

TEUPEPAWRE 

N87-14442'# 

Ames Research Center, Moffett Field, Calif. 

SYSTEM AND METHOD THEREOF Patent Application 

S. R. RICCITIELLO, inventor (to NASA), M. SMITH, inventor (to 

NASA), H. GOLDSTEIN, inventor (to NASA), and N. B. 

ZIMMERMAN, inventor (to NASA) 14 May 1986 31 p 

US-PATENT-APPL-SN-862925) 

CSCL 11 D 

A ceramic reusable, externally applied composite thermal 

protection system (TPS) is proposed. The system functions by 

utilizing a ceramic/ceramic upper shell structure which effectively 

separates its primary functions as a thermal insulator and as a 

load carrier to transmit loads to the cold structure. The composite 

tile system also prevents impact damage to the atmospheric entry 

vehicle thermal protection system. The composite tile comprises 

a structurally strong upper ceramic/ceramic shell manufactured 

from ceramic fibers and ceramic matrix meeting the thermal and 

structural requirements of a tile used on a re-entry aerospace 

vehicle. In addition, a lightweight high temperature ceramic lower 

temperature base tile is used. The upper shell and lower tile are 

attached by means effective to withstand the extreme temperature 

(3000 to 3200 F) and stress conditions. The composite tile may 

include one or more layers of variable density rigid or flexible 

thermal insulation. The assembly of the overall tile is facilitated 

by two or more locking mechanisms on opposing sides of the 

overall tile assembly. The assembly may occur subsequent to the 

installation of the lower shell tile on the spacecraft structural skin. 

NASA 

National Aeronautics and Space Administration. 

CERAMIC-CERAMIC SHELL TILE THERMAL PROTECTION 

(NASA-CASE-ARC-1 1641-1; NAS 1.71:ARC-11641-1; 

Avail: NTlS HC AOWMF A01 

W 

N87-10179'# 

Lewis Research Center, Cleveland, Ohio. 

Patent Application 

H. E. SLINEY, inventor (to NASA) 5'May 1986 12 p 

1.71:LEW-14196-1) Avail: NTlS HC A02/MF A01 CSCL llD 

This invention relates to a self-lubricating, friction and wear 

reducing composite material for use over a wide temperature 

National Aeronautics and Space Administration. 

CARBIDE/FLUORIDE/SILVER SELF-LUBRICATING COMPOSITE 

(NASA-CASE-LEW-14196-1; USPATENT-APPL-SN-859688; NAS 

8 
25 INORGANIC AND PHYSICAL CHEMISTRY 

N87-18613'# 

Langley Research Center, Hampton, Va. 

MATRIX COMPOSITE STRUCTURES AND PROCESS FOR 

THEIR MANUFACTURE Patent Application 

RAYMOND M. BLUCK, inventor (to NASA) (Lockheed Missiles 

and Space Co., Sunnyvale, Calif.), HAROLD G. BUSH, inventor 

(to NASA), and ROBERT R. JOHNSON, inventor (to NASA) 21 

Oct. 1986 10 p 

US-PATENT-APPL-SN-921572) 

CSCL 11 D 

The invention relates to seamless metal clad filament reinforced 

resin matrix composite tubular structures and processes for their 

manufacture and is particularly useful in the construction of 

spacecraft and space structures. Metal clad composites make a 

significant advancement over those composite systems being used 

for both spacecraft and aircraft; however, the material consolidation 

and tooling advances necessary to realize the potential of such 

metal clad composites had not hitherto been achieved. Accordingly, 

it is an object of this invention to provide an efficient method of 

producing seamless metal clad composite structures. A metallic 

outer sleeve is provided which is capable of enveloping a hollow 

metallic inner member having continuous reinforcing fibers attached 

to the distal end thereof. Inner member is then introduced into 

outer sleeve until inner member is completely enveloped by outer 

sleeve. A liquid matrix material is then injected into the space 

between inner member and outer sleeve. A pressurized heat 

transfer medium is flowed through the inside of inner member, 

thereby forming a fiber reinforced matrix composite material. The 

wall thicknesses of both inner member and outer sleeve are then 

reduced to the appropriate size by chemical etching, to adjust the 

thermal expansion coefficient of the metal-clad composite structure 

to the desired value. The novelty of this invention resides in the 

development of a efficient method of producing seamless metal 

clad fiber reinforced organic matrix composite structures. NASA 

National Aeronautics and Space Administration. 

SEAMLESS METAL-CLAD FIBER-REINFORCED ORGANIC 

(NASA-CASE-LAR-13562-1; NAS 1.71 :LAR-13562-1; 

Avail: NTlS HC A02/MF A01 

25 

INORGANIC AND PHYSICAL CHEMISTRY 

Includes chemical analysis, e.g., chromatography; combustion 

theory; electrochemistry; and photochemistry. 

N87-18625'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

ISOTOPE SEPARATION USING TUNED LASER AND ELECTRON 

BEAM Patent Application 

SANDOR TRAJMAR, inventor (to NASA) 13 Nov. 1986 24 p 

(Contract NAS7-918) 

(NASA-CASE-NPO- 1 6907-1 -Cui US-PATENT-APPL-SN-9302 1 7; 

NAS 1.71:NPO-16907-1-CU) 

CSCL 20H 

High selectivity and economy have been attained by the 

apparatus of the present invention for producing and separating a 

stream of a selected isotope from an atomic beam containing a 

mixture of isotopes comprising means for producing an atomic 

beam containing the isotope of interest and other isotopes. Means 

are provided for producing a magnetic field traversing the path of 

the atomic beam of an intensity sufficient to broaden the energy 

domain of the various individual magnetic sublevels of the isotope 

of interest and having the atomic beam passing therethrough. A 

laser beam is produced of a frequency selected to maximize the 

activation of only individual magnetic sublevels of the isotope of 

interest within the portion of its broadened energy domain most 

removed from other isotopes within the beam. The laser beam is 

directed so as to strike the atomic beam within the magnetic field 

and traverse the path of the atomic beam whereby only the isotope 

of interest is activated by the laser beam. The apparatus further 

includes means for producing a collimated and high intensity beam 

of electrons of narrow energy distribution within the magnetic field 

which is aimed so as to strike the atomic beam while the atomic 

beam is simultaneously struck by the laser beam and at an energy 

level selected to ionize the activated isotope of interest but not 

ground state species included therein. Finally, deflection means 

are disposed in the usual manner so as to have the atomic beam 

pass therethrough after being struck by the electron beam so 

that the ionized isotope is deflected from the remainder of the 

beam to form a separate stream composed only of the isotope of 

interest. NASA 

Avail: NTlS HC A02/MF A01 

N87-18626'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

METHOD AND DEVICE FOR DETERMINING HEATS OF 

COMBUSTION OF GASEOUS HYDROCARBONS Patent 

Application 

JAG J. SINGH, inventor (to NASA), DANNY R. SPRINKLE, inventor 

(to NASA), and RICHARD L. PUSTER, inventor (to NASA) 24 

Nov. 1986 16 p 

US-PATENT-APPL-SN-933962) 

CSCL 21 B 

A method and device is provided for a quick, accurate and 

on-line determination of heats of combustion of gaseous 

hydrocarbons. First, the amount of oxygen in the carrier stream 

air is sensed by a oxygen sensing system. Second, three individual 

volumetric flow rates of oxygen, carrier stream air, and hydrocarbon 

test gas are introduced into a burner. The hydrocarbon test gas 

is fed into the burner at a volumetric flow rate, n, measured by a 

(NASA-CASE-LAR-13528-1; NAS 1.71 :LAR-13528-1; 

Avail: NTlS HC A02/MF A01 

9 
25 INORGANIC AND PHYSICAL CHEMISTRY 

flowmeter. Third, the amount of oxygen in the resulting combustion 

products is sensed by an oxygen sensing system. Fourth, the 

volumetric flow rate of oxygen is adjusted until the amount of 

oxygen in the combustion product equals the amount of oxygen 

previously sensed in the carrier stream air. This equalizing 

volumetric flow rate, m, is measured by the flowmeter. The heat 

of combustion of the hydrocarbon test gas is then determined 

from the ratio m/n. NASA 

N87-18627'# National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

MOVING WALL, CONTINUOUS FLOW ELECTROPHORESIS 

APPARATUS Patent Application 

PERCY H. RHODES, inventor (to NASA) 

US-PATENT-APPL-SN-904128) 

CSCL 07D 

This invention relates generally to electrophoresis devices and 

more particularly to a moving wall, continuous flow device wherein 

an electrophoresis chamber is angularly positionable with respect 

to the direction of moving belt walls. A frame having an 

electrophoresis chamber is rotatably supported between two 

synchronously driven belt walls. This allows the chamber to be 

angularly positionable with respect to the direction of belt travel, 

which compensates for electroosmatic flow within the 

electrophoresis chamber. Injection of a buffer solution via an 

opening and a homogenous sample stream via another opening 

is performed at end of a chamber, and collection of buffer and 

the fractionated species particles is done by a conventional 

collection array at an opposite end of the chamber. Belts are 

driven at a rate which exactly matches the flow of buffer and 

sample through the chamber, which entrains the buffer to behave 

as a rigid electrophoretic medium, eliminating flow distortions 

(Poiseuille effect). Additionally, belt material for each belt is stored 

at one end of the device and is taken up by drive reels at an 

opposite end. The novelty of this invention particularly lies in the 

electrophoresis chamber being angularly positionable between two 

moving belt walls in order to compensate for electoosmatic flow. 

Additionally, new belt material is continuously exposed within the 

chamber, minimizing flow distortions due to contamination of the 

belt material by the sample. NASA 

5 Sep. 1986 17 p 

Avail: NTlS HC A02/MF A01 

(NASA-CASE-MFS-28142-1; NAS 1.71 :MFS-28142-1; 

146 \ 

METALLIC MATERIALS 

Includes physical, chemical, and mechanical properties of metals, 

e.g., corrosion; and metallurgy. 

N87-10192'# National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

CASTABLE HOT CORROSION RESISTANT ALLOY Patent 

Application 

C. A. BARRETT, inventor (to NASA) and W. H. HOLT, inventor 

(to NASA) 30 Jul. 1986 8 p 

1.71:LEW-14134-1) Avail: NTlS HC AO2/MF A01 CSCL 11F 

About ten weight percent nickel is added to a Fe-base ferritic 

alloy to improve the high temperature castability and crack 

resistance while about 0.2 weight percent zirconium is added for 

improved high temperature cyclic oxidation and corrosion 

resistance. The basic material is a high temperature FeCrAl heater 

alloy, and the addition provides a material suitable for burner rig 

nozzles. NASA 

(NASA-CASE-LEW-14134-1; US-PATENT-APPL-SN-890584; NAS 

I -50 J" 

N87-14482' National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

NICKEL BASE COATING ALLOY Patent 

C. A. BARRETT, inventor (to NASA) and C. E. LOWELL, inventor 

(to NASA) 9 Sep. 1986 4 p Filed 23 Mar. 1983 Supersedes 

N83-24639 (21 - 14, p 2189) 

(NASA-CASE-LEW-13834-1; US-PATENT-4.610,736; 

US-PATENT-APPL-SN-47813 1 ; US-PATENT-CLASS-1 48-429; 

US-PATENT-CLASS-420-460) 

Office CSCL 11F 

Zirconium is added to a Ni-30 AI (beta) intermetallic alloy in 

the range of 0.05 w/o to 0.25 w/o. This addition is made during 

melting or by using metal powders. The addition of zirconium 

improves the cyclic oxidation resistance of the alloys at 

temperatures above 1100 C. 

Official Gazette of the US Patent and Trademark Office 

Avail: US Patent and Trademark 

N 

6 

z 

. 

J 

l3 

t 

a 

I 

V 

I 

W 

'3 

3 

u 

5 

n 

W V

u) 

0 Olllllllllr 600 1200 I800 2400 3000 

TIME, hr 

10 
27 NONMETALLIC MATERIALS 

27 

NONMETALLIC MATERIALS 

Includes physical, chemical, and mechanical properties of plastics, 

elastomers, lubricants, polymers, textiles, adhesives, and ceramic 

materials. 

N87-10205'# 

Ames Research Center, Moffett Field, Calif. 

CERAMIC MATERIALS THEREOF Patent Application 

S. R. RICCITIELLO, inventor (to NASA), M. T. S. HSU. inventor 

(to NASA) (Chem (H. C.) Research and Service Corp., San Jose, 

Calif.), and T. S. CHAN. inventor (to NASA) 30 Jul. 1986 20 p 

(NASA-CASE-ARC-1 1649-1 -SB; US-PATENT-APPL-SN-890577; 

NAS 1.71:ARC-11649-1-SB) Avail: NTlS HC A02/MF A01 

CSCL 11 B 

The present invention relates to organic silicon-boron polymers 

which upon pyrolysis produce high-temperature ceramic materials. 

More particularly, it relates to the polyorganoborosilanes containing 

-Si-B- bonds which generate high-temperature ceramic materials 

(e.g., Sic, SiB4, SiB6, B3C) upon thermal degradation. The 

processs for preparing these organic silicon-boron polymer 

precursors are also a part of this invention. M.G. 

National Aeronautics and Space Administration. 

BORON-CONTAINING ORGANOSllANE POLYMERS AND 

N87-10206'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

A METHOD OF ESTIMATING THE MOLECULAR WEIGHT OF 

POLYMERIC MATERIALS Patent Application 

J. R. TYERYAR, inventor (to NASA), B. J. JENSEN, inventor (to 

NASA), and R. L. FOX, inventor (to NASA) 14 p 

1.71:LAR-13212-1) Avail: NTlS HC AO2/MF A01 CSCL llB 

A rapid method to estimate the molecular weight of polymers 

by forming a film from the polymeric material and subjecting the 

newly formed film to a crease test to estimate molecular weight 

is disclosed. An induction heating apparatus, essentially as 

disclosed in US. Patent No. 4,521,659, is mounted in a hydraulic 

press. The polymeric material to be tested is placed between two 

sheets of high-temperature release film, which is placed between 

two conductive plates, which is placed between two layers of 

insulation to form a sandwich specimen fixture. Heat is applied 

rapidly to the fixture by the induction heating apparatus until a 

temperature above the melting point of the polymer is reached, 

while pressure is applied simultaneously by means of the hydraulic 

press. The temperature of the fixture is held constant for between 

one and five minutes, after which the fixture is cooled to a 

temperature below the glass transition temperature of the polymer, 

and the pressure is then released. The newly formed film is then 

22 Aug. 1986 

(NASA-CASE-LAR-13212-1; US-PATENT-APPL-SN-898986; NAS 

subjected to a crease test. If the film is creaseable and not brittle, 

the polymer is determined to be of sufficiently high molecular 

weight. NASA 

32 

lo 

N87-14515' 

Langley Research Center, Hampton, Va. 

