NASA 

PATENT 

ABSTRACTS 

BIBLIOGRAPHY 

A CONTINUING BIBLIOGRAPHY 

Section 1 Abstracts 

JANUARY 1987 

{NASA-SP-7039 (30) -Sect-l) NASB EATEWT NE7-16654 

AESTBAC3S BIBLICGEAPBY: A CCI'IZBDXNG 

EIBLICGEAPHY. SECTICN 1: AESIEACIS 

[SUPPLEfiEIT 30) [laticrial Aeicnautics and Unclas 

sgace Bdsi:;istraticrn) 50 p CSCL 058 00182 43479 
.. r, 

'& 

ACCESSION NUMBER RANGES 

Bibliography Number 

NASA SP-7039(04) SEC 1 

NASA SP-7039( 12) SEC 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 

STAR Accession Numbers 

N69-20701 - N73-33931 

N74-10001 - N77-34042 

N78-10001 - N78-22018 

N78-22019 - N78-34034 

N79-10001 - 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 

N83-10001 - N83-23266 

N83-23267 - N83-37053 

N84-10001 - N84-22526 

N84-22527 - N84-35284 

N85-10001 - N85-22341 

N85-22342 - N85-36162 

N86-10001 - N86-22536 

N86-22537 - N86-33262 

This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National 

Aeronautics and Space Administration by RMS Associates. 
NASA SP-7039(30) 

Section 1 

Abstracts 

NASA 

PATENT 

ABSTRACTS 

BIBLIOGRAPHY 

A CONTINUING BIBLIOGRAPHY 

Section 1 Abstracts 

Annotated references to NASA-owned inventions 

covered by U.S. patents and applications for patent 

that were announced in Scientific and Tmhnical 

Aerospace Reports (STAR) between July 1986 and 

December 1986. 

Scientific and Technical Information Branch 1987 

Washington, DC 

National Aeronautics and Space Administration 
This supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161, 

price code 1403. 
INTRODUCTION 

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 PAB 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 PAB 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 105 citations published in this issue of the Abstract Section cover the period July 1986 through December 

1986. The Index Section references over 4500 citations covering the period May 1969 through December 1986. 

ABSTRACT SECTION (SECTION 1) 

This PAB issue incorporates the 1975 STAR category revisions which include 10 major subdivisions divided into 

74 specific categories and one general category/division. (See Table of Contents for the scope note of each category 

under which are grouped appropriate NASA inventions.) This new scheme was devised in lieu of the 34 category 

divisions which were utilized in PAB 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 in 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(@ 

(for issued patents only) 

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

iii 
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) U.S. 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 U.S. 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 Categow: 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 Category listing. 

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

not include applications for 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 I 

ouiiinea in (Pj(Bj, ana (Dj above. 

iv 
TYPICAL CITATION AND ABSTRACT 

ON MICROFICHE 

NASA SPONSORED 1 1 

ACCESSION NUMBER-NE6-20470'# National Aeronautics and Space Administration. 

TITLE-TELESCOPING SPACE STATION MODULES Patent 

Langley Research Center. Hampton, Va. - CORPORATE SOURCE 

Application 

INVENTORS-R. D. WITCOFSKI, inventor (to NASA) 31 Jul. 1985 15 p 

NASA CASE NUMBER-(NASA-CASE-LAR-13330-1; NAS 1.71:LAR-13330-1; 

US-PATENT-APPL-SN-761233) Avail: NTlS 

I 

HC AO2lMF A01 - PRICE CODE 

US PATENT APPLICATIONS/CSCL 22B 

SERIAL NUMBER 

AVAILABILITY SOURCE / A space station module consisting of a cylindrical can within a 

can is presented. The outer can, which has one open end, encloses 

the inner can. The inner can has one tapered end with a hatch 

and one untapered end with a hatch. The outer can has one 

tapered end with a hatch. The overall length of the outer can is 

25 11. and its outer diameter is 14 8. Two such assemblies easily 

fit end lo end in the Shuttle Orbiter payload bay. With a shuttle -ABSTRACT 

payload capability of 65,000 pounds and an approximate weight 

of each twin can assembly of 16,000 pounds, 33,000 pounds of 

payload are available for instrumenting the cans. Only the inner 

can can be instrumented prior to launch. Once in orbit, the module 

is expanded to provide twice the usable space, approximately 48 

11 total length. NASA 

COSATI CODE 

V 
TABLE OF CONTENTS 

Section 1 0 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 N.A. 

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 

tions; and aircraft accidents. 

tation and 85 Urban Technology and Transportation. 

04 AIRCRAFT COMMUNICATIONS AND 

1 

Includes passenger and cargo air transport operaFor related information see also 76 Space TransporNAVIGATION 1 

Includes digital and voice communication with aircraft; air navigation systems (satellite and ground 

based); and air traffic control. 

For related information see also 7 7 Spacecraft Communications, Command and Tracking and 32 Communications. 

05 AIRCRAFT DESIGN, TESTING AND 

PERFORMANCE N.A. 

Includes aircraft simulation technology. 

For related information see also 78 Spacecraft Design, Testing and Performance and 39 Structural 

Mechanics. 

06 AIRCRAFT INSTRUMENTATION 2 

Includes cockpit and cabin display devices; and 

flight instruments. 

For related information see also 19 Spacecraft 

Instrumentation and 35 Instrumentation and 

Photography. 

07 AIRCRAFT PROPULSION AND POWER N.A. 

Includes prime propulsion systems and systems 

components, e.g., gas turbine engines and compressors; and on-board auxiliary power plants for aircraft. 

For related information see also 20 Spacecraft Propulsion and Power, 28 Propellants and Fuels. and 44 

Energy Production and Conversion. 

08 AIRCRAFT STABILITY AND CONTROL 

controls; and autopilots. 

09 RESEARCH AND SUPPORT 

2 

Includes aircraft handling qualities; piloting; flight 

FACILITIES (AIR) 3 

Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tube 

facilities; and engine test blocks. 

For related information see also 14 Ground Support 

Systems and Facilities (Space). 

ASTRONAUTICS 

Includes astronautics (general), astrodynamics, 

ground support systems and facilities (space), launch 

vehicles and space vehicles, space transportation, 

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 

orbit 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; manned orbital laboratories; 

reusable vehicles: and space stations. 

16 SPACE TRANSPORTATION 3 

Includes passenger and cargo space transportation, 

e.g., shuttle operations; and rescue techniques. 

For related information see also 03 Air Transportation and Safety and 85 Urban Technology and Transportation. 

17 SPACECRAFT COMMUNICATION, 

COMMAND AND TRACKING N.A. 

Includes telemetry; space communications netFor related information see also 04 Aircraft Comworks; astronavigation; and radio blackout. 

munications and Navigation and 32 Communications. 

18 SPACECRAFT DESIGN, TESTING AND 

PERFORMANCE 4 

Includes spacecraft thermal and environmental control; and attitude control. 

For life support systems see 54 ManISystem Technology and Life Support For related information see 

also 05 Aircraft Design, Testing and Performance and 

39 Structural Mechanics 

19 SPACECRAFT INSTRUMENTATION N.A. 

For related information see also 06 Aircraft 

Instrumentation and 35 Instrumentation and 

Photography 

20 SPACECRAFT PROPULSION AND 

POWER 4 

Includes main propulsion systems and components, 

e g , rocket engines, and spacecraft auxiliary power 

sources 

For related information see also 07 Aircraft Propulsion and Power, 28 Propellants and Fuels, and 44 Energy Production and Conversion 

vi 
CHEMISTRY AND MATERIALS 

Includes chemistry and materials (general); 

composite materials; inorganic and physical chemistry; 

metallic materials; nonmetallic materials; and 

propellants and fuels. 

23 CHEMISTRY AND MATERIALS 

(GENERAL) 5 

Includes biochemistry and organic chemistry. 

24 COMPOSITE MATERIALS 

Includes laminates. 

5 

25 INORGANIC AND PHYSICAL 

CHEMISTRY 6 

Includes chemical analysis, e.g.. chromatography; 

combustion theory; electrochemistry; and photochemistry. 

For related information see also 77 Thermodynamics and Statistical Physics. 

26 METALLIC MATERIALS 7 

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

27 NONMETALLIC MATERIALS 8 

Includes physical, chemical, and mechanical properties of plastics, elastomers, lubricants, polymers, textiles, adhesives, and ceramic materials. 

28 PROPELLANTS AND FUELS 11 

Includes rocket propellants, igniters, and oxidizers; 

storage and handling; and aircraft fuels. 

For related information see also 07 Aircraft Propulsion and Power, 20 Spacecraft Propulsion and Power, 

and 44 Energy Production and Conversion. 

ENGINEERING 

Includes engineering (general); communications; 

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. 

Includes vacuum technology; control engineering; 

display engineering; and cryogenics. 

32 COMMUNICATIONS 13 

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

For related information see also 04 Aircraft Communications and Navigation and 17 Spacecraft Communications. Command and Tracking. 

33 ELECTRONICS AND ELECTRICAL 

31 ENGINEERING (GENERAL) 12 

ENGINEERING 15 

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

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 02 Aerodynamics 

mass transfer; and ablation cooling. 

and 77 Thermodynamics and Statistical Physics. 

35 INSTRUMENTATION AND 

PHOTOGRAPHY 17 

Includes remote sensors; measuring instruments 

and gages; detectors; cameras and photographic 

supplies; and holography. 

For aerial photography see 43 Earth Resources. For 

related information see also 06 Aircraft Instrumentation 

and 19 Spacecraft Instrumentation, 

36 LASERS AND MASERS 

Includes parametric amplifiers. 

21 

37 MECHANICAL ENGINEERING 22 

Includes auxiliary systems (non-power); 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 25 

Includes structural element design and weight analysis; fatigue; and thermal stress. 

For applications see 05 Aircraft Design, Testing and 

Performance and 18 Spacecraft Design, Testing and 

Performance. 

GEOSCIENCES 

Includes geosciences (general); earth resources; 

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 N.A. 

Includes remote sensing of earth resources by aircraft and spacecraft; photogrammetry; and aerial 

photography. 

For instrumentation see 35 Instrumentation and 

Photography. 

44 ENERGY PRODUCTION AND 

CONVERSION 25 

Includes specific energy conversion systems, e.g., 

fuel cells and batteries; global sources of energy; fossil 

fuels; geophysical conversion; hydroelectric power; 

and wind power. 

For related information see also 07 Aircraft Propulsion and Power, 20 Spacecraft Propulsion and Power, 

28 Propellants and Fuels, and 85 Urban Technology 

and Transportation. 

45 ENVIRONMENT POLLUTION N.A. 

Includes air, noise, thermal and water pollution; environment monitoring; and contamination control. 

46 GEOPHYSICS N.A. 

Includes aeronomy; upper and lower atmosphere 

studies; ionospheric and magnetospheric physics; and 

geornayetism. 

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. 

vii 
LIFE SCIENCES 

Includes sciences (general), aerospace medicine 

behavioral sciences man system technolbgy and life 

support. and planetary biology 

51 LIFE SCIENCES (GENERAL) N.A. 

Includes genetics 

52 AEROSPACE MEDICINE N.A. 

Includes physiological factors, biological effects of 

radiation. and weightlessness 

53 BEHAVIORAL SCIENCES N.A. 

Includes psychological factors, individual and group 

behavior, crew training and evaluation. and psychiatric 

research 

54 MANSYSTEM TECHNOLOGY AND 

LIFE SUPPORT 27 

Includes human engineering: biotechnology; and 

space suits and protective clothing. 

55 PLANETARY BIOLOGY N.A. 

Includes exobiology; 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 28 

Includes computer graphics and data processing 

For components see 33 Electronics and Electrical 

Engineering 

61 COMPUTER PROGRAMMING AND 

SOFTWARE N.A. 

Includes computer programs, routines, and algorithms 

62 CG;riPiiiE; S.,.SiEiS 

Includes computer networks 

63 CYBERNETICS N.A. 

Includes feedback and control theory 

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 N.A. 

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 fngmeermg 

70 PHYSICS (GENERAL) N.A. 

Fo grophysics see 46 Geophysics For astrophysics see 90 Astrophysics For solar physics see 

92 Solar Physics 

71 ACOUSTICS N.A. 

Includes sound generation. transmission. and attenuation 

For noise pollution see 45 Environment Pollution 

72 ATOMIC AND MOLECULAR PHYSICS 29 

Includes atomic structure and molecular spectra 

73 NUCLEAR AND HIGH-ENERGY 

PHYSICS N.A. 

Includes elementary and nuclear particles. and reacFor space radiation see 93 Space Radiation 

tor theory 

74 OPTICS 

Includes light phenomena. 

30 

75 PLASMA PHYSICS N.A. 

Includes magnetohydrodynamics and plasma fusion 

For ionospheric plasmas see 46 Geophysics For 

space plasmas see 90Astrophysic.s 

76 SOLID-STATE PHYSICS 32 

Includes superconductivity 

For related information see also 33 Electronics and 

Electrical Engineermg and 36 Lasers and Masers 

77 THERMODYNAMICS AND 

STATISTICAL PHYSICS N.A. 

Includes quantum mechanics. and Bose and Fermi 

statistics 

Fur reidieu iriiurmdtion see ais0 25 inorganic ana 

Physical Chemistry and 34 Fluid Mechanics and Heat 

Transfer 

S O C I A L S C I E N C E S 

Includes social sciences (general), administration 

and management, documentation and information science, economics and cost analysis. law and political 

science, 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. 

viii 
82 DOCUMENTATION AND 

INFORMATION SCIENCE 

88 SPACE SCIENCES (GENERAL) N.A. 

32 

Includes information storage and retrieval technolFor computer documentation see 61 Computer 

ogy, micrography. and library science 

Programming and Software 

83 ECONOMICS AND COST ANALYSIS N.A. 

Includes cost effectiveness studies. 

84 LAW AND POLITICAL SCIENCE N.A. 

Includes space law; international law; international 

cooperation; and patent policy. 

85 URBAN TECHNOLOGY AND 

TRANSPORTATION V.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 Safety, 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 

89 ASTRONOMY N.A. 

Includes radio and gamma-ray astronomy, celestial 

mechanics, and astrometry 

90 ASTROPHYSICS N.A. 

Includes cosmology, and interstellar and interplanetary gases and dust 

91 LUNAR AND PLANETARY 

EXPLORATION N.A. 

Includes planetology, and manned and unmanned 

flights 

For spacecraft design see 78 Spacecraft Design, 

Testing and Performance For space stations see 15 

Launch Vehicles and Space Vehicles 

92 SOLAR PHYSICS N.A. 

Includes solar activity, solar flares. solar radiation 

and sunspots 

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 

99 GENERAL N.A. 

Note: N.A. means that no abstracts were assigned to this category for this issue 

Section 2 0 Indexes 

SUBJECT INDEX 

INVENTOR INDEX 

SOURCE INDEX 

NUMBER INDEX 

ACCESSION NUMBER INDEX 

ix 
JANUARY 1987 (Supplement 30) 

NASA Patent Abstracts Bibliography 

A Semiannual Publication of the National Aeronautics and Space Administration 

03 

AIR TRANSPORTATION AND SAFETY 

Includes passenger and cargo air transport operations; and aircraft 

accidents. 

N86-24673'# 

Langley Research Center, Hampton, Va. 

ICE DETECTOR Patent Appllcatlon 

L. M. WEINSTEIN, inventor (to NASA) 31 Mar. 1986 14 p 

(NASA-CASE-LAR-13403-1; NAS 1.71 :LAW1 3403-1; 

US-PATENT-APPL-SN-846429) Avail: NTlS HC AO2/MF A01 

CSCL 01c 

An ice detector for aircraft that can accurately determine the 

presence and thickness of ice and control devices to remove it is 

proposed. A small depression on the surface of an aircraft structure 

is filled with a plastic or epoxy material. Two capacitance gauges 

and a temperature gauge are embedded in this material near the 

surface. When moisture forms on the surface the capacitance of 

each of the gauges changes. This signal combined with the signal 

from a temperature gauge determines whether the moisture is 

water or ice. If ice is present its thickness may be measured 

based on the output of the second capacitance gauge. Once the 

presence of ice is determined, the thickness is easily determined. 

The output of the device may be used to provide an indication to 

the pilot or to automatically control heating elements to remove 

the ice. NASA 

National Aeronautics and Space Administration. 

N86-26296'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

LIGHTNING DISCHARGE PROTECTION ROD Patent 

Appllcatlon 

C. F. BRYAN, JR., inventor (to NASA) 24 Apr. 1986 14 p 

Sponsored by NASA 

(NASA-CASE-LAR-13470-1; NAS 1.71 :LAR-13470-1; 

US-PATENT-APPL-SN-855983) Avail: NTlS HC AO2/MF A01 

CSCL 01c 

This invention is a system for protecting an in-air vehicle from 

damage due to the craft sustaining a lightning strike. It is an 

extremely simple device consisting of a sacrificial graphite 

composite rod, approximately the diameter of a pencil with a length 

of about five inches. The sacrificial rod is constructed with the 

graphite fibers running axially within the rod in a manner that best 

provides a path of conduction axially from the trailing edge of an 

aircraft to the trailing end of the rod. The sacrificial rod is inserted 

into an at!achment hole 32 machined into trailing edges of aircraft 

flight surfaces, such as vertical fin cap 31, and attached with 

adhesive in a manner not prohibiting the conduction path between 

the rod and aircraft. The trailing end of rod may be tapered for 

aerodynamic and esthetic requirements. This rod is sacrificial but 

has the capability to sustain several lightning strikes and still provide 

protection. The novelty of this invention appears to reside in a 

system for protecting the most vulnerable parts of an in-air vehicle 

when the craft is hit by lightning with an extremely simple and 

inexpensive device. The materials are easily procured and the 

sacrificial rod generally can be constructed from the same 

composite as the flight or control surface to be protected. The 

protection extends to several in-air lightning strikes and provides 

protection to aircraft parts manufactured from all materials including 

organic composites. NASA 

04 

AIRCRAFT COMMUNICATIONS AND NAVIGATION 

Includes digital and voice communication with aircraft; air navigation 

systems (satellite and ground based); and air traffii control. 

N86-27270' National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

HIGH DYNAMIC GLOBAL POSITIONING SYSTEM RECEIVER 

Patent 

W. J. HURD. inventor (to NASA) (Jet Propulsion Lab., California 

Inst. of Tech., Pasadena) 25 Mar. 1986 13 p Filed 14 Nov. 