Patent 

P. M. HERGENROTHER and B. J. JENSEN, inventors (to NASA) 

11 Nov. 1986 7 p Division of US-Patent-4,587,312. 

US-Patent-Appl-SN-613139, filed 23 May 1984 

Avail: US Patent and Trademark Office CSCL 07A 

Sulfone-ester polymers containing pendent ethynyl groups and 

a direct and multistep process for preparing them are disclosed. 

The multistep process involves the conversion of a pendent bromo 

group to the ethynyl group while the direct route involves reating 

hydroxy-terminated sulfone oligomer or polymers with a 

stoichiometric amount of 5-(4-ethynylphenoxy) isophthaloyl 

chloride. The 5-(4-ethynylphenoxy) isophthaloyl chloride and the 

process for preparing it are also disclosed. 

Official Gazette of the US Patent and Trademark Office 

National Aeronautics and Space Administration. 

THE 5-(4-ETHYNYLOPHENOXY) ISOPHTHALIC CHLORIDE 

(NASA-CASE-LAR-13316-2; US-PATENT-4,622,182; 

US-PATENT-APPL-SN-760791; US-PATENT-CLASS-260-544-P) 

N87-14516' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

ACETYLENE (ETHYNYL) TERMINATED POLYIMIDE SILOXANE 

AND PROCESS FOR PREPARATION THEREOF Patent 

T. L. STCLAIR and S. MAUDGAL, inventors (to NASA) (National 

Academy of Sciences - National Research Council, Washington, 

D. C.) 25 Nov. 1986 6 p Filed 30 Sep. 1985 Supersedes 

N86-21685 (24 - 12, p 1927) 

(NASA-CASE-LAR-13318-1; US-PATENT-4,624,888; 

US-PATENT-APPL-SN-781813; US-PATENT-CLASS-428-262; 

US-PATENT-CLASS-428-447; US-PATENT-CLASS-528-26) 

Avail: US Patent and Trademark Office CSCL 11 B 

Siloxane containing addition polyimides having improved 

physical property characteristics of flexibility, drape, tack, and 

toughness and the process for preparing and utilizing the same 

are disclosed. The novelty of this invention appears to reside in 

the composition and process of preparing addition type polyimides 

useful as structural adhesives as well as composite matrix materials 

and the process of preparing the same. 

Official Gazette of the US Patent and Trademark Office 

11 
27 NONMETALLIC MATERIALS 

N87-14517*# National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

FIBER REINFORCED CERAMIC MATERIAL Patent Application 

R. T. BHATT, inventor (to NASA) 

US-PATENT-APPL-SN-886149) 

CSCL 710 

Alternate layers of mats of specially coated Sic fibers and 

silicon monotapes are hot pressed in two stages to form a fiber 

reinforced ceramic material. In the first stage a die is heated to 

about 600 C in a vacuum furnace and maintained at this 

temperature for about one-half hour to remove fugitive binder. In 

the second stage the die temperature is raised to about 1000 C 

and the layers are pressed at between 35 MPa and 138 MPa. 

The resulting preform is placed in a reactor tube where a nitriding 

gas is flowed past the preform at 11 00 C to 1400 C to nitride the same. NASA 

16 Jul. 1986 14 p 

(NASA-CASE-LEW-14392-1; NAS 1.71 :LEW-l4392-1; 

Avail: NTlS HC AO2IMF A01 

N87-15304' 

Ames Research Center, Moffett Field, Calif. 

PROCESS FOR CURING BlSMALElMlDE RESINS Patent 

JOHN A. PARKER, inventor (to NASA), ALVIN H. HEIMBUCH, 

inventor (to NASA), MING-TA S. HSU. inventor (to NASA) (San 

Jose State Univ., Calif.), and TIMOTHY S. CHEN, inventor (to 

NASA) (San Jose State Univ., Calif.) 21 Oct. 1986 10 p 

Division of US-Patent-4,526,925, US-Patent-Appl-SN-553339, filed 

18 Nov. 1983 

National Aeronautics and Space Administration. 

(NASA-CASE-ARC-I 1429-4CU; US-PATENT-4,618,652; 

US-PATENT-APPL-SN-725686 US-PATENT-CLASS-525-282) 

Avail: US Patent and Trademark Office 

This invention relates to vinyl pyridine group containing 

compounds and oligomers, their advantageous copolymerization 

with bismaleimide resins, and the formation of reinforced 

composites based on these copolymers. When vinyl pyridines 

including vinyl stilbazole materials and vinyl styrylpyridine oligomer 

materials are admixed with bismaleimides and cured to form 

copolymers the cure temperatures of the copolymers are 

substantially below the cure temperatures of the bismaleimides 

alone. Official Gazette of the US Patent and Trademark Office 

CSCL 078 

N87-16907' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

ETHYNYL TERMINATED ESTER OLIGOMERS AND POLYMERS 

THEREFROM Patent 

PAUL M. HERGENROTHER, inventor (to NASA) and STEPHEN 

J. HAVENS, inventor (to NASA) (Kentron International, Inc., 

Hampton, Va.) 20 Jan. 1987 7 p 

Avail: US Patent and Trademark Office 

A new class of ethynyl-terminated ,oligomers and the process 

for preparing same are disclosed. Upon the application of heat, 

with or without a catalyst, the ethynyl groups react to provide 

crosslinking and chain extension to increase the polymer use 

temperature and improve the polymer solvent resistance. These 

improved polyesters are potentially useful in packaging, magnetic 

(NASA-CASE-LAR-I 31 18-2; US-PATENT-4,638,083; 

US-PATENT-APPL-SN-760797; US-PATENT-CLASS-560-1 04) 

CSCL 11 B 

tapes, capacitors, industrial belting, protective coatings, structural 

adhesives and composite matrices. 

Official Gazette of the US Patent and Trademark Office 

N87-16908' National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

VINYL STILBAZOLES Patent 

JOHN A. PARKER, inventor (to NASA), ALVIN H. HEIMBUCH, 

inventor (to NASA), MING-TA S. HSU, inventor (to NASA) (San 

Jose State Univ., Calif.), and TIMOTHY S. CHEN, inventor (to 

NASA) 2 Dec. 1986 9 p Division of US-Patent-4,526,925, 

US-Patent-Appl-SN-553339, dated 18 Nov. 1983 

(NASA-CASE-ARC-1 1429-3CU; US-PATENT-4,626,593; 

US-PATENT-APPL-SN-725725; US-PATENT-CLASS-546-339; 

US-PATENT-CLASS-546-346; US-PATENT-CLASS-546-350) 

Avail: US Patent and Trademark Office 

Vinyl pyridines including vinyl stilbazole materials and vinyl 

styrylpyridine oligomer materials are disclosed. These vinylpyridines 

form copolymers with bismaleimides which copolymers have good 

fire retardancy and decreased brittleness. The cure temperatures 

of the copolymers are substantially below the cure temperatures 

of the bismaleimides alone. Reinforced composites made from 

the cured copolymers are disclosed as well. 

Official Gazette of the US Patent and Trademark Office 

CSCL 11 B 

1 

N87-16909' National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

FIRE AND HEAT RESISTANT LAMINATING RESINS BASED ON 

MALEIMIDO SUBSTITUTED AROMATIC CYCLOTRIPHOSPHAZENE POLYMER Patent 

DEVENDRA KUMAR, inventor (to NASA) (National Academy of 

Sciences - National Research Council, Washington, D. C.), 

GEORGE M. FOHLEN, inventor (to NASA), and JOHN A. PARKER, 

inventor (to NASA) 6 Jan. 1987 20 p Division of 

US-Patent-4,550,177; US-Patent-Appl-SN-599126, dated 14 Apr. 

1984 

(NASA-CASE-ARC-I 1428-2; US-PATENT-4,634,759; 

US-PATENT-APPL-SN-760374; US-PATENT-CLASS-528-321; 

US-PATENT-CLASS-528-1 68; US-PATENT-CLASS-528-322; 

US-PATENT-CLASS-428-421 ;US-PATENT-CLASS-428-473.5; 

US-PATENT-CLASS-428-500; US-PATENT-CLASS-428-704) 

Avail: US Patent and Trademark Office CSCL 11 B 

4-Aminophenoxy cyclotriphosphazenes are reacted with maleic 

anhydride to produce maleamic acids which are converted to the 

maleimides. The maleimides are polymerized. By selection of 

starting materials (e.g., hexakis amino or trisaminophenoxy 

trisphenoxy cyclotriphosphazenes), selection of molar proportions 

of reactants, use of mixtures of anhydrides and use of dianhydrides 

as bridging groups a variety of maleimides and polymers are 

produced. The polymers have high limiting oxygen indices, high 

char yields and other useful heat and fire resistant properties 

making them useful as, for example, impregnants of fabrics. 

Official Gazette of the US Patent and Trademark Office 

1 

29 

MATERIALS PROCESSING 

Includes space-based development of products and processes for 

commercial applications. 

N87-18679'# 

Marshall Space Flight Center, Huntsville, Ala. 

National Aeronautics and Space Administration. 

12 
SPACE ULTRA-VACUUM FACILITY AND METHOD OF 

OPERATION Patent Application 

ROBERT J. NAUMANN, inventor (to NASA) 26 Sep. 1986 17 

P 

(NASA-CASE-MFS-28139-1; NAS 1.71 :MFS-28139-1; 

US-PATENT-APPL-SN-911851) 

CSCL 22A 

A wake shield facility providing an ultrahigh vacuum level for 

space processing is described. The facility is in the shape of a 

truncated, hollow hemispherical section, one side of the shield 

convex and the other concave. The shield surface is preferably 

made of material that has low out-gassing characteristics such as 

stainless steel. A material sample supporting fixture in the form of 

a carousel is disposed on the convex side of the shield at its 

apex. Movable arms, also on the convex side, are connected by 

the shield in proximity to the carousel, the arms supporting 

processing fixtures, and providing for movement of the fixtures to 

predetermined locations required for producing interations with 

material samples. For MBE processes a vapor jet projects a stream 

of vaporized material onto a sample surface. The fixtures are 

oriented to face the surface of the sample being processed when 

in their extended position, and when not in use they are retractable 

to a storage position. The concave side of the shield has a support 

structure includina metal struts connected to the shield, extendina 

Avail: NTlS HC AO2/MF A01 

radially inward. fhe struts are joined to 

parallel to the outer edge of the shield. 

outgassing contamination. 

an end plate dispose2 

This system eliminates 

NASA 

31 

ENGINEERING (GENERAL) 

Includes vacuum technology; control engineering; display 

engineering; cryogenics; and fire prevention. 

N87-15327'# 

Pasadena Office, Calif. 

HIGH INTENSITY CASTING SYSTEM Patent Application 

EARL R. COLLINS, JR., inventor (to NASA) 

P 

(Contract NAS7-918) 

(NASA-CASE-NPO-16901-1-CU; NAS 1.71 :NPO-16901-1-CU; 

US-PATENT-APPL-SN-921574) 

CSCL 13H 

A system is provided for casting thin sheets (or tapes) of 

particles bound together, that are used for oxygen membranes 

National Aeronautics and Space Administration. 

21 Oct. 1986 11 

Avail: NTlS HC AO2/MF A01 

31 ENGINEERING (GENERAL) 

and other applications, which enables the particles to be cast at 

a high packing density in a tape of uniform thickness. A slurry 

contains the particles, a binder, and a solvent, and is cast against 

the inside walls of a rotating chamber. Prior to spraying the slurry 

against the chamber walls, a solvent is applied to a container. 

The solvent evaporates to saturate the chamber with solvent vapor. 

Only then is the slurry cast. As a result, the slurry remains fluid 

long enough to spread evenly over the casting surface formed by 

the chamber, and for the slurry particles to become densely packed. 

Only then is the chamber vented to remove solvent, so the slurry 

can dry. The major novel feature is applying solvent vapor to a 

rotating chamber before casting slurry against the chamber walls. 

NASA 

)I 

2. 16 2 

N87-16918' National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

ELEVATED WATERPROOF ACCESS FLOOR SYSTEM AND 

METHOD OF MAKING THE SAME Patent 

MARC M. COHEN, inventor (to NASA) 20 Jan. 1987 9 p 

Filed 1 Jun. 1983 Supersedes N83-28281 (21 - 17, p 2736) 

(NASA-CASE-ARC-1 1363-1 ; US-PATENT-4,637,181; 

US-PATENT-APPL-SN-500046; US-PATENT-CLASS-52-1 26.5; 

US-PATENT-CLASS-52-309.1 5; US-PATENT-CLASS-52-391 ;

US-PATENT-CLASS-52-51 1 ; US-PATENT-CLASS-52-81 4) Avail: 

US Patent and Trademark Office CSCL 13B 

An elevated waterproof access floor system having subfloor 

channels or compartments for power lines, gas lines or the like is 

adapted such that it can be opened and subsequently resealed 

without destroying the waterproofing and without destroying its 

aesthetic appearance. A multiplicity of tiles are supported on a 

support grid, and a flooring sheet is supported on the tiles. 

Attachment means are provided to prevent lateral but not vertical 

movement of the flooring sheet with respect to the tiles so that 

the flooring sheet can be lifted off the tiles, but when the flooring 

sheet is supported on the tiles, no lateral slipping will occur. The 

flooring sheet is made of a heat resealable material, so that it 

can be cut away in sections, and the tiles therebelow lifted off, to 

provide access to subfloor Compartments. 

Official Gazette of the US Patent and Trademark Office 

13 
32 COMMUNICATIONS AND RADAR 

32 

COMMUNICATIONS AND RADAR 

Includes radar; land and global communications; communications 

theory; and optical communications. 

N87-14559' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

DOUBLE REFERENCE PULSED PHASE LOCKED LOOP Patent 

J. S. HEYMAN, inventor (to NASA) 25 Nov. 1986 6 p Filed 7 

Mar. 1985 Supersedes N85-21441 (23 - 12, p 1824) 

(NASA-CASE-LAR-13310.1; US-PATENT-4,624,142; 

US-PATENT-APPL-SN-709257; US-PATENT-CLASS-73-597; 

US-PATENT-CLASS-73-615 US-PATENT-CLASS-367-99; 

US-PATENT-CLASS-356-5) Avail: US Patent and Trademark 

Office CSCL 20N 

A double reference pulse phase locked loop is described which 

measures the phase shift between tone burst signals initially derived 

from the same periodic signal source (voltage controlled oscillator) 

and delayed by different amounts because of two different paths. 