1983 Supersedes N84-12151 (22 - 03, p 330) Sponsored by 

NASA. Pasadena Office 

(NASA-CASE-NPO-16171-1 CU; US-PATENT-4.578,678; 

US-PATENT-APPL-SN-551536; US-PATENT-CLASS343-357; 

US-PATENT-CLASS-343-41 8) 

Office CSCL 17G 

A Global Positioning System (GPS) receiver having a number 

of channels, receives an aggregate of pseudorange code Ume 

division modulated signals. The aggregate is converted to baseband 

and then to digital form for separate processing in the separate 

channels. A fast fourier transform processor computes the signal 

energy as a function of Doppler frequency for each correlation 

lag, and a range and frequency estimator computes estimates of 

pseudorange, and frequency. Raw estimates from all channels 

are used to estimate receiver position, velocity. clock offset and 

Avail: US Patent and Trademark 

1 
06 AIRCRAFT INSTRUMENTATION 

clock rate offset in a conventional navigation and control unit, 

and based on the unit that computes smoothed estimates for the 

next measurement interval. 

Official Gazette of the U.S. Patent and Trademark Office 

06 

AIRCRAFT INSTRUMENTATION 

Includes cockpit and cabin display devices; and flight instruments. 

N86-27280' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

AIRCRAFT LIFTMETER Patent 

E. W. MILLEN, inventor (to NASA) 29 Apr. 1986 10 p Filed 

8 Feb. 1984 Supersedes N84-32383 (22 - 22, p 3535) Sponsored 

by NASA. Langley Research Center 

(NASA-CASE-LAR-12518-1; US-PATENT-4.586,140; 

US-PATENT-APPL-SN-578388; US-PATENT-CLASS-364-433; 

US-PATENT-CLASS-364-435; US-PATENT-CLASS-244-1 81 ; 

US-PATENT-CLASS-73-1 78T; US-PATENT-CLASS-340-968) 

Avail: US Patent and Trademark Office CSCL 01 D 

A display for aiding the pilot of an aircraft in anomalous wind 

environments is described. Wind velocity components are 

measured by an instrument, processed by a computer and a vector 

generator, and then displayed as a vector. The display utilizes the 

measurements of ground speed and of wind velocity in three 

mutually perpendicular directions. This display will also show 

changes in lift of an aircraft. 

Official Gazette of the U.S. Patent and Trademark Office 

AIRCRAFT STABILITY AND CONTROL 

Includes aircraft handling qualities; piloting; flight controls; and 

autopilots. 

N86-24700'# National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

SWASHPLATE CONTROL SYSTEM Patent Application 

R. J. PEYRAN, inventor (to NASA) (Army Aviation Engineering 

Flight Activity, Edwards AFB, Calif.), G. H. LAUB. inventor (to NASA) 

(Army Aviation Engineering Flight Activity, Edwards AFB. Calif.), 

and H. A. MORSE, inventor (to NASA) (Army Aviation Engineering 

Flight Activity, Edwards AFB, Calif.) 31 Mar. 1986 13 p 

(NASA-CASE-ARC-1 1633-1; NAS 1.71 :ARC-11633-1; 

US-PATENT-APPL-SN-846439) Avail: NTlS HC AO2/MF A01 

CSCL 01c 

A mechanical system to control the position of a rotating 

swashplate is developed. This system provides independent lateral 

cyclic, longitudinal cyclic and collective pitch control of a helicopter 

rotor attached to the swashplate, without use of a mixer box. The 

system also provides direct, linear readout of cyclic and collective 

swashplate positions. A swashplate control system has a first 

gimbal ring pivotally mounted along a longitudinal axis. A second 

gimbal ring is pivotally attached to the first gimbal ring along a 

lateral axis. A longitudinal cyclic actuator pivots the first gimbal 

ring along the longitudinal axis. A lateral cyclic actuator pivots the 

second gimbal ring along the lateral axis. The lateral cyclic actuator 

is mounted on the first gimbal ring. A swashplate is rotatably 

mounted on the second gimbal ring. Prior swashplate control 

systems required use of a mixer box to provide true decoupling of 

lateral and longitudinal cyclic input to the swashplate. NASA 

N86-27288' National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field. Calif. 

THUMB-ACTUATED TWO-AXIS CONTROLLER Patent 

R. H. HOLLOW, inventor (to NASA) (Computer Sciences Cop., 

Mountain View, Calif.) 22 Apr. 1986 11 p Filed 8 Sep. 1982 

Supersedes N83-12098 (21 - 03, p 328) Sponsored by NASA. 

Ames Research Center 

(NASA-CASE-ARC-1 1372-1; US-PATENT-4,584,510; 

US-PATENT-APPL-SN-415878; US-PATENT-CLASS91 8-584; 

US-PATENT-CLASS-31 8-640; US-PATENT-CLASS-250-21 1 K; 

US-PATENT-CLASS-200- 1 57; US-PATENT-CLASS-244-234) 

Avail: US Patent and Trademark Office CSCL 01C 

A two axis joystick controller is described. It produces at least 

one output signal in relation to pivotal displacement of a member 

with respect to an intersection of the two axes. The member is 

pivotally movable on a support with respect to the two axes. The 

2 
16 SPACE TRANSPORTATION 

support has a centrally disposed aperture. A light source is mounted 

on the pivotally movable member above the aperture to direct 

light through the aperture. A light sensor is mounted below the 

aperture in the support at the intersection of the two axes to 

receive the light from the light source directed through the aperture. 

The light sensor produces at least one output signal related to a 

location on the sensor at which the light from the light source 

strikes the sensor. 

Official Gazette of the US. Patent and Trademark Office 

-, .-- a ,- 

f .- 1 I .z 

2. .* 

09 

RESEARCH AND SUPPORT FACILITIES (AIR) 

Includes airports, hangars and runways; aircraft repair and overhaul 

facilities; wind tunnels; shock tube facilities; and engine test 

blocks. 

N86-31594'# National Aeronautics and Space Administration. 

Langley Research Center. Hampton, Va. 

AIRFOIL FLUTTER MODEL SUSPENSION SYSTEM Patent 

Appllcatlon 

W. H. REED, 111, inventor (to NASA) (DEI-Tech, Inc., Newport News, 

Va.) 30 Jul. 1986 14 p 

(Contract NASl -1 7686) 

1.71:LAR-13522-1) Avail: NTlS HC A02/MF A01 CSCL 148 

The invention is a wind tunnel suspension system for testing 

flutter models under various loads and at various angles of attack. 

The invention comprises a mounting bracket assembly affixing the 

suspension system to the wind tunnel, a drag-link assembly and 

a compound spring arrangement. The compound spring 

arrangement comprises a plunge spring working in opposition .to 

a compressive spring so as to provide a high stiffness to trim out 

steady state loads and simultaneously a low stiffness to dynamic 

loads. By this arrangement an airfoil may be tested for oscillatory 

response in both plunge and pitch modes while being held under 

high lifting loads in a wind tunnel. NASA 

(NASA-CASE-LAR-13522-1; US-PATENT-APPL-SN-890575; NAS 

N86-32447. National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

SIMULATOR SCENE DISPLAY EVALUATION DEVICE Patent 

R. F. HAINES, inventor (to NASA) 12 Aug. 1986 8 p Filed 

22 Dec. 1983 Supersedes N84-16221 (22 - 07, p 960 

Avail: US Patent and Trademark Office CSCL 148 

An apparatus for aligning and calibrating scene displays in an 

aircraft simulator has a base on which all of the instruments for 

the aligning and calibrating are mounted. Laser directs beam at 

double right prism which is attached to pivoting support on base. 

The pivot point of the prism is located at the design eye point 

(DEP) of simulator during the aligning and calibrating. The objective 

lens in the base is movable on a track to follow the laser beam 

at different angles within the field of vision at the DEP. An eyepiece 

and a precision diopter are movable into a position behind the 

prism during the scene evaluation. A photometer or illuminometer 

is pivotable about the pivot into and out of position behind the 

eyepiece. 

Official Gazette of the US. Patent and Trademark Office 

(NASA-CASE-ARC-1 1504-1 ; US-PATENT-4,605,303; 

US-PATENT-APPL-SN-565481; US-PATENT-CLASS-356-73) 

16 

SPACE TRANSPORTATION 

Includes passenger and cargo space transportation, e.g., shuttle 

operations; and rescue techniques. 

N86-26352' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

MAGNETIC SPIN REDUCTION SYSTEM FOR FREE SPINNING 

OBJECTS Patent 

G. F. VONTIESENHAUSEN, inventor (to NASA) 15 Apr. 1986 

6 p Supersedes N85-11122 Filed 23 Aug. 1984 Sponsored by 

NASA 

(NASA-CASE-MFS-25966-1; US-PATENT-4,582,277; 

US-PATENT-APPL-SN-643522 US-PATENT-CLASS-244-1 61) 

Avail: US Patent and Trademark Office CSCL 228 

A spizzizg Ea$h satellite is shown in which it is desked to 

reduce the rotation or spin to a level that the satellite may be 

secured or handled remotely from a spacecraft. This is 

accomplished by the spacecraft having a mast carrying an electrical 

current coil which encircles the satellite. The magnetic field of the 

coil is normal to the spin axis of the satellite which causes circular 

eddy current flow in the housing of the satellite. This generates 

magnetic force opposing the rotation. In another embodiment the 

3 
18 SPACECRAFT DESIGN, TESTING AND PERFORMANCE 

magnetic field is generated by the use of an electromagnet on a 

remote manipulation arm. 

Official Gazette of the U.S. Patent and Trademark Office 

SPACECRAFT DESIGN, TESTING AND 

PERFORMANCE 

Includes spacecraft thermal and environmental control; and attitude 

control. 

N86-24729' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

SHUTTLE-LAUNCH TRIANGULAR SPACE STATION Patent 

W. C. SCHNEIDER, inventor (to NASA), R. B. BERKA, inventor 

(to NASA), C. KAVANAUGH, inventor (to NASA), K. NAGY, inventor 

(to NASA), R. C. PARISH, inventor (to NASA), J. A. SCHLIESING, 

inventor (to NASA), P. D. SMITH, inventor (to NASA), F. J. 

STEBBINS, inventor (to NASA), and C. J. WESSELSKI, inventor 

(to NASA) 1 Apr. 1986 9 p Filed 9 Mar. 1984 Sponsored 

by NASA 

Avail: US Patent and Trademark Office CSCL 22B 

A triangular space station deployable in orbit is described. The 

framework is cornprized of three trusses, formed of a pair of 

generally planar faces consistine of foldable struts. The struts 

expand and lock into rigid structural engagement forming a 

repetition of equilater triangles and nonfolding diagonal struts 

interconnecting the two faces. The struts are joined together by 

node fittings. The framework can be packaged into a size and 

configuration transportable by a space shuttle. When deployed, 

the framework provides a large work/construction area and ample 

of modules are secured to the framework and then joined by 

tunnels to make an interconnected modular display. Thruster units 

for the space station orientation and altitude maintenance are 

provided. 

Official Gazette of the U.S. Patent and Trademark Office 

(NASA-CASE-MSC-20676-1; US-PATENT-4.579.302; 

US-PATENT-APPL-SN-587764; US-PATENT-CLASS-244-1 59) 

p!gn.r snrtare ?_re?_ fer se!er pa!?e!c and !harms! ndi?_!erc. .A p!LVi!y 

,,- 

N86-31630'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

PRELOADED SPACE STRUCTURAL COUPLING JOINTS Patent 

Appllcatlon 

M. D. RHODES, inventor (to NASA) 30 Jul. 1986 16 p 

1.71:LAR-13489-1) Avail: NTlS HC AO2/MF A01 CSCL 228 

This invention relates to a coupling device for tubular members, 

of large truss structures, with a locking collar being the only moving 

part. Each tubular member is constructed with an end bell section 

that has a belled flange with a mating face, and a necked area 

which is smaller in diameter than the tubular members to be joined. 

A split ring is affixed to each tubular member and is constructed 

so that when two tubular members are laterally moved into axial 

alignment and the collar is rotated thereover, the split ring loads 

the joint with axial force by pressing the belled flange mating 

surfaces together, and a preloading force is provided by the collar 

mating with a taper on the outside of the split rings. All free play 

is thereby removed by preloaded force. A major object of the 

invention is to provide an ability to remove and replace individual 

tubular members without disturbing other structural parts of a truss 

structure. An additional anticipated use of this joint is to couple 

high pressure fluid lines. NASA 

(NASA-CASE-IAR-13489-1; US-PATENT-APPL-SN-890445; NAS 

IP 21 3. 

20 

SPACECRAFT PROPULSION AND POWER 

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

engines; and spacecraft auxiliary power sources. 

N86-26368' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

PROPULSION APPARATUS AND METHOD USING BOIL-OFF 

GAS FROM A CRYOGENIC LIQUID Patent 

D. H. BLOUNT, inventor (to NASA) 29 Apr. 1986 7 p Supersedes 

N84-15183 Filed 29 Apr. 1986 Sponsored by NASA 

(NASA-CASE-MFS-25946-1; US-PATENT-4.585,lgl; 

US-PATENT-APPL-SN-561432; US-PATENT-CLASS-244-1 69; 

US-PATENT-CLASS-244-1 58.R; US-PATENT-CLASS-60-203.1 ; 

US-PATENT-CLASS-60-39.465) Avail: US Patent and Trademark 

Office CSCL 21H 

A propulsion system and method are disclosed for controlling 

the attitude and drag of a space vehicle. A helium dewar contains 

liquid helium which cools an experiment package. The helium is 

heated or vented to keep the temperature between 1.5 and 1.7 

degrees K to maintain adequate helium boil-off gas as a propellant 

without adversely affecting the experiment package which is 

contained in the helium dewar for protection from solar heating. 

The apparatus includes auxiliary heater and temperature sensor 

for controlling the temperature of the helium. The boil-off gas 

4 
24 COMPOSITE MATERIALS 

propellant is delivered to thruster modules to control vehicle objects. These polyarylene ethers are suitable for use in adhesives, 

attutude and compensate for drag. coatings, films, membranes, and composite matrices. The 

Official Gazette of the U.S. Patent and Trademark Office polyarylene ethers of this invention are the polycondensation 

products from the reaction of either 1.3-bis (4-chloro or 

fluorobenzoyl) benzene with any one of the following bisphenolic 

compounds: bis (3-hydroxyphenyl) methane; bis (4-hydroxyphenyl) 

methane; 1.1 -dimethyl-bis (4-hydroxyphenyl)methane, or 9,9-bis 

(4-hydroxyphenyl) fluorene. Random and block copolymers are also 

comprehended. NASA 

24 

COMPOSITE MATERIALS 

Includes laminates. 

N86-25416' National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

LAMINATE COMPRISING FIBERS EMBEDDED IN CURED 

AMINE TERMINATED BIS-IMIDE Patent 

23 

CHEMISTRY AND MATERIALS (GENERAL) 

Includes biochemistry and organic chemistry. 

N86-32525' 

Ames Research Center, Moffett Field, Calif. 

BENZENE AND POLYFUNCTIONAL MONOMER Patent 

J. A. MIKROYANNIDIS. inventor (to NASA) (National Academy of 

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

A. KOURTIDES, inventor (to NASA) 6 May 1986 6 p Filed 

16 Aug. 1984 

National Aeronautics and Space Administration. 

POLYMER OF PHOSPHONYLMETHYL-2,4- AND -2,6-DIAMINO 

(NASA-CASE-ARC-1 1506-2; US-PATENT-4,587,324; 

US-PATENT-APPL-SN-641142; US-PATENT-CLASS-528-108; 

US-PATENT-CLASS-528-1 24; US-PATENT-CLASS-528-337; 

US-PATENT-CLASS-528-352; US-PATENT-CLASS-528-399; 

US-PATENT-CLASS-528-406; US-PATENT-CLASS-528-407) 

Avail: US Patent and Trademark Office CSCL 07A 

A phosphonyl methyl benzene is prepared by nitration to 

produce a 2,4-dinitro phosphonyl methyl benzene, which is then 

reduced to a diamino compound. The diamino compound is then 

used to cure a polymerizable monomer. The diamino compound 

may be polymerized with polyfunctional epoxides to produce heat 

and fire resistant polymer structures for making flame and fire 

resistant polymer structures such as for aircraft secondary 

structures. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-32526'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

POLYARYLENE ETHERS WITH IMPROVED PROPERTIES Patent 

Application 

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

inventor (to NASA), and S. J. HAVENS, inventor (to NASA) (PRC 

Kentron, Inc., Hampton, Va.) 5 Jun. 1986 18 p 

1.71:LAR-I3555-1) Avail: NTlS HC A02/MF A01 CSCL 07A 

This invention relates to novel polyarylene ethers which possess 

the combination of high strength, toughness, and high use 

temperature with ease of extrusion and formation into complex 

(NASA-CASE-LAR-13555-1; US-PATENT-APPL-SN-871207; NAS 

D. KUMAR, inventor (to NASA) (National Academy of Sciences - National Research Council, Washington, D. C.), G. M. FOHLEN, 

inventor (to NASA), and J. A. PARKER, inventor (to NASA) 1 

Apr. 1986 7 p Filed 30 Aug. 1985 Sponsored by NASA 

(NASA-CASE-ARC-1 1421 -3; US-PATENT-4,579-782; 

US-PATENT-APPL-SN-771538; US-PATENT-CLASS-428-473.5; 

US-PATENT-CLASS-428-474.4; US-PATENT-CLASS-428-477.7; 

US-PATENT-CLASS-528-1 70; US-PATENT-CLASS-528-220; 

US-PATENT-CLASS-528-321 ; US-PATENT-CLASS-528-322) 

Avail: US Patent and Trademark Office CSCL 11 D 

Amine terminated bisaspartimides are prepared by a Michael 

type reaction of an aromatic bismaleimide and an aromatic diamine 

in an aprotic solvent. These bisaspartimides are thermally 

polymerized to yield tough, resinous polymers crosslinked through 

-NH- groups. Such polymers are useful in applications requiring 

materials with resistance to change at elevated temperatures. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-28131' National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

LIGHT WEIGHT FIRE RESISTANT GRAPHITE COMPOSITES 

Patent 

D. A. KOURTIDES, J. A. PARKER, and M. T. S. HSU 1 Jul. 

1986 Filed 28 Feb. 1985 Supersedes N85-28976 (23 - 18, p 3068) 

12 p 

(NASA-CASE-ARC-1 161 5-1 SB; US-PATENT-4.598,007; 

US-PATENT-APPL-SN-706682; US-PATENT-CLASS-428-1 16; 

US-PATENT-CLASS-428-408; US-PATENT-CLASS-428-921; 

US-PATENT-CLASS-526-265) Avail: US Patent and Trademark 

Office CSCL 11 D 

Composite structures with a honeycomb core and characterized 

by lightweight and excellent fire resistance are provided. These 

sandwich structures employ facesheets made up of 

bismaleimide-vinyl styrylpyridine copolymers with fiber 

reinforcement such as carbon fiber reinforcement. In preferred 

embodiments the facesheets are over layered with a decorative 

5 
25 INORGANIC AND PHYSICAL CHEMISTRY 

film. The properties of these composites make them attractive 

materials of construction aircraft and spacecraft. 