A first path is from the transducer to the surface of a sample and 

back. A second path is from the transducer to the opposite surface 

and back. A first pulse phase locked loop including a phase detector 

and a phase shifter forces the tone burst signal delayed by the 

second path in phase quadrature with the periodic signal source. 

A second pulse phase locked loop including a second phase 

detector forces the tone burst signals delayed by the first path 

into phase quadrature with the phase shifted periodic signal 

source. Official Gazette of the US Patent and Trademark Office 

N87-15390'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

GROUND PLANE INTERFERENCE ELIMINATION BY PASSIVE 

ELEMENT Patent Application 

MARK E. BONEBRIGHT, inventor (to NASA) and DERLING 

KILLION, inventor (to NASA) 30 Jul. 1986 12 p 

(Contract NAS7-918) 

(NASA-CASE-NPO-16632-1-CU; NAS 1.71:NPO-16632-1-CU; 

US-PATENT-APPL-SN-890586) 

CSCL 178 

The radiation pattern of a beam at elevation angles near the 

horizon is improved for phased array antennas by control of the 

radiation field intensity near the horizon to reduce multipath 

disturbances, and to improve the axial ratio of a circularly polarized 

phased array antenna. This is accomplished by placing a parasitic 

phase shifting element directly below the antenna beam axis. The 

waveguide section is designed to produce a phase shift in the 

portion of antenna radiation energy passing through it to cancel 

some of the radiation energy in the direction of the horizon. The 

spacing of the waveguide section in front of the antenna is 

determined empirically for optimum results, i.e., for reduction of 

Avail: NTlS HC AO2/MF A01 

14 

beam power below about 20 deg. without affecting beam power 

at high elevation angles. NASA 

/ 

N87-18691'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

TRELLIS CODED MODULATION FOR TRANSMISSION OVER 

FADING MOBILE-SATELLITE CHANNEL Patent Application 

MARVIN K. SIMON, inventor (to NASA) (Jet Propulsion Lab., 

California Inst. of Tech., Pasadena) and DARIUSH DIVSALAR, 

inventor (to NASA) 9 Dec. 1986 52 p 

(Contract NAS7-918) 

(NASA-CASE-NPO-16904-1-CU; NAS 1.71:NPO-16904-1-CU; 

US-PATENT-APPL-SN-929876) 

CSCL 178 

The combination of trellis coding and Multiple Pulse Shift Keying 

(MPSK) signaling with asymmetry (nonuniform spacing) to the signal 

set is disclosed with regard to its suitability for a fading mobile 

satellite communication channel. For MPSK signaling, introducing 

nonuniformity in the phase spacing between signal points provides 

an improvement in performance over that achievable with trellis 

coded symmetric MPSK signaling, all this without increasing the 

average or peak power, or changing the bandwidth constraints 

imposed on the system. Block interleaving may be used to reduce 

error and pilot tone(s) may be used for improving the error 

correction performance of the trellis decoder in the presence of 

channel fading. NASA 

Avail: NTlS HC A04/MF A01 

N87-18692'# National Aeronautics and Space Administration, 

Lyndon 6. Johnson Space Center, Houston, Tex. 

METHOD AND APPARATUS FOR MEASURING FREQUENCY 

AND PHASE DIFFERENCE Patent Applicatlon 

PAUL SHORES, inventor (to NASA), CHRISTOPHER 

LICHTENBERG, inventor (to NASA), HERBERT S. KOBAYASHI, 

inventor (to NASA), and ALLEN R. CUNNINGHAM, inventor (to 

NASA) 29 Oct. 1986 31 p 

1.71:MSC-20865-1) Avail: NTlS HC AO3/MF A01 CSCL 20N 

The present invention is a system for deriving direct digital 

indications of frequency and phase difference between two 

incoming pulse trains adaptable for collision avoidance systems 

or the like. A pair of radar beams are directed toward a target 

(NASA-CASE-MSC-20865-1; US-PATENT-APPL-SN-924472; NAS 
33 ELECTRONICS AND ELECTRICAL ENGINEERING 

and corresponding beams returning therefrom are detected. A 

digital difference circuit forms a pulse train from the Doppler shift 

frequencies of each beam pair having a repetition rate functionally 

related to the difference in magnitude of the shift frequencies. 

Pulses from the pulse train are counted as a function of time. 

Visual indications thereof on display are correlative to target position 

relative to beams. NASA 

86 

' I -a- BP I. PEST 

33 

ELECTRONICS AND ELECTRICAL ENGINEERING 

N87-14594' National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

METHOD OF EXAMINING MICROCIRCUIT PATTERNS Patent 

S. F. SUSZKO, inventor (to NASA) (Jet Propulsion Lab., California 

Inst. of Tech., Pasadena) 18 Nov. 1986 10 p Filed 13 Oct. 

1983 Supersedes N85-20250 (23 - 11, p 1628) Sponsored by 

NASA 

(NASA-CASE-NPO-16299-1; US-PATENT-4,623,255; 

Avail: US Patent and Trademark Office CSCL 09C 

Examination of microstructures of LSI and VLSl devices is 

facilitated by employing a method in which the device is 

photographed through a darkfield illumination optical microscope 

and the resulting negative subjected to inverse processing to form 

a positive on a photographic film. The film is then developed to 

form photographic prints or transparencies which clearly illustrate 

the structure of the device. The entire structure of a device may 

be examined by alternately photographing the device and 

selectively etching layers of the device in order to expose underlying 

layers. Official Gazette of the US Patent and Trademark Office 

US-PATENT-APPL-SN-541526; US-PATENT-CLASS-356-389) 

Includes test equipment and maintainability; components, e.g.. 

tunnel diodes and transistors; microminiaturization; and integrated 

circuitry. 

N87-10231*# 

Pasadena Office, Calif. 

CROSS-CONTACT CHAIN Patent Application 

U. LIENEWEG, inventor (to NASA) 26 Jun. 1986 16 p 

(Contract NAS7-918) 

1.71:NPO-16784-1) Avail: NTlS HC A02/MF A01 CSCL 09A 

A system is provided for use with wafers that include multiple 

integrated circuits that include two conductive layers in contact at 

multiple interfaces. Contact chains are formed beside the integrated 

circuits, each contact chain formed of the same two layers as the 

circuits, in the form of conductive segments alternating between 

the upper and lower layers and with the ends of the segments 

connected in series through interfaces. A current source passes a 

current through the series-connected segments, by way of a pair 

of current tabs connected to opposite ends of the series of 

segments. While the current flows, voltage measurements are taken 

between each of a plurality of pairs of voltage tabs, the two tabs 

of each pair connected to opposite ends of an interface that lies 

along the series-connected segments. A plot of interface 

conductances on normal probability chart enables prediction of 

the yield of good integrated circuits from the wafer. NASA 

National Aeronautics and Space Administration. 

(NASA-CASE-NPO-16784-1; US-PATENT-APPL-SN-879757; NAS 

r 

N87-15413'# 

Pasadena Office, Calif. 

LARGE TV DISPLAY SYSTEM Patent Application 

HUA-KUANG LIU, inventor (to NASA) 30 Sep. 1986 11 p 

(Contract NAS7-918) 

(NASA-CASE-NPO-16932-1 CU; NAS 1.71 :NPO-16932-1; 

US-PATENT-APPL-SN-913433) 

CSCL 09c 

A relatively small and low cost system is provided for projecting 

a large and bright television image onto a screen. A miniature 

liquid crystal array is driven by video circuitry to produce a pattern 

of transparencies in the array corresponding to a television image. 

Light is directed against the rear surface of the array to illuminate 

it, while a projection lens lies in front of the array to project the 

image of the array onto a large screen. Grid lines in the liquid 

crystal array are eliminated by a spacial filter which comprises a 

negative of the Fourier transform of the grid. NASA 

National Aeronautics and Space Administration. 

Avail: NTlS HC AO2/MF A01 

I 10 

15 
33 ELECTRONICS AND ELECTRICAL ENGINEERING 

N87-15414'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

COAXIAL CABLE CONNECTOR Patent Application 

EDWARD CARO. inventor (to NASA) and WALTER J. BONAZZA, 

inventor (to NASA) 8 Sep. 1986 10 p 

(Contract NAS7-918) 

(NASA-CASE-NPO-16964-1 CU; NAS 1.71 :NPO-I 6764-1 ; 

US-PATENT-APPL-SN-704513) Avail: NTlS HC AO2/MF A01 

CSCL 09c 

A coaxial cable connector is provided, which resists radio 

frequency breakdown in coaxial cables used in the vacuum of 

outer space. The connector body surrounds an insulator which 

includes an easily compressible elastomeric portion. An insulated 

coaxial cable is prepared so its insulation projects beyond the 

outer conductor and compresses the elastomeric portion of the 

connector insulator. NASA 

N87-18761'# National Aeronautics and Space Administration. 

Langley Research Center, Harnpton, Va. 

FREQUENCY DOMAIN LASER VELOCIMETER SIGNAL Patent 

Application 

JAMES F. MEYERS, inventor (to NASA), JOHN W. STROUGHTON, 

inventor (to NASA) (Old Dominion Univ., Norfolk, Va.), JAMES I. 

CLEMMONS, JR., inventor (to NASA), SHARAD V. KANETKAR, 

inventor (to NASA), and ANDREAS E. SAVAKIS, inventor (to 

NASA) 24 Nov. 1986 23 p 

(NASA-CASE-LAR-13552-1-CU; NAS 1.71:LAR-13552-1-CU; 

US-PATENT-APPL-SN-933941) Avail: NTlS HC A02/MF A01 

CSCL 09c 

The invention is a signal processor for measuring the oscillating 

frequency contained in a laser velocimeter signal burst or bursts. 

The input to the signal processor is applied through a fixed gain 

amplifier to an amplifier that has an automatic gain control provided 

by automatic gain circuit. The output from amplifier 14 is converted 

to digital by a non-linear analog-to-digital converter (ADC). The 

output from ADC 16 is shifted into two shift registers with a register 

receiving the most significant bits (MSB) from the ADC and with 

register receiving the least significant bits (LSB) from the ADC. A 

signal integration circuit under the control of the bits shifted into 

and out of the MSB shifter register determines when a signal 

burst has been captured by the shift registers. When a signal 

burst has been captured the data in the shift registers is transferred 

and processed by a bank of digital filters and other circuitry to 

determine the frequency in the signal burst. The automatic gain 

circuit is under the control of the bits shifted into and out of both 

shift registers. The novel feature of the invention appears to lie in 

the overall combination of the signal integration circuit, the 

automatic gain circuit with amplifiers, the ADC, the shift registers 

and the digital filter circuitry for processing captured signal bursts. 

NASA 

34 

FLUID MECHANICS AND HEAT TRANSFER 

Includes boundary layers; hydrodynamics; fluidics; mass transfer; 

and ablation cooling. 

N87-18778'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

THIN-ELEMENT RIBLET SURFACE Patent Application 

STEPHEN P. WILKINSON, inventor (to NASA) 21 Oct. 1986 

13 P 

(NASA-CASE-LAR-13553-1; NAS 1.71 :LAR-13553-1; 

US-PATENT-APPL-SN-921575) 

CSCL 20D 

The thin-element riblet surface of this invention is a modification 

of the traditional smooth flow surfaces used in aerodynamic or 

hydrodynamic applications. This modification is made by adding 

an array of very thin elements projecting from an otherwise smooth, 

impervious surface and forming small, adjacent, rectangular 

channels on the surface which are aligned with the flow. When 

the riblets are closely spaced, the normal process of turbulence 

production takes place above the peaks of the riblets. When the 

riblets are widely spaced, vortices form within the channels in 

pairs with opposite rotations at each riblet. The vortex rotation is 

such that turbulence production is localized above the vortices. In 

either case, the area immediately above the surface remains 

relatively quiet. NASA 

Avail: NTlS HC AO2/MF A01 

, 

16 
35 INSTRUMENTATION AND PHOTOGRAPHY 

I. 

N87-18779"# National Aeronautics and Space Administration. 

Lyndon B. Johnson Space Center, Houston, Tex. 

HIGH EFFECTIVENESS CONTOUR MATCHING CONTACT HEAT 

EXCHANGER Patent Appllcation 

ROBERT L. BLAKELY, inventor (to NASA), GEORGE J. 

ROEBELEN, JR., inventor (to NASA), and ARTHUR K. 

DAVENPORT, inventor (to NASA) 19 Dec. 1986 11 p 

US-PATENT-APPL-SN-943346) 

CSCL 20D 

There is a need in the art for a heat exchanger design having 

a flexible core which provides contour matching capabilities, which 

compensates for manufacturing tolerance and distortion buildups, 

and which accordingly furnishes a relatively uniform thermal contact 

conductance between the core and external heat sources under 

essentially all operating conditions. The core of the heat exchanger 

comprises a top plate and a bottom plate, each having alternating 

rows of pins attached thereto. Each of the pins fits into 

corresponding tight-fitting recesses in the opposite plate. Thus, 

the pin and recess design allows the heat exchanger core to 

expand the contract to match the mating part contours without 

significantly affecting the flow distribution, since gaps of varying 

thickness are not created at the ends of pins by the thermal 

expansion and contraction of the plates. Novelty resides in the 

use of recesses for one end of the pins to maintain the pins in 

thermal contact with both plates despite the nonuniform distance 

between the plates. NASA 

(NASA-CASE-MSC-20840-1; NAS 1.71 :MSC-20840-1; 

Avail: NTlS HC AO2/MF A01 

20 / 

2f 72 

INSTRUMENTATION AND PHOTOGRAPHY 

by a detector and processed by a boxcar averager. The lens and 

corner cube combination, called a retrometer, ensure that the 

measurements are unaffected by vibrations. 

Official Gazette of the US Patent and Trademark Office 

N87-14670' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

EMITTED VIBRATION MEASUREMENT DEVICE AND METHOD 

Patent 

G. L. GISLER, inventor (to NASA) (Sperry Corp., Phoenix, Ariz.) 

28 Oct. 1986 9 D Filed 3 Oct. 1984 Suoersedes N85-20299 

(23 - 11, p 1635) 

(NASA-CASE-MFS-25981-1: US-PATENT-4.61 9.1 42: 

US-PATENT-APPL-SN-657310; US-PATENT-CbSS-73-462; 

US-PATENT-CLASS-73-473; US-PATENT-CLASS-73-477) Avail: 

US Patent and Trademark Office CSCL 14B 

This invention is directed to a method and apparatus for 

measuring emitted vibrational forces produced by a reaction wheel 

assembly due to imbalances, misalignment, bearing defects and 

the like. The apparatus includes a low mass carriage supported 

on a large mass base. The carriage is in the form of an octagonal 

frame having an opening which is adapted for receiving the reaction 

wheel assembly supported thereon by means of a mounting ring. 