Official Gazette of the U.S. Patent and Trademark Office 

25 

INORGANIC AND PHYSICAL CHEMISTRY 

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

theory; electrochemistry; and photochemistry. 

N86-25428' National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

SOLAR HEATED OIL SHALE PYROLYSIS PROCESS Patent 

S. A. QADER, inventor (to NASA) (Jet Propulsion Lab., California 

Inst. of Tech., Pasadena) 15 Apr. 1985 7 p Filed 23 Jul. 

1984 Supersedes N84-32912 Sponsored by NASA 

(NASA-CASE-NPO-16392-1; US-PATENT-4,582,590; 

US-PATENT-APPL-SN-633363; US-PATENT-CLASS-208-1 1 ; 

US-PATENT-CLASS-48-1 974; US-PATENT-CLASS-8-DIG.9) 

Avail: US Patent and Trademark Office CSCL 07D 

An improved system for recovery of a liquid hydrocarbon fuel 

from oil shale is presented. The oil shale pyrolysis system is 

composed of a retort reactor for receiving a bed of oil shale 

particules which are heated to pyrolyis temperature by means of 

a recycled solar heated gas stream. The gas stream is separated 

from the recovered shale oil and a portion of the gas stream is 

rapidly heated to pyrolysis temperature by passing it through an 

efficient solar heater. Steam, oxygen, air or other oxidizing gases 

can be injected into the recycle gas before or after the recycle 

gas is heated to pyrolysis temperature and thus raise the 

temperature before it enters the retort reactor. The use of solar 

thermal heat to preheat the recycle gas and optionally the steam 

before introducing it into the bed of shale, increases the yield of 

shale oil. 

Official Gazette of the U.S. Patent and Trademark Office 

--. *.., 

N86-27431 National Aeronautics and Space Administration. 

Lyndon B. Johnson Space Center, Houston, Tex. 

SPILLAGE DETECTOR FOR LIQUID CHROMATOGRAPHY 

SYSTEMS Patent 

M. J. JARVIS (Illinois Univ., Urbana) and D. S. FULTON, inventors 

(to NASA) 27 May 1986 12 p Filed 23 Mar. 1983 Supersedes 

N83-29325 (21 - 18, p 2890) Sponsored by NASA. Johnson 

Space Center 

(NASA-CASE-MSC-20206-1; US-PATENT-4,591,838; 

US-PATENT-APPL-SN-478129; US-PATENT-CUSS-340-605; 

US-PATENT-CUSS-200-61.05; US-PATENT-CLASS-1 41 -1 98) 

Avail: US Patent and Trademark Office 

A spillage detector device for use in conjunction with 

fractionation of liquid chromatography systems which includes a 

spillage recieving enclosure beneath the fractionation area is 

described. A sensing device having a plurality of electrodes of 

alternating polarity is mounted within the spillage recieving 

enclosure. Detection circuitry, responsive to conductivity between 

electrodes, is operatively connected to the sensing device. The 

detection circuitry feeds into the output circuitry. The output circuit 

has relaying and switching circuitry directed to a solenoid, an alarm 

system and a pump. The solenoid is connected to the pliable 

conduit of the chromatography system. The alarm system 

comprises an audio alarm and a visual signal. A 11 5-volt power 

system interconnected with the pump, the solenoid, the sensing 

device, and the detection and output circuitry. 

Official Gazette of the U.S. Patent and Trademark Office 

CSCL 07D 

N86-32540'# 

Langley Research Center, Hampton, Va. 

Patent Application 

R. V. HESS, inventor (to NASA), B. T. UPCHURCH, inventor (to 

NASA), K. G. BROWN, inventor (to NASA) (Old Dominion Univ.. 

Norfolk, Va.). I. M. MILLER, inventor (to NASA), D. R. SCHRYER. 

inventor (to NASA), B. D. SIDNEY, inventor (to NASA), G. M. 

WOOD, inventor (to NASA), and R. F. HOYT, inventor (to NASA) 

National Aeronautics and Space Administration. 

ISOTOPE EXCHANGE IN OXIDE-CONTAINING CATALYST 

12 Jun. 1986 11 p 

(Contract NASA-ORDER L-79510-B NASA-ORDER L-83135-8; 

NASl -1 7993) 

NAS 1.71:LAR-13542) Avail: NTlS HC AO2/MF A01 CSCL 

07D 

A method of exchanging rare-isotope oxygen for 

common-isotope oxygen in the top several layers of an 

oxide-containing catalyst is disclosed. A sample of an 

oxide-containing catalyst is exposed to a flowing stream of reducing 

gas in an inert carrier gas at a temperature suitable for the removal 

of the reactive common-isotope oxygen atoms from the surface 

layer or layers of the catalyst without damaging the catalyst 

structure. The reduction temperature must be higher than any at 

which the catalyst will subsequently operate. Sufficient reducing 

gas is used to allow removal of all of the reactive common-isotope 

oxygen atoms in the top several layers of the catalyst. The catalyst 

is then reoxidized with the desired rare-isotope oxygen in sufficient 

quantity to replace all of the common-isotope oxygen that was removed. NASA 

(NASA-CASE-LAR-13542-1 SB; US-PATENT-APPL-SN-874304; 

6 
26 METALLIC MATERIALS 

N8&32541'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton. Va. 

PRETREATMENT AND REACTIVATION OF AN 

OXIDECONTAINING CATALYST Patent Appllcatlon 

B. T. UPCHURCH, inventor (to NASA), I. M. MILLER, inventor (to 

NASA), K. G. BROWN, inventor (to NASA), R. V. HESS, inventor 

(to NASA), D. R. SCHRYER, inventor (to NASA), B. D. SIDNEY, 

inventor (to NASA), G. M. WOOD, inventor (to NASA), and P. A. 

PAULIN, inventor (to NASA) 12 Jun. 1986 9 p 

(Contract NASA ORDER-L-795106; NASA ORDER-L-831358; 

NASl -1 7099) 

(NASA-CASE-LAR-13540-1SB; USPATENT-APPL-SN-874320; 

NAS 1.71:LAR-13540-1) Avail: NTlS HC AOWMF A01 CSCL 

07D 

A pretreatment and reactivation process for enhancing the 

recombination activity of an oxide-containing catalyst is disclosed. 

Pretreatment is achieved by first exposing the catalyst to a flowing 

stream of a reducing agent in an inert carrier gas while the catalyst 

is heated to a temperature greater than its operating temperature. 

The catalyst is then exposed to a flowing stream of the inert 

carrier gas in pure form at the same temperature. Finally, the 

catalyst is cooled to its operating temperature in a flowing stream 

of the inert carrier gas in pure form. Reactivation is achieved by 

merely reheating the catalyst, in the presence of CO-containing 

recombining gases, to a temperature greater than its operating 

temperature and then recooling the catalyst to its operating 

temperature. NASA 

26 

METALLIC MATERIALS 

Includes physical, chemical, and mechanical properties of metals, 

e.g., corrosion; and metallurgy. 

N8&24814'# National Aeronautics and Space Administration. 

Langley Research Center. Hampton, Va. 

DIFFUSION OXYGEN BARRIER COATING AO2/MF A01 Patent 

Application 

J. UNNAM, inventor (to NASA) (Analytical Services and Materials, 

Inc.. Tabb. Va.) and R. K. CLARK, inventor (to NASA) 18 Mar. 

1986 15p 

(NASA-CASE-LAR-13474-1 -SB; NAS 1.71 :LAR-?3474-1-SB; 

US-PATENT-APPL-SN-840900) Avail: NTlS HC AOP/MF A01 

CSCL 11 F 

A method for coating a titanium panel or foil with aluminum 

and amorphous silicon to provide an oxygen barrier abrogating 

oxidation of the substrate metal is developed. The process is 

accomplished with known inexpensive procedures common in 

materials research laboratories. i.e., electron beam disposition and 

sputtering. The procedures are conductive to treating foil gage 

titanium and result in submicron layers which virtually add no weight 

to the titanium. There are no costly heating steps. The coatings 

blend with substrate titanium until separate mechanical properties 

are subsumed by those of the substrate eliminating cracking and 

spallation. This method appreciably increases the ability of titanium 

to perform in high thermal environments such as those witnessed 

on structures of space vehicles during re-entry. The novelty of 

this method is the ability to greatly enhance the operating envelope 

of titanium metal, particularly in thermal protection system 

applications. NASA 

EXPOSURE CONO~T~ONS~ 21 HOURS IN 41R 4t 900. I( 

E. IO 

45 

z 

P 

a 

W 

W 

d 

Eo NONE 41 CVD AI-CVD siop 41-31q 

TYPE Of COATING 

N86-26414'# 

Lewis Research Center, Cleveland, Ohio. 

HEAT TREATMENT FOR SUPERALLOY Patent Application 

F. H. HARF. inventor (to NASA) 

US-PATENT-APPL-SN-832296) Avail: NTlS HC AO2/MF A01 

CSCL 11F 

A cobalt-free nickel-base superalloy composed of in weight 

15 Cr - 5 Mo - 3.5 Ti - 4 AI - 0.07 (max) C - remainder Ni is 

given a modified heat treatment. With this heat treatment the 

cobalt-free alloy achieves certain of the mechanical properties of 

the corresponding cobalt-containing nickel-base superalloy at 1220 

F (650 C). Thus, strategic cobalt can be replaced with nickel in 

the superalloy. NASA 

National Aeronautics and Space Administration. 

24 Feb. 1986 11 p 

(NASA-CASE-LEW-14262-1; NAS 1.71:LEW-14261-1; 

N86-32550' National Aeronautics and Space Administration. 

Goddard Space Flight Center, Greenbelt, Md. 

METHOD OF COATING A SUBSTRATE WITH A RAPIDLY 

SOLIDIFIED METAL Patent 

H. P. CHU. inventor (to NASA) and C. L. STAUGAITIS. inventor 

(to NASA) 12 Nov. i985 5 p Filed 19 Mar.-l984 Supersedes 

N84-20670 (22 - 1 1, p 1632) 

(NASA-CASE-GSC-12880-1; US-PATENT-4,552,784: 

US-PATENT-APPL-SN-590925; US-PATENT-CLASS-427-1 92; 

US-PATENT-CLASS-427-1 91 US-PATENT-CLASS-427-421 : 

US-PATENT-CLASS-427-427) Avail: US Patent and Trademark 

Office - . . CSCL - - - - 11 F 

A method for coating a substrate with rapidly solidified metal 

is described which comprises spraying a mixture of rapidly solidified 

(RS) metal powder and small peening particles at high velocity 

against a substrate. The velocity is sufficient for the rapidly solidified 

metal powder and peening particles to impact the substrate and 

simultaneously bond the metal powder to the substrate. If the 

substrate is metallic, the method may provide the simultaneous 

mechanical working of the substrate surface. 

Official Gazette of the US. Patent and Trademark Office 

N86-32551 National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

APPARATUS FOR PRODUCTION OF ULTRAPURE 

AMORPHOUS METALS UTILIZING ACOUSTIC COOLING 

Patent 

M. C. LEE: inventor (to NASA) 19 Nov. 1985 8 p Filed 21 

Dec. 1982 Supersedes N83-19890 (21 - 10, p 1486) 

(NASA-CASE-NPO-15658-1; US-PATENT-4,553,917; 

US-PATENT-APPL-SN-451896; US-PATENT-CLASS-425-6; 

US-PATENT-CLASS-65-21.2 US-PATENT-CLASS-65-1 42; 

US-PATENT-CLASS-73-505; US-PATENT-CLASS-21 9-1 21 LE; 

US-PATENT-CLASS-21 9-1 21 LY; US-PATENT-CLASS-264-5) 

Avail: US Patent and Trademark Office CSCL 11 F 

7 
26 METALLIC MATERIALS 

Amorphous metals are produced by forming a molten unit of 

metal and deploying the unit into a bidirectional acoustical levitating 

field or by dropping the unit through a spheroidizing zone, a slow 

quenching zone, and a fast quenching zone in which the sphere 

is rapidly cooled by a bidirectional jet stream created in the standing 

acoustic wave field produced between a half cylindrical acoustic 

driver and a focal reflector or a curved driver and a reflector. The 

cooling rate can be further augmented first by a cryogenic liquid 

collar and secondly by a cryogenic liquid jacket surrounding a 

drop tower. The molten unit is quenched to an amorphous solid 

which can survive impact in a unit collector or is retrieved by a 

vacuum chuck. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-32556'# National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

ION-BEAM NITRIDING OF STEELS Patent Application 

J. SALIK. inventor (to NASA) and T. E. HUBBELL, JR.. inventor 

(to NASA) 29 Jan. 1986 11 p 

1.71:LEW-14104-2) Avail: NTlS HC AO2/MF A01 CSCL 11F 

A surface of a steel substrate is nitrided without external heating 

by exposing it to a beam of nitrogen ions under a low pressure. 

The pressure is much lower than that employed for ion-nitriding, 

and an ion source is used instead of a glow discharge. Both of 

these features reduce the introduction of impurities into the 

substrate surface. NASA 

(NASA-CASE-LEW-I 41 04-2; US-PATENT-APPL-SN-823713; NAS 

27 

NONMETALLIC MATERIALS 

Includes physical, chemical, and mechanical properties of plastics, 

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

materials. 

N86-24840'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

AROMATIC POLYMERS WITH IONIZING RADIATION Patent 

Application 

V. L. BELL, inventor (to NASA) and S. J. HAVENS, inventor (to 

PROCESS FOR CROSSLINKING METHYLENE-CONTAINING 

8 

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

29 P 

US-PATENT-APPL-SN-838654) Avail: NTlS HC A03/MF A01 

CSCL 11 B 

A process for crosslinking aromatic polymers containing 

radiation-sensitive methylene groups (-CH2-) by exposing the 

polymers to ionizing radiation thereby causing crosslinking of the 

polymers through the methylene groups is described. Crosslinked 

polymers are resistant to most organic solvents such as acetone, 

alcohols, hydrocarbons, methylene, chloride, chloroform, and other 

halogenated hydrocarbons.to common fuels and to hydraulic fluids 

in contrast to readily soluble uncrosslinked polymers. In addition, 

the degree of crosslinking of the polymers depends upon the 

percentage of the connecting groups which are methylene which 

ranges from 5 to 50% and preferably from 25 to 50% of the 

connecting groups, and is also controlled by the level of irradiation 

which ranges from 25 to 1000 Mrads and preferably from 25 to 

250 Mrads. The temperature of the reaction conditions ranges 

from 25 to 200C and preferably at or slightly above the glass 

transition temperature of the polymer. The crosslinked polymers 

are generally more resistant to degradation at elevated 

temperatures such as greater than 150C, have a reduced tendency 

to creep under load, and show no significant embrittlement of 

parts fabricated from the polymers. NASA 

11 Mar. 1986 

(NASA-CASE-LAR-13448-1; NAS 1.71 :LAR-I 3448-1 ; 

WEIGHT 

LOSS 

(v 

"IN AIR 

o rnmxwemyD6mmBa) 

TEMPERATURE rtl 

N86-24841'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

POLY(CARB0NATE-MIDE) POLYMER Patent Appllcatlon 

T. L. ST.CLAIR. inventor (to NASA), S. MAUDGAL, inventor (to 

NASA), and J. R. PRATT, inventor (to NASA) (Mississippi Univ. 

For Women., Columbus) 27 Feb. 1986 25 p 

US-PATENT-APPL-SN-834978) Avail: NTlS HC AO2/MF A01 

CSCL 11 B 

A novel series of polymers and copolymers based on a polymide 

backbone with the incorporation of carbonate moieties along the 

backbone is presented. The preparation process for the polymers 

and copolymers is disclosed together with a novel series of 

clinitrrliphany! ca_~na_!!ps ?~nd di=mi~rvliph~~y! c&=R&s. Thc 

novel polyners and copolymers exhibit high temperature capability 

and because of the carbonate unit, many exhibit a high degree of 

order and/or crystallinity. NASA 

(NASA-CASE-LAR-13292-1; NAS 1.71 :LAR-13292-1; 
27 NONMETALLIC MATERIALS 

N86-25477'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

PROCESS FOR CROSSLINKING AND EXTENDING 

CONJUGATED DIENE-CONTAINING POLYMERS Patent 

Appllcatlon 

V. L. BELL, inventor (to NASA) and S. J. HAVENS, inventor (to 

NASA) (PRC Kentron, Inc., Hampton, Va.) 

US-PATENT-APPL-SN-838655) Avail: NTlS HC AOP/MF A01 

CSCL 11 B 

A process using a Diels-Adler reaction which increases the 

molecular weight and/or crosslinks polymers by reacting the 

polymers with bisunsaturated dienophiles is develoepd. The 

polymer comprises at least 75% by weight based on the reaction 

product, has a molecular weight of at least 5000 and a plurality 

of conjugated 1 ,%diene systems incorporated into the molecular 

structure. A dienophile reaction with the conjugated 1,3-diene of 

the polymer is at least 1 % by weight based on the reaction product. 

Examples of the polymer include polyesters, polyamides, 

polyethers, polysulfones and copolymers. The bisunsaturated 

dienophiles may include bis-maleimide, bisnadimides. bis maleic 

and bis tumaric esters and amides. This method for expanding 

the molecular weight chains of the polymers, preferably 

thermoplastics, is advantageous for processing or fabricating 

thermoplastics. A low molecular weight thermoplastic is converted 

to a high molecular weight plastic having improved strength and 

toughness for use in the completed end use article. NASA 

11 Mar. 1986 17 p 

(NASA-CASE-LAR-13452-1; NAS 1.71 :LAR-13452-1; 

N86-25478'# 

Langley Research Center, Hampton. Va. 

TEMPERATURE SYSTEMS Patent Appllcatlon 

A. 0. EGLI. inventor (to NASA) (Kentron International, Inc., 

Hampton, Va.) and T. L. STCLAIR. inventor (to NASA) 18 Mar. 

1986 19p 

US-PATENT-APPL-SN-840816) Avail: NTlS HC AOP/MF A01 

CSCL 11 B 

A semi-2-interpenetrating network of improved qualities which 

is prepared by combining a linear polymer and a cross-linkable 

oligomer having identical repeating units is developed. Polymers 

have been combined in the past into interpentrating networks in 

order to gain useful properties from the combination of materials. 

However, previous semi-interpenetrating networks have only been 

formed using polymers having different repeating units. This method 

provides a semi-2-interpenetrating network of improved 

characteristics which is constructed by combining a linear polymer 

with a cross-linkable oligomer which has the same repeating unit 

as the linear polymer. The resulting interpenetrating network has 

improved poperties over prior networks because the polymer and 

oligomer with identical functionalities are mutually soluble and form 

one homogeneous phase. This eliminates the phase separation 

problems common to other networks. NASA 

National Aeronautics and Space Administration. 