The carriage is supported on the base by means of air bearings 

which support the carriage in a generally frictionless manner when 

supplied with compressed air from a source. A plurality of carriage 

brackets and a plurality of base blocks provided for physical 

coupling of the base and carriage. The sensing axes of the load 

cells are arranged generally parallel to the base and connected 

between the base and carriage such that all of the vibrational 

forces emitted by the reaction wheel assembly are effectively 

transmitted through the sensing axes of the load cells. In this 

manner, a highly reliable and accurate measurment of the 

vibrational forces of the reaction wheel assembly can be had. 

The output signals from the load cells are subjected to a dynamical 

analyzer which analyzes and identifies the rotor and spin bearing 

components which are causing the vibrational forces. 

Official Gazette of the US Patent and Trademark Office 

Includes remote sensors; measuring instruments and gages; 

detectors; cameras and photographic supplies; and holography. 

N87-14669' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

R. J. EXTON, inventor (to NASA) 25 Nov. 1986 9 p Filed 25 

Apr. 1985 Supersedes N85-29216 (23 - 18, p 3104) 

US-PATENT-CLASS-356-301 ) Avail: US Patent and Trademark 

Office CSCL 148 

A method and apparatus unaffected by vibrational environments 

for obtaining measurements using Raman Doppler Velocimetry is 

described. Two laser beams, a pump beam, and a probe beam, 

are focused by a lens to a point in a flow. A lens collimates the 

two beams. A beam splitter dumps the beam and the other beam 

is reflected by a corner cube back to the lens. The other lens 

then focuses the beam back to the point. The reflected beam 

and the backward and forward scattering at the point are detected 

VIBRATION-FREE RAMAN DOPPLER VELOCIMETER Patent 

(NASA-CASE-LAR-13268-1; US-PATENT-4,624,561 ; 

US-PATENT-APPL-SN-727034; US-PATENT-CLASS-356-28.5; 

17 

I 
35 INSTRUMENTATION AND PHOTOGRAPHY 

N87-14671* 

Goddard Space Flight Center, Greenbelt, Md. 

SPECTROMETER Patent 

G. E. ALCORN, inventor (to NASA) and A. S. BURGESS, inventor 

(to NASA) 21 Oct. 1986 7 p Filed 18 Jun. 1985 Supersedes 

National Aeronautics and Space Administration. 

METHOD OF FABRICATING AN IMAGING X-RAY 

N86-20754 (24 - 11, p 1776) 

(NASA-CASE-GSC-12956-1; US-PATENT-4,618.380; 

US-PATENT-APPL-SN-745977; US-PATENT-CLASS1 48-1 87; 

US-PATENT-CLASS1 48-1 88; US-PATENT-CLASS-1 48-1 89; 

US-PATENT-CLASS1 48-1 90 US-PATENT-CLASS-29-580; 

US-PATENT-CLASS-29-591) Avail: US Patent and Trademark 

Office CSCL 148 

A process for fabricating an X-ray spectrometer having imaging 

and energy resolution of X-ray sources is discussed. The 

spectrometer has an ariay oi adjoinging rectangularly shaped 

detector cells formed in a silicon body. The walls of the cells are 

created by laser drilling holes completely through the silicon body 

and diffusing n(+) phosphorous doping material therethrough. A 

thermally migrated aluminum electrode is formed centrally through 

each of the cells. 

Official Gazette of the US Patent and Trademark Office 

N87-14675'# National Aeronautics and Space Administration. 

Langley Research Center, Harnpton. Va. 

DEVICE FOR QUICK CHANGEOVER BETWEEN WIND TUNNEL 

FORCE AND PRESSURE TESTlNG Patent Appllcation 

R. M. WOOD, inventor (to NASA) 28 Aug. 1986 10 p 

US-PATENT-APPL-SN-901113) Avail: NTlS HC AO2/MF A01 

CSCL 828 

This device allows for expeditious and repeated changeovers 

between pressure and force testing and which uses a minimum 

internal volume of a wind tunnel test structure. A matrix 

configuration of holes is located on the outer surface of the 

structure. Pressure tubes lead through the internal cavity of the 

structure from test sites to this outer surface matrix configuration. 

A pressure tube connector with a corresponding matrix of holes 

is connected to the surface of the structure. Pressure tubes leading 

from remotely located transducers are joined to the connector, 

thus forming pressure passageways from the test sites to the 

transducers to allow for pressure testing. When force testing is 

required, the pressure tube connector is disconnected and a cover 

plate is connected. The cover plate seals the exposed internal 

pressure tubes. Also, the outer surface of the cover plate conforms 

to the exterior of the structure, providing the necessary smooth 

surface for force testing. If further pressure testing is required, 

the cover plate can be disconnected and the pressure tube 

connector reconnected. The novelty of this invention resides in 

the development of a device which allows for an expeditious 

changeover between wind tunnel force and pressure testing 

(NASA-CASE-LAR-13512-1; NAS 1.71 :LAR-13512-1; 

involving numerous test sites while utilizing a minimum internal 

volume of the test structure. NASA 

N87-14676'#' National Aeronautics and Space Administration. 

Lyndon B. Johnson Space Center, Houston, Tex. 

ACOUSTIC EMISSION FREQUENCY DISCRIMINATION Patent 

Application 

F. E. SUGG, inventor (to NASA) (Rockwell International Corp., 

Thousand Oaks, Calif.) and L. J. GRAHAM 12 Jun. 1986 17 p 

Sponsored by NASA 

US-PATENT-APPL-SN-874319) 

CSCL 148 

In acoustic emission nondestructive testing, broadband 

frequency noise is distinguished from narrow banded acoustic 

emission signals, wherein the latter are valid events indicative of 

structural flaws in the material being examined. This is 

accomplished by separating out those signals which contain 

frequency components both within and beyond (either above or 

below) the range of valid acoustic emission events. Application to 

acoustic emission monitoring during nondestructive bond 

verification and proof loading of undensified tiles on the space 

shuttle orbiter is considered. NASA 

(NASA-CASE-MSC-20467-1; NAS 1.71 :MSC-20467-1; 

Avail: NTlS HC A02/MF A01 

N87-15452'# 

Lewis Research Center, Cleveland, Ohio. 

GAS PARTICLE RADIATOR Patent Applicatlon 

DONALD L. CHUBB, inventor (to NASA) 

US-PATENT-APPL-SN-917125) 

CSCL 828 

A gas particle radiator adapted to operate in a microgravity 

space environment having a transparent boundary which transmits 

National Aeronautics and Space Administration. 

9 Oct. 1986 8 p 

(NASA-CASE-LEW-14297-1; NAS 1.71 :LEW-14297-1; 

Avail: NTlS HC AO2/MF A01 

1 

18 
energy in the infrared spectrum, and a gas particle mixture that 

yields high absorption and emittances are described. NASA 

r 1 16 

LASERS AND MASERS 

Includes parametric amplifiers. 

N87-17026' National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

PROJECTION LENS SCANNING LASER VELOCIMETER 

SYSTEM Patent 

WILLIAM D. GUNTER, JR., inventor (to NASA) and ANEMARIE 

DEYOUNG, inventor (to NASA) 30 Dec. 1986 7 p Filed 18 

Jan. 1985 Supersedes N85-20320 (23 - 11, p 1638) 

US-PATENT-CLASS-356-28) Avail: US Patent and Trademark 

Office CSCL 20E 

A laser Doppler velocimeter system is disclosed that has a 

laser, a waist position adjusting lens, and a beam splitter which 

direct laser beams parallel to the optical axis of the negative 

lens. The negative lens is fixed relative to an afocal lens pair. A 

pair of planar mirrors intersect at right angles and respectively 

intersect the optical axis and the optical axis of the afocal lens 

pair. Mirrors are movable along the optical axis toward and away 

from the afocal lens pair to focus the laser beams in focus area 

while maintaining a constant beam waist, crossing angle, and 

intersection with other laser beams. This produces a constant 

sensitive volume as the focus is changed. 

Official Gazette of the US Patent and Trademark Office 

(NASA-CASE-ARC-1 1547-1 ; US-PATENT-4,632,548; 

US-PATENT-APPL-SN-692745; US-PATENT-CLASS-356-28.5; 

37 MECHANICAL ENGINEERING 

37 

MECHANICAL ENGINEERING 

Includes auxiliary systems (nonpower); machine elements and 

processes; and mechanical equipment. 

N87-14704'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

ACTIVE HOLDDOWN FOR HEAT TREATING Patent 

Application 

E. R. COLLINS, JR., inventor (to NASA) 

(Contract NAS7-918) 

US-PATENT-APPL-SN-921573) 

CSCL 131 

The object of the disclosure is to provide a vacuum hold-down 

for holding thin sheets to a support surface, which permits the 

thin sheet to change dimensions as it is held down. The hold-down 

includes numerous holes in the support surface, through which a 

vacuum is applied from a vacuum source. The holes are arranged 

in zones. The vacuum is repeatedly interrupted at only one or a 

few zones, while it continues to be applied to other zones, to 

allow the workpiece to creep along that interrupted zone. The 

vacuum to different zones is interrupted at different times, as by 

a slowly turning valve number, to allow each zone of the workpiece 

to creep. A positive pressure may be applied from a pressured air 

source to a zone when the vacuum is interrupted there, to help 

lift the corresponding workpiece zone off the surface to aid in 

creeping. The workpiece may undergo dimensional changes 

because of heating, cooling, drying, or other procedure. NASA 

21 Oct. 1986 12 p 

(NASA-CASE-NPO-16892-1-CU; NAS 1.71 :NPO-16892-1-CU; 

Avail: NTlS HC A02/MF A01 

N87-14705'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

PASSIVELY ACTIVATED PREHENSILE DIGIT FOR A ROBOTIC 

END EFFECTOR Patent Application 

E. R. COLLINS, JR., inventor (to NASA) 21 Oct. 1986 14 p 

(Contract NAS7-918) 

US-PATENT-APPL-SN-921577) Avail: NTlS HC AO2/MF A01 

CSCL 131 

A common hydraulic reservoir holds one or more rows of slidable 

pistons or fingers in a base or hand. The individual fingers in 

each row expose graduated cross-sectional fluid application areas 

to the hydraulic fluid in the reservoir, with the smallest fluid 

application area in the center of the row and graduating to 

progressive larger fluid areas towards both ends of each row. 

The fingers are elongated pistons. Exposed outer ends of each 

piston extending away from the reservoir, house a transverse pad 

to contact an object to be held. The transverse pads are universally 

ball-joint and spring-center mounted in a longitudinally located 

(NASA-CASE-NPO-16766-1-CU; NAS 1.71 :NPO-16766-1 -Cui 

19 
37 MECHANICAL ENGINEERING 

opening at the outer tapered end of each finger. Simple and 

effective capacitance metering in the reservoir is provided for each 

finger. NASA 

N87-15464*# 

Langley Research Center, Hampton, Va. 

COMPOSITE PISTON Patent Application 

ALLAN H. TAYLOR, inventor (to NASA) 30 Jul. 1986 17 p 

US-PATENT-APPL-SN-890683) Avail: NTlS HC AO2/MF A01 

CSCL 940 

A composite piston structure is disclosed which provides a 

simple and reliable means for joining a carbon-carbon or ceramic 

piston cap with a metallic piston body. Attachment is achieved by 

means of a special geometry which compensates for differences 

in thermal expansion without complicated mechanical fastening 

devices. The shape employs a flange created by opposed 

frustoconical shapes with coincident vertices intersecting on the 

radial centerline of the piston in order to retain the piston cap. 

The use of carbon-carbon for the piston cap material allows a 

close fit between the piston and a cylinder wall, eliminating the 

need for piston rings. The elimination of extra mechanical parts of 

previous composite pistons provides a lightweight composite piston 

capable of extended high temperature operation. NASA 

National Aeronautics and Space Administration. 

(NASA-CASE-LAR-13435-1; NAS 1.71 :LAR-13435-1; 

'51 rl2 

extraction. A piston operating in a first chamber draws a solvent 

into the first chamber where it may be heated, and then moves 

the heated solvent into a second chamber containing the infusible 

material, where infusion extraction takes place. The piston then 

moves the solvent containing the extract through a filter into the 

first chamber, leaving the extraction residue in the second chamber. 

The method is applicable to operation in low or micro-gravity 

environments. NASA 

h 

N87-17034" National Aeronautics and SDace Administration. 

Pasadena Office, Calif. 

TANK TREAD ASSEMBLIES WITH TRACK-LINKING 

MECHANISM Patent 

EARL R. COLLINS, JR., inventor (to NASA) (Jet Propulsion Lab., 

California Inst. of Tech., Pasadena) 2 Dec. 1986 8 p Filed 

18 Jan. 1985 Supersedes N85-29291 (23 - 18, p 31 17) 

(NASA-CASE-NPO-16321-1 CU; USPATENT-4,626,046; 

USPATENT-APPL-SN-692602; US-PATENTCUSS-305-36; 

US-PATENT-CLASS-305-58PC; US-PATENT-CLASS-305-51 ;

US-PATENT-CLASS-305-58R; US-PATENT-CLASS-474-220) 

Avail: US Patent and Trademark Office CSCL 13F 

The proposed tank tread assembly has adjacent tank tread 

segments joined by a link bearing tapered pins retained by clips 

inserted through the tread shells perpendicular to the axes of the 

pin. It also has highway pads attached by a release rod bearing 

tapered, grooved cams which interlockingly engage tabs inserted 

into the tread shells. 

Official Gazette of the US Patent and Trademark Office 

17 

N87-15465'# 

Lyndon 6. Johnson Space Center, Houston, Tex. 

INFUSION EXTRACTOR Patent Application 

FRANKLIN R. CHANG-DIAZ, inventor (to NASA) 

15 P 

(NASA-CASE-MSC-20761-1; NAS 1.71 :MSC-20761-1; 

US-PATENT-APPL-SN-913446) Avail: NTlS HC AO2/MF A01 

CSCL 131 

This invention relates to an apparatus and method of removing 

desirable constituents from an infusible material by infusion 

National Aeronautics and Space Administration. 