SEMI-2-INTERPENETRATING NETWORKS OF HIGH 

(NASA-CASE-LAR-13450-1; NAS 1.71:lAR-13450-1~ 

RELATNE 

CkawNG 

289.C n 

N86-26434'# National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

OXIDATION PROTECTING COATINGS FOR POLYMERS Patent 

Appllcatlon 

J. S. SOVEY, inventor (to NASA), E. A. BANKS, inventor (to NASA), 

and M. J. MIRTICH, inventor (to NASA) 27 Feb. 1986 12 p 

Sponsored by NASA 

US-PATENT-APPL-SN-834977) Avail: NTlS HC AOP/MF A01 

CSCL 11 B 

A polymeric substrate is coated with a metal oxide film to 

provide oxidation protection in low Earth orbital environments. The 

film contains about four volume percent polymer to provide 

flexibility. NASA 

(NASA-CASE-LEW-14072-3; NAS 1.71 :LEW-14072-3; 

14 

N86-26435'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton. Va. 

POLYETHER-POLYESTER GRAFT COPOLYMER Patent 

Application 

V. L. BELL, inventor (to NASA) 24 Apr. 1986 20 p Sponsored 

by NASA 

US-PATENT-APPL-SN-855879) Avail: NTlS HC AO2/MF A01 

CSCL 11 B 

This invention relates to a polyether graft copolymer having 

improved solvent resistance and crystalline thermally reversible 

crosslinks. The copolymer is prepared by a novel process of anionic 

copolymerization. The polymers of this invention exhibit good 

solvent resistance and are well suited for commercial aircraft parts. 

Previous aromatic polyethers. also well known as polyphenylene 

oxides, have certain deficiencies which detract from their 

usefulness. These well known commercial polymers are often 

soluble in common solvents including the halocarbon and aromatic 

hydrocarbon types of paint thinners and removers. This limitation 

prevents the use of these polyethers in structural articles that 

require frequent painting. In addition, the most popular commercially 

c\*ai!able ;=!yether is a very high meltifig p:as%c. This iiiakes it 

considerably more difficult to fabricate finished parts from this 

material. The present invention solves these problems by providing 

an aromatic polyether graft copolymer with improved solvent 

resistance and crystalline thermally reversible crosslinks. The graft 

copolymer is formed by converting the carboxyl groups of a 

carboxylated polyphenylene oxide polymer to ionic carbonyl groups 

in a suitable solvent, reacting pivalolactone with the dissolved 

(NASA-CASE-LAR-13447-1; NAS 1.71:LAR-13447-1; 
27 NONMETALLIC MATERIALS 

polymer, and adding acid to the solution to produce the graft 

copolymer. NASA 

N86-27450' 

Langley Research Center, Hampton, Va. 

GROUPS Patent 

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

6 May 1986 Filed 23 May 1984 Supersedes N84-28987 

(22 - 19, p 2996) Sponsored by NASA. Langley Research 

Center 

National Aeronautics and Space Administration. 

SULFONE-ESTER POLYMERS CONTAINING PENDENT ETHYNL 

8 p 

(NASA-CASE-LAR-13316-1: US-PATENT-4,587,312; 

US-PATENT-APPL-SN-613139; US-PATENT-CLASS-525-535; 

US-PATENT-CLASS-260-544P; US-PATENT-CLASS-525-534; 

US-PATENT-CLASS-526-285; US-PATENT-CLASS-528-1 71 ; 

US-PATENT-CLASS-528-1 74; US-PATENT-CLASS-528-1 76) 

Avail: US Patent and Trademark Office CSCL 11 B 

Sulfone ester polymers containing pendent ethnyl groups and 

a direct and multistep process for their preparation are disclosed. 

The process involves the conversion of a pendent bromo group 

to the ethynyl group while the direct route involves reacting 

hydroxy-terminated sulfone oligomer or polymers with a 

stoichiometric amount of 5(4-ethynyl phenoxy)isophthaloyl chloride. 

The 5(4-ethynyl phenoxy)isophthaloyl chloride synthesis procedures 

are also disclosed. 

Official Gazette of the U. S. Patent and Trademark Office 

N86-27451 National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

TOUGHENING REINFORCED EPOXY COMPOSITES WITH 

BROMINATED POLYMERIC ADDITIVES Patent 

2. NIR. Inventor (to NASA) (National Academy of Sciences - National Research Council, Washington, D. C.) and W. J. GILWEE, 

JR., Inventor (to NASA) 15 Aug. 1985 13 p 

(NASA-CASE-ARC-I 1427-2; US-PATENT-4.588,778; 

US-PATENT-APPL-SN-765-980; US-PATENT-CLASS-525-1 1 5; 

US-PATENT-CLASS-525-1 19 US-PATENT-CLASS-525-1 22; 

US-PATENT-CLASS-525-1 08; US-PATENT-CLASS-523-434; 

US-PATENT-CLASS-523-445; US-PATENT-CLASS-523-461) 

Avail: US Patent and Trademark Office CSCL 11 B 

Cured plyfunctional eyxy resins including 

tris(hydroxypheny1)methane triglycidyl ether are toughened by 

addition of polybrominated polymeric additives having an EE below 

1500 to the pre-cure composition. Carboxy-terminated 

butadiene-acrylonitrile rubber is optionally present in the pre-cure 

mixture as such or as a pre-formed copolymer with other reactants. 

Reinforced composites, particularly carbon-reinforced composites, 

of these resins are disclosed and shown to have improved 

toughness. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-29039' National Aeronautics and Space Adwinistration. 

Langley Research Center, Hampton. Va. 

PROCESS FOR PREPARING ESSENTIALLY COLORLESS 

POLYIMIDE FILM CONTAINING PHENOXY-LINKED DIAMINES 

Patent 

A. K. STCLAIR and T. L. STCLAIR 17 Jun. 1986 8 p Filed 

23 Aug. 1984 Supersedes N85-20128 (23 - 11, p 161 1) 

(NASA-CASE-LAR-13353-1: US-PATENT-4,595,548; 

US-PATENT-APPL-SN-643524; US-PATENT-CLASS-264-236 

US-PATENT-CLASS-264-204: US-PATENT-CLASS-264-216; 

US-PATENT-CLASS-264-347; US-PATENT-CLASS-528-222; 

US-PATENT-CLASS-528-341 ; US-PATENT-CLASS-528-1 83) 

Avail: US Patent and Trademark Office CSCL 11C 

A polyimide film that is approximately 90% transparent at 500 

nm, useful for thermal protective coatings and solar cells, and the 

processes for preparing the same by thermal and chemical 

conversion are disclosed. An essential feature for achieving 

maximum optical transparency films requires utilizing recrystallized 

and/or sublimated specific aromatic diamines and dianhydride 

monomers and introducing phenoxy or thiophenyl separator groups 

and isomeric m,m' or o,p'-oriented diamines into the polymer 

molecular structure. The incorporation of these groups in the 

polymer structure serves to separate the chromaphoric centers 

and reduce the formation of inter-chain and intra-chain charge 

transfer complexes which normally cause absorptions in the 

UV-visible range. The films may be obtained by hand, brushing, 

casting, or spraying a layer of polyamic acid solutions onto a 

surface and thermally converting the applied layer to the polyimide, 

or the polyamic acid solution can be chemically converted to the 

polyimide, subsequentially dissolved in an organic solvent, and 

applied as a polyimide film layer with the solvent therein thermally 

removed. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-31726'# National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

AMINE TERMINATED BlSASPARTlMlDE POLYMER Patent 

D. KUMAR, inventor (to NASA) (National Academy of Sciences - National Research Council, Washington, D. C.), G. M. FOHLEN, 

inventor (to NASA), and J. A. PARKER, inventor (to NASA) 15 

Jul. 1986 8 p Filed: May 31, 1985 

(NASA-CASE-ARC-1 1421 -2; US-PATENT-4,600,769; 

US-PATENT-APPL-SN-7327EQ; I-IS-PA.TENT-CLA.S~~E~83'2; 

US-PATENT-CLASS-428-473.5; US-PATENT-CLASS-528-1 70; 

US-PATENT-CLASS-528-220; US-PATENT-CLASS-528-321 )

Avail: US Patent and Trademark Office 

Novel amine terminated bisaspartimides are prepared by a 

Michael-type reaction of an aromatic bismalteimide and an aromatic 

diamine in an aprotic solvent. These bisaspartimides are thermally 

polymerized to yield tough, resinous polymers cross-lined through 

-NH- groups. Such polymers are useful in applications requiring 

materials with resistance to change at elevated temperatures, e.g., 

as lightweight laminates with graphite cloth, molding material 

prepregs, adhesives and insulating material. 

Official Gazette of the U.S. Patent and Trademark Office 

CSCL 11 B 

N86-31727' National Aeronautics and Space Administration. 

Langley Research Center, Hampton. Va. 