30 Sep. 1986 

20 
N87-17035' 

Lyndon 6. Johnson Space Center, Houston, Tex. 

CLEANING MODULE Patent 

FRED P. ROLLINS, inventor (to NASA) (Lockheed Engineering 

and Management Services Co., Inc., Houston, Tex.) and JAMES 

S. GLASS, inventor (to NASA) 13 Jan. 1987 5 p Filed 3 Oct. 

1985 Supersedes N86-20807 (24 - 11, p 1784) 

National Aeronautics and Space Administration. 

SELF-CONTAINED, SINGLE-USE HOSE AND TUBING 

(NASA-CASE-MSC-20857-1; US-PATENT-4,635,663; 

US-PATENT-APPL-SN-783886; US-PATENT-CLASS-1 34-93; 

US-PATENT-CLASS-1 34-1 66'2; US-PATENT-CLASS-21 0-282) 

Avail: US Patent and Trademark Office CSCL 131 

A self contained, single use hose and tubing cleaning module 

which utilizes available water supplies without requiring access to 

precision cleaning facilities is presented. The module is attached 

to the water source at the inlet side and to the hose or tubing to 

be cleaned at the outlet side. The water flows through a water 

purification zone, a detergent dispensing zone, a filtration zone 

before the detergent laden water flows into the tubing to clean 

the tubing walls. The module contains an embedded pad which is 

impregnated with a pH indicator to indicate to the user when the 

detergent has dissolved and rinsing of the tubing begins. 

Official Gazette of the US Patent and Trademark Office 

N87-17036' 

Lyndon B. Johnson Space Center, Houston, Tex. 

SUN SHIELD Patent 

ARTHUR M. FRANK, inventor (to NASA), SlLVlO F. DERESPINIS, 

inventor (to NASA), and JOHN MOCKOVCIAK, JR., inventor (to 

NASA) 20 Jan. 1987 8 p Filed 12 Aug. 1985 Supersedes 

National Aeronautics and Space Administration. 

N86-20803 (24 - 11, p 1783) 

(NASA-CASE-MSC-20162-1; US-PATENT-4.637,447; 

US-PATENT-APPL-SN-764805; US-PATENT-CLASS-160-265; 

US-PATENT-CLASS-1 60-23R; US-PATENT-CLASS-244-1 21 ; 

US-PATENT-CLASS-244-1 58R; US-PATENT-CLASS-1 35-903; 

US-PATENT-CLASS-296-1 00) 

Office CSCL 131 

A shading device which is capable of compactly storing a flexible 

shade on a biased, window shade type spring roller is disclosed. 

It is controlled to deliver the shade selectively to either its operative 

shading or compact storage orientation. 

Official Gazette of the US Patent and Trademark Office 

Avail: US Patent and Trademark 

37 MECHANICAL ENGINEERING 

N87-17037' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

NON-BACKDRIVEABLE FREE WHEELING COUPLING Patent 

WILLIAM R. LLEWELLIN, inventor (to NASA) (Martin Marietta Corp., 

Bethesda, Md.) 13 Jan. 1987 7 p Filed 22 Apr. 1985 

Supersedes N85-29290 (23 - 18, p 3116) 

US-PATENT-CLASS-1 92-67R) Avail: US Patent and Trademark 

Office CSCL 131 

A rotary coupling for connecting a driven part to a source of 

rotary force is described. This device transmits rotary force in one 

direction only and disengages to permit the driven part to free 

wheel when the input member is stopped and precludes the 

backdriving of rotary force from output member to input member. 

The coupling includes an input member having a splined shaft, a 

coupling member connected to the splined shaft, and a coaxial 

output member. The coupling member and the output member 

having complementary sets of axially facing clutch teeth. Guides 

in the form of helical grooves on the coupling member and spring 

loaded followers acting with the guides affect the engagement 

and disengagement of the clutch teeth by moving the coupling 

member toward and away from output member, the followers and 

guides themselves disengaging to permit free wheeling of output 

member when input member is stopped. 

Official Gazette of the US Patent and Trademark Office 

(NASA-CASE-MSC-20475-1; US-PATENT-4,635,77'3; 

US-PATENT-APPL-SN-725689; US-PATENT-CLASS-1 92-46; 

N87-17038' National Aeronautics and Space Administration. 

Goddard Space Flight Center, Greenbelt, Md. 

RADIAL AND TORSIONALLY CONTROLLED MAGNETIC 

BEARING Patent 

PHILIP A. STUDER, inventor (to NASA) 13 p 

Filed 21 Nov. 1985 Supersedes N86-20804 (24 -1 1, p 1784) 

6 Jan. 1987 

(NASA-CASE-GSC-12957-1; US-PATENT-4,634,191; 

US-PATENT-APPL-SN-800193; US-PATENT-CLASS-31 0-90.5) 

Avail: US Patent and Trademark Office CSCL 131 

A magnetic bearing including a circular stator member with a 

plurality of circumferential pole faces and a suspended annular 

ring member with corresponding number of inward facing 

circumferential pole faces separated by respective air gaps is 

presented. A source of dc magnetic flux circulates flux between 

the circumferential pole faces of the stator and the ring to provide 

axial stability along a central longitudinal axis. Flux coil means are 

included on the stator member to provide variable flux density 

along predetermined radial paths to provide active radial 

stabilization. Flux coil means are included on the stator to actively 

modulate the magnitude of the magnetic forces as well as their 

direction by differential flux control involving the dc magnetic flux 
37 MECHANICAL ENGINEERING 

I 

to produce torquing moments about a pair of mutually orthogonal 

axes which are perpendicular to the central axis. 

Official Gazette of the US Patent and Trademark Office 

N87-18818*# National Aeronautics and Space Administration. 

Lyndon B. Johnson Space Center, Houston, Tex. 

MULTI-PATH PERISTALTIC PUMP Patent Application 

JOSEPH A. CHANDLER, inventor (to NASA) 7 Nov. 1986 15 

I 

N87-18817'# National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

ORBITAL MANEUVERING END EFFECTORS Patent 

Application 

W. NEILL MYERS, inventor (to NASA), JOHN C. FORBES, inventor 

(to NASA), and WAYNE L. BARNES, inventor (to NASA) 16 

Dec. 1986 12p 

(NASA-CASE-MFS-28161-1: NAS 1.71:MFS-28161-1: 

US-PATENT-APPL-SN-942159) 

CSCL 131 

This invention relates to an end effector device for grasping 

and maneuvering objects such as berthing handles of a space 

telescope. The device includes a V-shaped capture window defined 

as inclined surfaces in parallel face plates which converge toward 

a retainer recess in which the handle is retained. A pivotal finger 

(30) meshes with a pair of pivoted fingers which rotate in 

counterrotatiin. The fingers rotate to pull a handle within the 

capture window into recess where latches lock handle in the recess. 

To align the capture window, plates may be cocked plus or minus 

five degrees on base. Drive means is included in the form of a 

motor coupled with a harmonic drive speed reducer, which provides 

for slow movement of the fingers at a high torque so that large 

articles may be handled. Novelty of the invention is believed to 

reside in the combined intermeshing finger structure, drive means 

and the harmonic drive speed reducer, which features provide the 

required maneuverability and strength. NASA 

Avail: NTlS HC A02/MF A01 

P 

(NASA-CASE-MSC-20907-1: NAS 1.71 :MSC-20907-1; 

US-PATENT-APPL-SN-927992) Avail: NTlS HC A02/MF A01 

CSCL 13K 

The instant invention is directed to a peristaltic pump for critical 

laboratory or hospital applications requiring precise flow rates over 

an extended period of time. Within the cylindrical barrel pump 

housing is a single-piece, molded, elastometric, cylindrical liner 

with a multiplicity of flattened helical channels created therein 

from one end of the liner to the other. Three cylindrical rollers 

rotate about the center axis of the pump around the inside surface 

of the liner selectively compressing the liner, and hence the helical 

channels between the rollers and the barrel housing, creating a 

pumping action by forcing trapped fluid in the helical channels 

axially from one end of the liner to the opposite end. The novelty 

of the invention appears to lie in the provision of the special liner 

with multiple helical channels as the pumping chamber, rather 

than the standard single elastomeric tubing which is squeezed 

repeatedly by rollers to move the liquid through a typical peristaltic 

pump. Large, repeated deflections on the standard tubing causes 

a permanent set in the tubing, thus either changing the flow rate, 

or requiring a new section of tubing to be positioned in the pump 

head. Further, this configuration minimizes the amount of outflow 

pulsation which is characteristic of a typical single tubing peristaltic 

pump. NASA 

44 

ENERGY PRODUCTION AND CONVERSION 

Includes specific energy conversion systems, e.g.. fuel cells: global 

sources of energy: geophysical conversion: and windpower. 

N87-17399' National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

HIGH BAND GAP 2-6 AND 3-5 TUNNELING JUNCTIONS FOR 

SILICON YULTIJUNCTION SOLAR CELLS Patent 

TAHER DAUD, inventor (to NASA) (Jet Propulsion Lab., California 

Inst. of Tech., Pasadena) and AKARAM H. KACHARE, inventor 

(to NASA) 23 Dec. 1986 5 p 

Avail: US Patent and Trademark Office CSCL 10A 

A multijunction silicon solar cell of high efficiency is provided 

by providing a tunnel junction between the solar cell junctions to 

connect them in series. The tunnel junction is comprised of p+ 

and n+ layers of high band gap 3-5 or 2-6 semiconductor materials 

that match the lattice structure of silicon, such as GaP (band gap 

2.24 eV) or ZnS (band gap 3.6 eV). Each of which has a perfect 

(NASA-CASE-NPO-16526-1 CU: USPATENT4,631,352; 

US-PATENT-APPL-SN-809975: US-PATENT-CLASS-136-249) 

22 
62 COMPUTER SYSTEMS 

c os, SISI SI 

e 

lattice match with silicon to avoid defects normally associated 

with lattice mismatch. 

Official Gazette of the US Patent and Trademark Office 

GD 111-v or 11-VI 

(Gap or ZnSl 

N87-18921’# National Aeronautics and Space Administration. 

Lyndon B. Johnson Space Center, Houston, Tex. 

SCALLOPED-GEOMETRY SOLAR CONCENTRATOR Patent 

Application 

HOWARD ANDREW WAGNER, inventor (to NASA) 29 Oct. 

1986 27 p 

US-PATENT-APPL-SN-924400) 

CSCL 10A 

An improved solar collector is provided for concentrating solar 

energy at a target aperture of a receiver. The dispersion of reflected 

rays to the target aperture is substantially minimized over prior art 

arrangements. The collector is well suited as a component of a 

solar dynamic power unit for terrestrial use as well as space 

vehicles, concentrating sunlight to drive a heat engine. The solar 

concentrator includes a generally paraboloidal shape which is 

composed of sections or gores of compound curvature, the two 

inner edges of each gore (which abut the corresponding edges of 

adjacent gores) are parabolas. The compound curvature between 

the two edges of each gore being defined, in cross section, by a 

circular arc having its center at the focal point of the paraboloid. 

Novelty is believed to reside in the compound geometry which 

combines the advantages of both parabolas and circular arcs to 

minimize the dispersion of reflected rays from the desired target 

aperture. NASA 

(NASA-CASE-MSC-21061-1; NAS 1.71:MSC-21061-1; 

Avail: NTlS HC A03/MF A01 

60 

COMPUTER OPERATIONS AND HARDWARE 

Includes hardware for computer graphics, firmware, and data 

processing. 

N87-14863’# 

Lyndon B. Johnson Space Center, Houston, Tex. 

Patent Applicatlon 

R. L. SHULER, JR., inventor (to NASA) 

US-PATENT-APPL-SN-878916) 

CSCL 09B 

In a list processing system, small reference counters are 

maintained in conjunction with memory cells for the purpose of 

identifying memory cells that become available for re-use. The 

counters are updated as references to the cells are created and 

destroyed, and when a counter of a cell is decremented to logical 

zero the cell is immediately returned to a list of free cells. In 

those cases where a counter must be incremented beyond the 

maximum value that can be represented in a small counter, the 

cell is restructured so that the additional reference count can be 

represented. The restructuring involves allocating an additional cell, 

distributing counter, tag, and pointer information among the two 

cells, and linking both cells appropriately into the existing list 

structure. NASA 

National Aeronautics and Space Administration. 

REAL-TIME GARBAGE COLLECTION FOR LIST PROCESSING 

26 Jun. 1986 31 p 

Avail: NTlS HC AO3/MF A01 

(NASA-CASE-MSC-20964-1; NAS 1.71 :MSC-20964-1; 

COMPUTER SYSTEMS 

Includes computer networks and special application computer 

systems. 

N87-19021’# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

LOCAL AREA NETWORK WITH FAULT-CHECKING, 

PRIORITIES AND REDUNDANT BACKUP Patent Application 

SERGIO MORALES, inventor (to NASA) (Jet Propulsion Lab., 

California Inst. of Tech., Pasadena) and GARY L. FRIEDMAN, 

inventor (to NASA) 8 Sep. 1986 26 p 

(Contract NAS7-918) 

US-PATENT-APPL-SN-927987) Avail: NTlS HC A03/MF A01 

CSCL 09B 

This invention is a redundant error detecting and correcting 

local area networked computer system having a plurality of nodes 

each including a network connector board within the node for 

connecting to an interfacing transceiver operably attached to a 

network cable. There is a first network cable disposed along a 

path to interconnect the nodes. The first network cable includes 

(NASA-CASE-NPO-16949-1-CU; NAS 1.71 :NPO-16949-1-CU; 

23 
74 OPTICS 

a plurality of first interfacing transceivers attached thereto. A second 

network cable is disposed in parallel with the first cable and, in 

like manner, includes a plurality of second interfacing transceivers 

attached thereto. There are a plurality of three position switches 

each having a signal input, three outputs for individual selective 

connection to the input, and a control input for receiving signals 

designating which of the outputs is to be connected to the signal 

input. Each of the switches includes means for designating a 

response address for responding to addressed signals appearing 

at the control input and each of the switches further has its signal 

input connected to a respective one of the input/output lines from 

the nodes. Also, one of the three outputs is connected to a 

respective one of the plurality of first interfacing transceivers. There 

is master switch control means having an output connected to 

the control inputs of the plurality of three position switches and 

an input for receiving directive signals for outputting addressed 

switch position signals to the three position switches as well as 

monitor and control computer means having a pair of network 

connector boards therein connected to respective ones of one of 

the first interfacing transceivers and one of the second interfacing 

transceivers and an output connected to the input of the master 

switch means for monitoring the status of the networked computer 

system by sending messages to the nodes and receiving and 

verifying messages therefrom and for sending control signals to 

the master switch to cause the master switch to cause respective 

ones of the nodes to use a desired one of the first and second 

cables for transmitting and receiving messages and for 

disconnecting desired ones of the nodes from both cables. 

NASA 

~ - .. I Network Status Monitor 

74 

OPTICS 

Includes light phenomena; and optical devices. 

N87-14971' 

Marshall Space Flight Center, Huntsville, Ala. 

Patent 

R. P. HARRIS, inventor (to NASA), L. R. HOLLAND, inventor (to 

NASA) (Alabama Univ., University.), and R. E. SMITH, inventor (to 

NASA) 30 Sep. 1986 7 p Filed 17 Jan. 1984 Supersedes 

National Aeronautics and Space Administration. 

HIGH-TEMPERATURE, HIGH-PRESSURE OPTICAL CELL 

N84-16986 (22 - 07, p 1075) 

(NASA-CASE-MFS-26000-1; US-PATENT-4,614,428; 

US-PATENT-APPL-SN-571615; US-PATENT-CLASS-356-246; 

US-PATENT-CLASS-372-61) Avail: US Patent and Trademark 

Office CSCL 20F 

The invention is an optical cell for containment of chemicals 

under conditions of high temperature and high pressure. The cell 

is formed of a vitreous silica tube, two optical windows comprising 

a vitreous silica rod inserted into the ends of a tube, and fused 

into position in the tube ends. Windows are spaced apart to form 

a cavity enclosed by the tube and the windows. A hole is drilled 

24 

radially through the tube and into the cavity. Another vitreous 

silica tube is fused to the silica tube around the hole to form the 

stem, which is perpendicular to the long axis of the tube. The 

open end of the stem is used to load chemicals into the cavity. 

Then the stem may be sealed, and if desired, it may be shortened 

in order to reduce the volume of the cavity, which extends into 

the stem. 

Official Gazette of the US Patent and Trademark Office 

10 

I" 

N87-15786*# 

Marshall Space Flight Center, Huntsville, Ala. 

TORCH Patent Application 

STEPHEN S. GORDON, inventor (to NASA) (Rockwell International 

Corp., Canoga Park, Calif.) 30 Sep. 1986 11 p 

(Contract NAS8-27980) 

USPATENT-APPL-SN-913447) Avail: NTIS HC AO2/MF A01 

CSCL 20F 

The invention is directed to a coaxial extending metal mirror 

reflector attached to the electrode housing or gas cup on a welding 

torch. An electric welding torch with an internal viewing system 

for robotic welding is provided with an annular arc light reflector 

to reflect light from the arc back onto the workpiece. The reflector 

has a vertical split or gap in its surrounding wall to permit the 

adjacent wall ends forming the split to be sprung open slightly to 

permit the reflector to be removed or slipped onto the torch housing 

or gas cup. The split or gap also permits the feed of weld wire 

therethrough to the weld area. The reflected light provides an 

even light distribution onto the darker surrounding areas. Novelty 

lies in the use of a split annular arc light reflector on the end of a 

welding torch having an internal viewing system. NASA 

National Aeronautics and Space Administration. 

SELF-CLAMPING ARC LIGHT REFLECTOR FOR WELDING 

(NASA-CASE-MFS-29207-1; NAS 1.71 :MFS-29207-1; 
76 SOLID-STATE PHYSICS 

N87-17493' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

WELDING TORCH WITH ARC LIGHT REFLECTOR Patent 

STEPHEN S. GORDON, inventor (to NASA) (Rockwell International 

Corp.. Canoga Park, Calif.) 30 Dec. 1986 5 p Filed 3 Oct. 

1985 Supersedes N86-20130 (24 - 10, p 1670) 

(NASA-CASE-MFS-29134-1; US-PATENT-4,633,060; 

US-PATENT-APPL-SN-783890; US-PATENT-CLASS-219-1 30.01 ; 

US-PATENT-CLASS-21 9-1 24.34) Avail: US Patent and 

Trademark Office CSCL 20F 

A welding torch arc light reflector is disclosed for welding 

torches having optical viewing systems. A schematic of a welding 

torch having an internal coaxial viewing system consisting of a 

lens which focuses the field of view of the weld scene of the 

workpiece onto the end of the fiberoptic bundle is provided. The 

transmitted image of the fiberoptic bundle is provided to a camera 

lens which focuses it onto a TV sensor array for transmission. To 

improve the parity of the image of the monitoring system, an arc 

light reflector is shown fitted to the end of the torch housing or 

gas cup. The arc light reflector has an internal conical section 

portion which is polished to serve as a mirror which reflects the 

bright arc light back onto the darker areas of the weld area and 

thereby provides a more detailed image for the monitoring system. 

The novelty of the invention lies in the use of an arc light reflector 

on welding torches having optical viewing systems. 

Official Gazette of the US Patent and Trademark Office 

N87-19064'# 

Pasadena Office, Calif. 

PROCESSOR Patent Application 

HUA-KUANG LIU. inventor (to NASA) 7 Nov. 1986 12 p 

(Contract NAS7-918) 

NAS 1.71:NPO-16750-1-CU) Avail: NTlS HC A02/MF A01 

CSCL 20F 

An optical processor is provided which facilitates selection of 

any of a variety of patterns or images which are to be compared 

with a Fourier transform of a template image, wherein the processor 

can be constructed at low cost. One of the two images that are 

to be compared is formed by generating video signals representing 

National Aeronautics and Space Administration. 

REMOTELY CONTROLLABLE REAL-TIME OPTICAL 

(NASA-CASE-NPO-16750-1-CU; US-PATENT-APPL-SN-927972; 

the image and using those signals to drive a liquid crystal array 

through which light passes. NASA 

I1 

76 

SOLID-STATE PHYSICS 

Includes superconductivity 

N87-13313' 

Pasadena Office, Calif. 

FET CHARGE SENSOR AND VOLTAGE PROBE Patent 

P. A. ROBINSON, JR., inventor (to NASA) 

National Aeronautics and Space Administration. 

12 Aug. 1986 7 p 

(NASA-CASE-NPO-16045-1: US-PATENT-4,605.946; 

US-PATENT-APPL-SN-641146; US-PATENT-CLASS-357-23.1 ;

US-PATENT-CLASS-357-23.1 2; US-PATENT-CLASS-357-29; 

US-PATENT-CLASS-357-52; US-PATENT-CLASS-357-30 

US-PATENT-CLASS-250-338; US-PATENT-CLASS-250-370) 

Avail: US Patent and Trademark Office 

A MOSFET structure having a biased gate covered with an 

insulator is described. The insulator is of such a thickness as to 

render the structure capable of giving a measure of accumulated 

charge. The structure is also capable of being used in a stacked 

structure as a particle spectrometer. E.R. 

CSCL 20L 

25 
76 SOLID-STATE PHYSICS 

N87-15004'# National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

LIQUID ENCAPSULATED FLOAT ZONE PROCESS AND 

APPARATUS Patent Application 

R. J. NAUMANN, D. 0. FRAZIER. S. L. LEHOCZKY, M. VLASSE, 

and B. R. FACEMIRE. inventors (to NASA) 15 p 

US-PATENT-APPL-SN-924399) Avail: NTlS HC AO2/MF A01 

CSCL 460 

Process and apparatus for growing crystals using float zone 

techniques are described. A rod of crystalline materials is disposed 

in a cylindrical container, with a space being left between the rod 

and container walls. The space is filled with an encapsulant, 

selected to have a slightly lower melting point than the crystalline 

material. The rod is secured to a container end cap at one end 

and to a shaft at its other end. A piston slides over the rod and 

provides pressure to prevent loss of volatile components upon 

melting of the rod. Prior to melting the rod the container is first 

heated to melt the encapsulant, with any off-gas from this step 

being vented to a cavity behind the piston. The piston moves 

slightly forward owing to volume change upon melting of the 

encapsulant, and the vent pasageway is closed. The container is 

then moved longitudinally through a heated zone to progressively 

melt sections of the rod as in conventional float zone processes. 

The float zone technique may be used in the microgravity 

environment of space. NASA 

29 Oct. 1986 

(NASA-CASE-MFS-28144-1; NAS 1.71 MFS-28144-1; 

N87-15882' National Aeronautics and Space Administration. 

Pasadena Office, Cali. 

METHOD FOR GROWING LOW DEFECT, HIGH PURITY 

CRYSTALLINE LAYERS UTILIZING LATERAL OVERGROWTH 

OF A PATTERNED MASK Patent 

ANDREW D. MORRISON, inventor (to NASA) (Jet Propulsion Lab., 

California Inst. of Tech., Pasadena.) and TAHER DAUD, inventor 

(to NASA) 16 Sep. 1986 6 p Filed 28 Feb. 1985 Supersedes 

N85-30933 (23 - 19, p 3374) USPatent-Appl-SN-507624, filed 

24 Jun. 1983 Sponsored by NASA 

(NASA-CASE-NPO-15813-2 USPATENT-4,612,072; 

US-PATENT-APPL-SN-706564; US-PATENT-CLASS-1 48-1 75; 

US-PATENT-CLASS-29-576-E USPATENT-CLASS-29-576-J; 

US-PATENT-CLASS-29-576-W, US-PATENT-CLASS-29-575; 

US-PATENT-CLASS-29-578; US-PATENT-CLASS-1 48-1 74) 

Avail US Patent and Trademark Office CSCL 208 

A method for growing a high purity, low defect layer of 

semiconductor is described. This method involves depositing a 

patterned mask of a material impervious to impurities of the 

semiconductor on a surface of a blank. When a layer of 

semiconductor is grown on the mask, the semiconductor will first 

grow from the surface portions exposed by the openings in the 

mask and will bridge the connecting portions of the mask to form 

a continuous layer having improved purity, since only the portions 

overlying the openings are exposed to defects and impurities. The 

process can be iterated and the mask translated to further improve 

the quality of grown layers. 

Official Gazette of the US Patent and Trademark Office 

N87-15883'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

TAILORABLE INFRARED SENSING DEVICE WITH STRAIN 

LAYER SUPERLATTICE STRUCTURE Patent Application 

LIJEN CHENG. inventor (to NASA) 28 Aug. 1986 19 p 

(Contract NAS7-918) 

(NASA-CASE-NPO-16607-1CU; NAS 1.71 :NPO-16607-1; 

US-PATENT-APPL-SN-901114) Avail: NTIS HC AO2/MF A01 

CSCL 20L 

An infrared photodetector is formed of a heavily doped p-type 

Ge sub x Si sub 1-x/Si superlattice in which x is preestablished 

during manufacture in the range 0 to 100 percent. A custom tailored 

photodetector that can differentiate among close wavelengths in 

the range of 2.7 to 50 microns is fabricated by appropiate selection 

of the alloy constituency value, x, to establish a specific wavelength 

at which photodetection cut-off will occur. NASA 

N87-19115*# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

PROCEDURE TO PREPARE TRANSPARENT SILICA GELS 

Patent Appllcatlon 

PATRICK G. BARBER, inventor (to NASA) (Longwood Coll., 

Farmville, Va.) and NORMAN R. SIMPSON, inventor (to NASA) 

24 Nov. 1986 11 p 

US-PATENT-APPL-SN-933961) Avail: NTIS HC AO2/MF A01 

CSCL 206 

This invention relates to the production of silica gels and in 

particular to a process for the preparation of silica gels which can 

be used as a crystal growth medium that simulates the 

convectionless environment of space to produce structurally perfect 

(NASA-CASE-LAR-13476-1 -CU; NAS 1.71 :LAR-13476-1 -CU 

26 
76 SOLID-STATE PHYSICS 

I 

crystals. Modern utilizations of substances in electronics, such as 

radio transmitters and high frequency microphones, often require 

single crystals with controlled purity and structural perfection. The 

near convectionless environment of silica gel suppresses 

nucleation, thereby reducing the competitive nature of crystal 

growth, and provides a medium for growing single crystals with 

structural perfection and controlled purity. Previous methods of 

producing silica gels result in cloudy, translucent gels, while it is 

much more desirable to produce transparent gels so that the 

crystals can be more easily observed. In the current process, 

sodium ions in a sodium silicate solution are replaced with 

potassium ions from a soluble potassium salt solution by using 

cation exchange resin beads. The resulting treated silicate solution 

is then added to a volume of boiled, cooled distilled water, after 

which a volume of acetic acid solution is added to the mixture of 

distilled water and treated silicate solution. This mixture is then 

allowed to gel at room temperature, whereby a transparent silica 

gel is produced. NASA 

N87-19116’# National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

METHOD AND APPARATUS FOR GROWING CRYSTALS Patent 

Application 

ROBERT J. NAUMANN, inventor (to NASA), SANDOR L. 

LEHOCZKY. inventor (to NASA), and DONALD 0. FRAZIER, 

inventor (to NASA) 31 Oct. 1986 20 p 

(NASA-CASE-MFS-28137-1; NAS 1.71 :MFS-28137-1; 

US-PATENT-APPL-SN-925189) 

CSCL 208 

This invention relates to a method and apparatus for bulk growth 

of defect-free compound crystals. Crystal growth is carried out in 

the present invention in an apparatus having an enclosure with a 

spherical interior which is provided with an adjustable heat source. 

A seed crystal is positioned within this interior and is connected 

to one end of a rod of heat conductive material which extends 

through the enclosure. The rod is independently heated, and a 

heat absorber is connected to an opposite end of the rod. 

Crystalline material is placed in the interior of the sphere and in 

engagement with the seed crystal, and pressure is applied to it. 

Encapsulant material having a slightly lower melting point than 

the crystalline material is disposed between the latter and the 

spherical container wall. A crystal structure is grown by heating 

the crystalline material up to a predetermined temperature while 

controlling heat dissipation through the rod by the application of 

heat to the rod. Heat application is reduced, allowing heat to 

escape via the seed crystal and the rod of material, causing the 

crystalline material to be deposited as a single crystal on the 

seed crystal. Novelty of the invention is believed to reside in the 

use of a spherical container with a heat removal rod at one pole 

of the sphere, the rod providing for control of the shape of the 

crystal-liquid interface during solidification. These features enable 

growth of relatively large, defect-free crystals of compound 

materials. NASA 

Avail: NTlS HC AO2/MF A01 

UWXI 

27 
PUBLIC AVAILABILITY OF COPIES OF PATENTS 

AND PATENT APPLICATIONS I 

Copies of US. patents may be purchased directly from the US. Patent and Trademark Office, Washington, D.C. 

20231 at $1.50 per copy. When ordering patents, the U.S. Patent Number should be used, and payment must be 

remitted in advance, preferably by money order or check payable to the Commissioner of Patents and Trademarks. 

Prepaid purchase coupons for ordering are also available from the Patent, and Trademark Off ice. 

NASA patent application specifications are sold in paper copy by the National Technical Information Service at 

price code A02. Microfiche are sold at price code A01. The US-Patent-Appl-SN-number should be used in ordering 

either paper copy or microfiche from NTIS. 

LICENSES FOR COMMERCIAL USE: 

INQUIRIES AND APPLICATIONS FOR LICENSE 

NASA inventions, abstracted in NASA PAB, are available for nonexclusive or exclusive licensing in accordance 

with the NASA Patent Licensing Regulations. It is significant that all licenses for NASA inventions shall be by 

express written instruments and that no license will be granted or implied in a NASA invention except as provided 

in the NASA Patent Licensing Regulations. 

Inquiries concerning the NASA Patent Licensing Program or the availablity of licenses for the commercial use of 

NASA-owned inventions covered by U.S. patents or pending applications for patent should be forwarded to the 

NASA Patent Counsel of the NASA installation having cognizance of the specific invention, or the Associate General 

Counsel for Intellectual Property, code GP, National Aeronautics and Space Administration, Washington, D.C. 

20546. Inquiries should refer to the NASA Case Number, the Title of the Invention, and the U.S. Patent Number 

or the U.S. Application Serial Number assigned to the invention as shown in NASA PAB. 

The NASA Patent Counsel having cognizance of the invention is determined by the first three letters or prefix of 

the NASA Case Number assigned to the invention. The addresses of NASA Patent Counsels are listed alongside 

the NASA Case Number prefix letters in the following table. 

STANDING ORDER SUBSCRIPTIONS 

NASA SP-7039, Section 1 and its supplements are available from the National Technical Information Service (NTIS) 

on standing order subscription as PB 86-911100 at the price of $11.50 domestic and $23.00 foreign. Standing order 

subscriptions do not terminate at the end of a year, as do regular subscriptions, but continue indefinitely unless 

specifically terminated by the subcriber. 
NASA Case 

Numbr 

Prefix Letters 

ARC-XXXXX 

XAR-XXXXX 

ERC-xxxxx 

XER-xxxxx 

HQN-XXXXX 

XHQ-xxxxx 

GSC-xxxxx 

XGS-xxxxx 

KSC-xxxxx 

XKS-xxxxx 

LAR-xxxxx 

XLA-xxxxx 

LEW-xxxxx 

XLE-xxxxx 

MSC-xxxxx 

XMS-xxxxx 

MFS-xxxxx 

XMF-xxxxx 

NPO-xxxxx 

XNP-xxxxx 

FRC-xxxxx 

XFR-xxxxx 

woo-xxxxx 

Address of Cognizant 

NASA Patent Counsel 

Ames Research Center 

Mail Code: 200-11A 

Moffett Field, California 94035 

Telephone: (415) 694-5104 

NASA Headquarters 

Mail Code: GP 

Washington, D.C. 20546 

Telephone: (202) 453-241 7 

Goddard Space Flight Center 

Mail Code: 204 

Greenbelt, Maryland 20771 

Telephone: (301) 286-7351 

John F. Kennedy Space Center 

Mail Code: PT-PAT 

Kennedy Space Center, Florida 32899 

Telephone: (305) 867-2544 

Langley Research Center 

Mail Code: 279 

Hampton, Virginia 23365 

Telephone: (804) 865-3725 

Lewis Research Center 

Mail Code: 500-318 

21 000 Brookpark Road 

Cleveland, Ohio 44135 

Telephone: (216) 433-5753 

Lyndon B. Johnson Space Center 

Mail Code: AL3 

Houston, Texas 77058 

Telephone: (713) 483-4871 

George C. Marshall Space Flight Center 

Mail Code: CCOl 

Huntsville, Alabama 3581 2 

Telephone: (205) 544-0024 

NASA Resident Legal Office 

Mail Code: 180-801 

4800 Oak Grove Drive 

Pasadena, California 91103 

Telephone: (81 8)354-2700 
PATENT LICENSING REGULATIONS 

NATIONAL AERONAUTICS AND 

SPACE ADMINISTRATION 

14 CFR Part 1245 

Lkensing of NASA Inventions 

AOEYCV: National Aerunautics and 

Space Administration. 

ACTION: Interim regulation with 

comments requested. 

1245 210 

1245 211 Apprels. 

1215 212 

invenliuns 

1:4'* 113 Trdiisfer of custody 

1245 214 Confidentinlily or information 

Sl.it 3023 and 3024 

Modificvtion and termination of 

1iLenst.s 

Protection and cidminislration uf 

Authonty 35 U S C Section 207 and uM.84 

..... 

SUYYARV: Thv National Aeronautics 

and Space Administration (NASA] is 

rwising its patent licensing regulations 

to conform with Pub L. 96-517. This 

interim regulation provides policies and 

prorFdurcs applicable to the licensing of 

feder.iIly owned inventions in the 

custody of the National Aeronautics and 

Spa1 C' Administration. and implements 

Puh L. 9t -517. The object of this subpart IS to use the patent system to promote 

the utilization of inventions arising from 

NASA supported research end 

development. 

LfFLCtlVI DATE: july 1.19n1. Coniments 

must be received in writing by 

December 2.1981. Unless a notice ir 

published in the F&rd Register after 

tile-conimeiit period indicating changes 

to be made, this interim rcgulation shall 

brcome n final regulation. 

ADDRESS: Mr. John G. hfannix. Director 

of Patent Lirensing. GP-4, NASA, 

Washington, D.C. XFW. 

FOR mmtn IWCO(W~TIOU COUTAC~: 

Mr john C Monnix, (202) 755-3954. 

SUPPUMENTARV IW0RYATK)W: 

PART 124S-PAl"S AND OTHER 

INTELLECTUAL PROPERTY RIGHTS 

Subport 2 of Part 1245 is revised to 

read as follows 

:.a*. 

--dknncbn 

set 

1245 .!W Scope of subpart 

1245 W1 Po!icy end oblecti\ e 

1245 202 Definiiions 

1245 2u3 Authority to grnnl liwnses 

Rcsrnctlons md Colditions 

1245 UU All lirrnses granted irnder thir 

siihparl 

Types uf Licenses 

1245 205 Nonexclusive licenses. 

1245 Zfk Exclusive and pdrtidlly exclusive 

Procedures 

1245 207 Application lor d license 

1215 20 Procresing applicalionr 

1245 ?09 Nc)c~x to Attorney Cencrd 

III eiibrs 

Subpart 2-Lkenslng of NASA 

Inventlons 

$1245.100 Scope of subpart. 

rhis siibpmt prescribes the terms. 

conditions. and procedures upon which 

NASA invention may be licensed. It 

does not affect licenses which (a) were in effect prior to july 1. 1981; (b) may 

e~ist at Ihe time of the Government's 

acqirisition of title to the invention. 

induding those resulting from the 

alloc.ation of rights to inventions made 

under Government resrarch and 

dcvelopment contracts. (c] are the result 

of an authorized exchange of rights in 

the settlement of patent disputer: or (d) are otherwise authorized by law or treaty. 

0 1245.101 Pole acid ob-. 

It is the policy and objective of this 

subpiirt to use the patent system to 

promote the utilization of inventions 

arising from NASA supported research 

and development. 

g1r46.202 o.(mbn. 

(a) "Federally owned invention" means an invention, plant, QT deswhich is cover6d by patent. or patent 

application in the United Stnter. or I 

patent. patent application. plant variety 

protection. or other form of protertion 

in a foreign country. title to which has 

been assigned to or otherwise vested cn 

the United States Government. 

exccutive department. military 

department, Government corporation, or independent establishment, except the 

Tennessee Valley Authority. which has 

custody of a Federally owned invention. 

Federally owned invention with respect 

to which NASA maintains custody and 

administration. in whole or in part. of 

the right. title or interest in such 

invention on behalf of the United States 

Government. 

(d] "Smell business firm" means a srnall business concern as defined at 

wction 2 of Pub. L 85-536 (15 U S.C. 6321 

and implementinR,reg,ilations of the 

Administrator of the Small Business 

Admlnrstration. For the purpose of these 

regulations. the sire rtandard for smell 

biisiness concerns involved in 

Gokrrnment procurement. contained in 

(b) "Federal qncy" means nn 

(c.) "NASA Invention" means a 

1J (.t R 121 3-8. and in subcontracting. 

conta.ired iii 13 CFR 121.3-12. will be 

used 

[P) I'ractical application" means to 

nianufecture in the caae of a 

rnrnposition or product. to practice in 

thr CdSe of a process or method. or to 

operate in the case ol a machme or 

system; and. in each case. under such 

conditions as to establish bat the 

invention is being utilized and that its 

benefits ere to the extent permitted by 

law or Government regulntians 

available to the public on rearonable 

terms. 

States of America. ita territories and 

possessions, the District of Columbia, 

and the Commonwealth of Puerto Riw. 

12C5.203 Authority to grsnl Wnses 

NASA inventions sholi be made 

available for Iicendng 8s deemed 

approprinte in the public intamt. NASA 

may grant nonexclusive. partially 

exclusive. or exclusive licenses thereto 

under this rubpart on inventions in its 

custody. 

Restrictions and Conditions 

(124uoo AMkcclwyrNUedundcfW. 

w)puL 

(a] Restrictiom. (1) A licen~ my be 

granted only if the applicant has 

supplied NASA witb a satisfactory plan 

for development or marketing of th 

invention, or both, and with informatlon 

about the applicant's capability to fulfill 

the plan. 

(2) A hw granting wts to nw or 

sell under a NASA invention in the 

United States shall normally be granted 

only to I licensee who agrees that any 

products embodying the invention or 

produced thmgh the use of the 

invention will be manufactured 

substantidy in the United Stater. 

(b) WItionr. Licenses shall main 

~uch terms and wnditionr as NASA 

determines are appmpriatc'for the 

protection of he interests of the Foddenl 

Gwarnment and the public and are not 

in cmflict witb law or this rubport. The 

followiq terns and conditions apply to 

any license: 

for a period specified in the license 

ajjreement. unless sooner terminated in 

accordance with this subpart. 

(2) The license may be granted for all or less than all fields of use of the 

invention or in specified geographical areas. or both. 

subsidiaries of the licensee or other 

parties if provided for in the license but 

shall be nonassignable without approval 

of NASA. except to the successor of that 

part of tbe licensee's business to which 

the invention pertains. 

(fj "United Stabs" means the United 

(1) The duration of the licensc shall be 

(3) The license may extend to 
PATENT LICENSING REGULATIONS 

(41 The license may provide the 

licensee the right to grant sublicenses 

under the Iiccmse!subject to the 

dpproval of NASA. Ench sublicense 

shall make reference to the license. 

including the rights retained by the 

Government. and a copy of such 

sublicense shall be furnished to NASA. 

(5) The license shall require the 

licensee to carry out the plan for 

development or marketing of the 

invention, or both, to bring the invention 

to practical application within a period 

specified in the license, and to continue 

to make the benefits of the invention 

reasonably accessible to the public. 

(6) The license shall require the 

licensee to report periodicaIly on the 

utilization or efforts at obtaining 

utilization that are being made by the 

licensee, with particular reference to the 

plan submitted. 

(7) All licenses shall normally require 

royaltier or other conrideration. 

(8) Where en agreement is obtained 

pursuant to 1245.2W(a)(2) that any 

products embodying the inventia or 

produced through use of the invention 

will be manufactured substantially in 

the United States. the license shall recite 

such agreement. 

(9) The license shall provide for the 

right of NASA to terminate the license, 

in whole or in part, if: 

[i) NASA determiner that the licensee 

is not executirq the plan submitted with 

its requeet for a licmre and the licensee 

cannot otherwise demonstrate to the 

satisfaction of NASA that it has taken or can be expected to take within a 

reasonable time dlective steps to 

achieve practical application of the 

invention: 

is necessary to meet requirements for 

public use specified by Federal 

regulations issued after the date of the 

license and such requirements are not 

reasonably satisfied by the licensee: 

(iii) The licensee has willfully made a 

false statement of or willfully omitted a material fact in the license npplication 

or in any report required by the license 

agreement: or 

substantial breach of covenant or 

agreement contained in the license. 

(10) The license may be modified or 

terminated. consistent with this subpart, 

upon mutual agreement of NASA and 

the licensee. 

license, nor the grant itself, shall be 

construed to confer upon any person 

any immunity from or defenses under 

the antitrust laws or from a charge of 

(ii) NASA determines that such action 

(iv) The licensee commits a 

(11) Nothing relating to the grant of a 

patent misuse, and the acquisition and use of rights pursuant to this subpart 

shall not be immunized from the 

operation of state or Federal law by 

reason of the source of the grant. 

Types of Licenses 

0 1245.205 Nonrxclur)vo hn8or. 

[a) A vuilabilify of licenses. 

Nonexclusive licenses may be granted 

under NASA inventions withou! 

publication of availability or notice of a 

prospective license. 

(b) Conditions. In addition to the 

provisions of 4 1245.204, the 

nonexclusive license may also provide 

that. after termination of a period 

specified in the license agreement, 

NASA may restrict the license to the 

fields of use or geographic areas, or 

both. in which the licensee has brought 

the invention to practical application 

and continues to make the benefits of 

the invention reaaonably accessible to 

the public. However, such restriction 

shall be made only in order to grant an exclusive or partially exclusive license 

in accordance with this subpart. 

9 1245.206 Exclurlvo and prtklly 

exclurlvo Ucmror. 

[a) Domestic licenses. 

(1) Avuilubility oflicenscs. Exclusive or partially exclusive licenses may be 

granted on NASA inventions: (i) 3 

months after notice of the invention's 

availability has been announced in the 

Federal RegisIer; or (ii) without such 

notice where NASA determines that 

expeditious granting of such a license 

will best serve the interests of the 

Frderal Government and the public; and 

(iii) in either situation, specified in 

(R)(l)(i) or (ii) of this section only if 

(A) Notice of a prospective license. 

itlentifying the invention and the 

prospective licensee. has been published 

in the Federal Register. providing 

opportunity for filing written objections 

within a 60-day period; 

(E) After expiration of the period in 

5 1245.206(a) (I)(iii)[A) and 

consideration of nay written objections 

received during the perlod. NASA has 

determined that: 

Gtivernment and the publicwill best be 

srrbed by the proposed license. in view 

of the applicant's intentions, plans, and 

ttbility to bring the invention to practical 

application or otherwise promote the 

invention's utilization by the public; 

(4 The desired practial application 

h<is not been achieved, or is not likely 

expeditiously to be achieved? under any 

nonexclusive license which has been 

granted, or which may be granted, on the invention; 

(I) The interests of the Federal 

(3) Exclusive or partially exclusive 

licensing is a reasonable and necessary 

incentive to call forth the investment of 

risk capital and expenditures to bring 

the invention to practical application or 

otherwise promote the invention'r 

utilization by the public: and 

(I) The proposed terms and scope of 

exclusivity are not greater than 

reasonably necessary to provide the 

incentive for bringing the invention to 

practical application or otherwise 

promote the invention's utilization by 

the public: 

grant of such license will tend 

substantially to lessen competition or 

result in undue concentration in any 

section of the country in any line of commerce to which the technology to be 

licensed relates, or to create or maintain 

other situations inconsistent with :he 

antitrust laws; and 

(D) NASA has given first preference 

to any small business firms submitting 

plans that are determined by the agency 

to be within the capabilities of the firms 

and as equally likely, if executed, to 

bring the invention to practical 

application as any plane submitted by 

applicants that are not small business 

firms. 

(2) Conditions. In addition to the 

provisions of 1245.204, the following 

terms and condition8 apply to domestic 

exclusive and partially exclusive 

licenses: 

irrevocable. royalty-free right of the 

Government of the United States to 

practice and have practiced the 

invention on behalf of the United States 

and on behalf of any foreign government or international organization pursuant to 

any existing or future treaty or agreement with the United States. 

(ii) The license shall reserve to NASA 

the right to require the licensee to grant 

sublicenses to respoiislble applicants. on reasonable terms, when necessary to 

fulfill health or safety needs. 

(iii) The license chall be subject to any 

licenses in force at the time of the grant 

of the exclusive or partially exclusive 

lirense. 

the right of enforcement of the licensed 

patent pursuant to the provisions of 

Chapter 29 of Title 35. United States 

Code. or other statutes, as determined 

appropriate in the public interest. 

(C) NASA has not determined that the 

(i) The license shall be subject to the 

(iv) The license may grant the licensee 

(b) Foreign licenses. 

(1) Avoilubility of licenses. Exclusive or partially exclusive licenses may be 

granted on a NASA invention covered 

by a foreign patent, patent application, 

or other form of protection. provided 

that: 

[i) Notice of a prospective license, 
PATENT LICENSING REGULATIONS 

identifying the invention and 

prpspective licensee, has been published 

in the Federal Register. providing 

opportunity for filing written objections 

within a 60-day period and following 

consideration of such objections: 

interests of the Federal Government or United States industry in foreign 

commerce will be enhanced: and 

(iii) NASA has not determined that 

the grant of such license will tend 

substantially to lessen competition or 

result in undue concentration in any 

section of the United States in any line 

of commerce to which the technology to 

be licensed relates. or to creete or maintain other situationr inconsirtent 

with antitrust laws. 

(2) Conditions. In addition to the 

provisions of I 1245.201. the following 

terms and conditions apply to foreign 

exclusive and partially exclusive 

licenses: 

Irrevocable, royalty-free right of the 

Government of the United States to 

practice and have practiced the 

Invention on behalf of the United States 

and on behalf of any foreign government or international organization pursuant to 

any existing or future treaty or 

agreemmt with the United Stater. 

(ii) The license shall be subject to any 

licenses in force at the time of the grant 

of the exclusive or partially exclusive 

I' icense. 

(iii) The license may grant the licensee 

the r@t to take any suitable and 

necessary actionr to protect the licensed 

property. on behalf of the Federal 

Government. 

(c) Recod ofdetermino/ions. NASA 

shnll maintain a record of 

determinations to grant exclusive or 

partially exclusive licenses. 

pmduraa 

I 1245307 rrgprc.ckn (or a Rwnn. 

An application for a license should bo 

addressed to the Patent Counsel at tho 

NASA inrtallation having responsibilit y 

for the invention and shall normally 

Include: 

(0) Identification of the invention for 

which the license is desired. including 

the patent application serial number or 

patent number, title. and date, if known; 

(b) Identification of the type of iicense 

for which the application is rubmitted, 

(c) Name and address of the person, 

company, or organization applying for 

the license and the citizenship or place 

of incorporation of the applicant; 

(Jl Name. address. and telephone 

number of representative of applicant to 

whom correspondence should be rent 

le) Nature and type of applicant's 

(ii) NASA has considered whether the 

(i) The license shall be iubject to tbe 

business, idennfying products or services which the applicant has 

successfully commei cialixed. and 

approximate numbor of appliunt'r em loyoor; (6 SO- of information mncemiq 

the avdlabllity of a Iiconw on tho 

invontion: 

[a) A rtatement Indicating whether 

applicant Ia a d burhss Ann as 

defined In I 1U5.202(c); 

(h) A detailed description of 

appliunt'r plan for dovolopment or 

marketing of the inventioa or both, 

which should includo: 

amount of anticipated Investment of 

capital md other resource# which 

applicant believer HLU be required to 

bring tho invention to practical 

application: 

(2) A statement as to applicant's 

capability and intention to fulfill the 

plan. includiry tnformation rsaordlry 

manufacturing doting, Bnurcial and 

technical re roue^.^; 

(3) A rUtomont of th frob of UIC for 

which appllunt Intends to practice the 

inwntiom d 

areal In which applicant Lot.nb to 

manufactum any products mbdylq 

the hvmtlon d geopphlc areas 

where appllcmt Int.nb to UL. or sell 

the Inva~Hon, ar both; 

granted to appllcrnt undu Fedody 

owned Inventions; 

best Imowl.cb. of th oxbnt b WM 

the invrntion is being practiced by 

privato indutry or COvetnIWnL or both 

or is othorwh av.il.blo coaunercidl~ 

and 

(k) Any other LafOrmrtioa which 

determination to grant the o&"" came to 

applicant believes will su 

I*- -sin@- 

(a) Applications for Ucerws will k 

initially reviewod by tho Patoat Counwl 

of the NASA installation &v&u 

rerponribility for the invmtloa Th. 

Patent Counsel shall mako a prelhhry 

recommendation to tb. Mnctor of 

Licensing, NASA Headquarters, whether 

to: (1) grant the license as requested (2) 

grant the license with modification after 

negottation with the licensee, or (3) deny 

the license. The Mnctor of kens@ 

shall review the preliminary 

recommendation of the Patent Counsel 

and make a find recommendation to the 

NASA Asristmt General Counsel for 

Patent Matters. Such miew and fhl 

recommendation may indude, and be 

bored on. any additional information 

obtained from applicant ad other sources that the Patent Cowel and the 

(1) A stabment of tho tlmo. ~hve and 

(4) A rtrbwnt of th. -8phlC 

(i) Identification of licaues prrvloorly 

(j) A statement contalaing applicant's 

appiicrnt 

Director of Licensing doom relevant to 

the licenso mquertd The determination 

to grant or dmy tho lianu shall be 

made by the Auirtmt General Counsel 

for Patent Mattorr bared on the final 

recommendation of tho Director of 

Licensing. 

(b) When notice of a prospective 

exclusivo or partially .Ichuivo Uconsr 

ir published in tho Federal -star In 

accordance with I lM&2o6(a)(l)(UiNA) 

or I lUaWS(bM1Mi). any writton 

objections recriwd m raponso thomto 

will bo considod by tho Director of 

Licensin~ in makh tho AMI 

recommendation to the Awirtant 

General Counsel for Patent Matters. 

(c) If tho requested liceme. including 

any nepttated modiliutionr, is dmiod 

by the Assistant General Counsel for 

Patent Matters. the applicant may 

requert mcouddration by riliq a 

written request for reconsideration 

within 36 days after mceiviry notice of 

denial. This m-day period may be 

extended for good cause. 

(d) In addition to. a in lieu of 

request- rrcoorideration, the 

applicant may .Lo appeal the denid of 

the liceme in accotbltcc with 

t lus.2ll. 

I 1248.208 Netice b A(bml Qmnl. 

A copy oflbr notic8 provided for in 

I I 1245.206(aNl)(iii)(A). md 

1US.zoS(b#l)(i) will be aent to the 

Attorney General. 

I 12uIlO Mod- and WnWWtbn d 

ltcemr 

liccnw. 0tb.r th.n by mutud agreement, 

NASA shall furnlah tho lice- and my 

rubliceowe of record a written notice of 

intention to madIfy or terminate the 

license. d the licensee and any 

rubllwnum hll be allowed 36 days 

after such notice to remedy any breach 

of the licenm or ohow cause why the 

license should not be modified or 

termilubd 

Befm dlfylng or terminating a 

Ilirull 

(a) fb. followlry putler my appeal 

to the NASA Adminirtrator or designee 

any decision or determination 

concernhg the grant. denial, 

interpretation, modification. or termination of a licenw: 

It) A pmar whow appbuh~ for a 

license has been denied. 

(2) A licensee whom llcsrW har been 

modified or terminated, Ln whole or in 

part; or 

(3) A person who timely filed a 

written objection in response to the 

notice required by 

lus2aI(aMl)(iii)(A) or 
PATENT LICENSING REGULATIONS 

1245.2oe(b)(l)(i) and who can demonstrate to the satisfaction of NASA 

that such person may% damaged by 

the Agency action. 

(b] Written notics of appeal must be 

filed within 30 days (or such other time 

as may be authorlted for god cause 

shown) after receiving notice of the 

adverse dedsion or determination; 

including. an adverse dedsion following 

the request for reconsideration under 

4 1=5.20B(c). The notice of appeal, 

along with all supporting documentation 

should be addressed to the 

Administrator, National Aeronautics 

and Space Administration. Washington. 

DC 20546. Should the appeal raise a 

genuine dispute over material facts. factfinding will be conducted by the NASA 

Inventions and Contributions Board. The 

person filing the appeal shall be 

afforded an opportunlty to be heard and 

to offer evidence in support of the 

appeal. The Chairperson of the 

Inventions and Contributions Board 

shall prepare written findings of fact 

and transmit them to the Administrator 

or designee. The decision on the appeal 

shall be made by the NASA 

Administrator or designee. There is no 

further right of administrative appeal 

from the decision of the Administrator 

or designee. 

1245.212 Protaction and administration 

of inventions. 

NASA may take any suitable and 

necessary steps to protect and 

administer rights to NASA inventionr. 

either directly or through contract. 

0 1245.213 Transfer of custody. 

NASA having custody of certain 

Federally owned inventions may 

transfer custody and administration in 

whole or in part, to another Federal 

agency, of the right, title, or interest in 

any such invention. 

0 1245.214 Conliiblity of infwmatkn 

Title 35, United States Code, section 

209. provides that any plan submitted 

pursuant to g 1245.207(h) and any report 

required by 8 1245.204(b)(e) may be 

treated by NASA as commercial and 

financial information obtained from a 

person and privileged and confidential 

and not subject to disclosure under 

section 552 of Title 5 of the United 

States Code. 

Iamer M. -& 

A dministmfor. 

October 15.1sCn. 

IFR Doc. 8141809 F1*d lO-m-Dl. 8AS ma 

I)ILUL(Q COO€ 7SlO-094 
-- 

! 

j 

ACCESSION NUMBER RANGES 

Bibliography Number STAR Accession Numbers 

NASA SP-7039(04) SEC 1 

NASAS?-703!3(12&S€C 1 

NASA SP-7039( 13) SEC 1 

NASA SP-7039(14) SEC 1 

NASA SP-7039(15) SEC 1 

NASA SP-7039( 16) SEC 1 

NASA SP-7039( 17) SEC 1 

NASA SP-7039(18) SEC 1 

NASA SP-7039(19) SEC 1 

NASA SP-7039(20) SEC 1 

NASA SP-7039(21) SEC 1 

NASA SP-7039(22) SEC 1 

NASA SP-7039(23) SEC 1 

NASA SP-7039(24) SEC 1 

NASA SP-7039(25) SEC 1 

NASA SP-7039(26) SEC 1 

NASA SP-7039(27) SEC 1 

NASA SP-7039(28) SEC 1 

NASA SP-7039(29) SEC 1 

NASA SP-7039(30) SEC 1 

NASA SP-7039(31) SEC 1 

N69-20701 - N73-33931 

N74-a001 ~N77-34042 

N78-1 OOO1 - N78-22018 

N78-22019 - N78-34034 

N79-10001 e- N79-21993 

N79-21994 - N79-34158 

N80-10001 - N80-22254 

N80-22255 - N80-34339 

N81-10001 - N81-21997 

N81-21998 - N81-34139 

N82-10001 - N82-22140 

N82-22141 - N82-34341 

N83-1 OOO T - N83-23266 

N83-23267 - N83-37053 

N84-10001 - N84-22526 

N84-22527 - N84-35284 

N85-10001 - N85-22341 

N85-22342'- N85-36162 

N86-1 OOO1 - N86-22536 

N86-22537 - N86-33262 

N87-10001 - N87-20170 

This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National 

Aeronautics and Space Administration by RMS Associates. 
1. Report No. 

NASA SP-7039 (31) 

A Continuing Bibliography 

Section 1 : Abstracts (Supplement 31) 

2. Government Accession No. 3. Recipient's Catalog No. 

,, ~ - 

6. Performing Organization Code 

4. Title and Subtitle 

NASA Patent Abstracts Bibliography 

7. Author@) 

5. Report Date 

Julv. 1987 

8. Performing Organization Report No. 

9. Performing Organization Name and Address 

National Aeronautics and Space Administration 

Washington, DC 20546 

12. Sponsoring Agency Name and Address 

10. Work Unit No. 

11. Contract or Grant No. 

13. Type of Report and Period Covered 

14. Sponsoring Agency Code 

19. Security Classif. (of this report) 20. Security Classif. 

t 

15. Supplementary Notes 

Section 1: Abstracts 

this page) 21. No. of Pages 22. Price 

16. Abstract 

Unclassified 

Abstracts are provided for 85 patents and patent applications entered into the NASA scientific and technical 

information system during the period January 1987 through June 1987. Each entry consists of a citation, an 

abstract, and in most cases, a key illustration selected from the patent or patent application. 

Unclassified 46 A03lHC 

17. Key Words (Suggested by Authors(s)) 

Bibliographies 

Patent Policy 

NASA Programs 

18. Distribution Statement 

Unclassified - Unlimited 

* For sale by the National Technical Information Service, Springfield, Virginia 22161 NASA-Langley, 1987