PROCESS FOR PREPARING HIGHLY OPTICALLY 

TRANSPARENT/COLORLESS AROMATIC POLYIMIDE FILM 

Patent 

10 
28 PROPELLANTS AND FUELS 

A. K. ST.CLAIR, inventor (to NASA) and T. L. ST.CLAIR, inventor 

(to NASA) 29 Jul. 1986 9 p Filed 23 Aug. 1984 Supersedes 

N85-21360 (23 - 12, P 1811) 

(NASA-CASE-LAR-13351-1; US-PATENT-4,603,061 ; 

US-PATENT-APPL-SN-643589; US-PATENT-CLASS-427-1 62; 

US-PATENT-CLASS-264-21 2; US-PATENT-CLASS-264-236; 

US-PATENT-CLASS-427-1 64; US-PATENT-CLASS-427-1 65; 

US-PATENT-CLASS-428-336; US-PATENT-CLASS-428-473.5) 

Avail: US Patent and Trademark Office CSCL 11 B 

An aromatic condensation polyimide film that is approximately 

90% transparent at 500 nm, useful for thermal protective coatings 

and the process for preparing same are disclosed. A feature to 

achieve maximum optical transparency films requires the utilization 

of recrystallized and/or sublimated specific aromatic diamines and 

dianhydride monomers and the introduction of bulky electron 

withdrawing groups and separator groups into the polymer 

molecular structure. 

Official Gazette of the US. Patent and Trademark Office 

N86-32568'# National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

FIRE RESISTANT POLYAMIDE BASED ON 

1-(DIORGANOOXYPHOSPH0NYL)METHY L-2,4- AND 

-2,6DIAMINO BENZENE Patent 

J. A. MIKROYANNIDIS, inventor (to NASA) and D. A. KOURTIDES, 

inventor (to NASA) 22 Jul. 1986 8 p Filed 16 Aug. 1984 

Supersedes N85-21362 (24 - 11. p 1872) 

(NASA-CASE-ARC-1 1512-2; US-PATENT-4,602,081; 

US-PATENT-CLASS-528-337; US-PATENT-CLASS-528-336; 

US-PATENT-CLASS-528340; US-PATENT-CLASS-528-347; 

US-PATENT-CLASS-564-1 5; US-PATENT-CLASS-568-1 4; 

US-PATENT-APPL-SN-641153) Avail: US Patent and Trademark 

Office CSCL llB 

1 -(Diorganooxyphosphonyl)methyl2,4- and-2.6diamino benzenes 

are reacted with polyacylhalides and optionally comonomers to 

produce polyamides which have desirable heat and fire resistance 

properties. These polymers are used to form fibers and fabrics 

where fire resistance properties are important, e.g., aircraft 

equipment and structures. 

Official Gazette of the US. Patent and Trademark Office 

N86-32569' National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

APPARATUS FOR PRODUCING OXIDATION PROTECTION 

COATINGS FOR POLYMERS Patent 

M. J. MIRTICH, inventor (to NASA), J. S. SOVEY, inventor (to 

NASA), and A. BANKS, inventor (to NASA) 5 Aug. 1986 7 p 

Division of US-Patent-Appl-SN-649330, 14 Sep. 1984. 

US-Patent-4,560,577 Filed 31 Jul. 1985 Supersedes N86-19463 

(24 - 10, p 1560) 

(NASA-CASE-LEW-14072-2; US-PATENT-4.604.1 81 ; 

VS-?.ATENT-.4P?L-SN-761235; VS-PATENT-GIASS-294-298; 

US-PATENT-CLASS-204-1 92C US-PATENT-CLASS-204-1 92D) 

Avail: US Patent and Trademark Office CSCL 11 B 

A polymeric substrate is coated with a metal oxide film to 

provide oxidation protection in low Earth orbital environments. The 

film contains about 4 volume percent polymer to provide flexibility. 

A coil of polymer materials moves through an ion beam as it is 

fed between reels. The ion beam first cleans the polymer material 

surface and then sputters the film material from a target onto this 

surface. 

Official Gazette of the US. Patent and Trademark Office 

N86-32570'# National Aeronautics and Space Administration. 

Goddard Space Flight Center, Greenbelt, Md. 

CELLULAR THERMOSETTING FLUOROPOLYMERS AND 

PROCESS FOR MAKING THEM Patent Application 

S. Y. LEE 29 May 1986 12 p 

1.71:GSC-13008-1) Avail: NTlS HC AO2/MF A01 CSCL llB 

Thermosetting fluoropolymer foams are made by mixing fluid 

form thermosetting fluoropolymer components having a substantial 

fluorine content, placing the mixture in a pressure tight chamber, 

filling the chamber with a gas, at relatively low pressure, that is 

unreactive with the fluoropolymer components, allowing the mixture 

to gel, removing the gelled fluoropolymer from the chamber and 

thereafter heating the fluoropolymer at a relatively low temperature 

to simultaneously cure and foam the fluoropolymer. The resulting 

fluoropolymer product is closed celled with the cells storing the 

gas employed for foaming. The fluoropolymer resins employed 

may be any thermosetting fluoropolymer including fluoroepoxies. 

fluoropolyurethanes and fluoroacrylates. NASA 

(NASA-CASE-GSC-13008-1; US-PATENT-APPL-SN-867987; NAS 

PROPELLANTS AND FUELS 

Includes rocket propellants, igniters, and oxidizers; storage and 

handling; and aircraft fuels. 

N86-23744'# National Aeronautics and Space Administration. 

John F. Kennedy Space Center, Cocoa Beach, Fla. 

LIQUID HYDROGEN POLYGENERATION SYSTEM AND 

PROCESS Patent Appllcatlon 

P. A. MINDERMAN, G. P. GUTKOWSKI, L. MANFREDI, J. V. KING, 

and F. S. HOWARD, inventors (to NASA) 15 Nov. 1985 23 p 

(NASA-CASE-KSC-11304-2: NAS 1.71 :KSC-11304-2 

US-PATENT-APPL-SN-789713) 

CSCL 21 I 

Avail: NTlS HC AO2/MF A01 

An integrated polygeneration system and process is disclosed 

for generating liquid hydrogen as a main energy product for use 

as a propellant for space vehicles. Secondary energy products 

and commodities for supporting a space center complex and 

launching of the space vehicle includes the production of electrical 

and thermal energy and gaseous nitrogen. The integrated process 

includes a coal gasification and gas cleanup system, a combined 

cycle power generation system, a hydrogen production and 

liquefaction system and a air separation system. A medium BTU 

gas is produced by the coal gasification system. Steam also 

11 
31 ENGINEERING (GENERAL) 

produced in the coal gasification process is delivered to a steam 

turbine in the combined cycle power generation system. NASA 

a 

N86-24867'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

DEPLOYABLE GEODESIC TRUSS STRUCTURE A01 Patent 

Application 

M. M. MIKULAS, JR., inventor (to NASA), M. D. RHODES, inventor 

(to NASA). and J. W. SIMONTON, inventor (to NASA) 20 Feb. 

is86 1511 

(NASA-CASE-LAR-13113-1; NAS 1.71 :LAR-13113-1; 

US-PATENT-APPL-SN-831371) Avail: NTlS HC AO2/MF A01 

CSCL 138 

A deployable geodesic truss structure which can be deployed 

from a stowed state to an erected state is described. The truss 

structure includes a series of bays, each bay having sets of battens 

connected by longitudinal cross members which give the bay its 

axial and torsional stiffness. The cross members are hinged at 

their mid point by a joint so that the cross members are foldable 

for deployment or collapsing. The bays are deployed and stabilized 

by actuator means connected between the mid point pints of the 

cross members. Hinged longerons may be provided to also connect 

the sets of battens and to collapse for stowing with the rest of 

the truss structure. The truss structure has the capability of serving 

a structural function even when only partly deployed. NASA 

31 

ENGINEERING (GENERAL) 

Includes vacuum technology; control engineering; display 

engineering; and cryogenics. 

N86-23750'# National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

METHOD FOR MACHINING HOLES IN COMPOSITE MATERIALS 

Patent Application 

J. M. CLEMONS, F. E. LEDBETTER, J. G. DANIELS, and B. G. 

PENN, inventors (to NASA) 3 Dec. 1985 9 p 

US-PATENT-APPL-SN-804039) Avail: NTlS HC A02/MF A01 

CSCL 13H 

A method for boring well defined holes in a composite material 

such as graphitelepoxy is discussed. A slurry of silicon carbide 

powder and water is projected onto a work area of the composite 

material in which a hole is to be bored with a conventional drill 

bit. The silicon carbide powder and water slurry allow the drill bit, 

while experiencing only normal wear, to bore smooth, cylindrical 

holes in the composite material. NASA 

(NASA-CASE-MFS-28044-1; NAS 1.71 :MFS-28044-1; 

N86-27467'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

OXYGEN CHEMISORPTION CRYOGENIC REFRIGERATOR 

Patent Application 

J. A. JONES, inventor (to NASA) (Jet Propulsion Lab., California 

Inst. of Tech., Pasadena) 24 Apr. 1986 15 p Sponsored by 

NASA 

US-PATENT-APPL-SN-855982) Avail: NTlS HC AO2/MF A01 

CSCL 131 

The present invention relates to a chemisorption compressor 

cryogenic refrigerator which employs oxygen to provide cooling at 

60 K to 100 K. The invention includes dual vessels containing an 

oxygen absorbent material, alternately heated and cooled to provide 

a continuous flow of high pressure oxygen, multiple heat 

exchangers for precooling the oxygen, a Joule-Thomson expansion 

valve system for expanding the oxygen to partially liquefy it and a 

liquid oxygen collection vessel. The primary novelty of the present 

invention lies in the provision of a refrigeration system which makes 

(NASA-CASE-NPO-16734-1-CU; NAS 1.71 :NPO-l6734-1-CU; 

12 
32 COMMUNICATIONS 

use of reversible chemical reactions with oxygen to provide cooling 

at 60 K to 100 K. NASA 

US-PATENT-CLASS-31 3-1 07; US-PATENT-CLASS-427-39) 

Avail: US Patent and Trademark Office CSCL 13H 

A very thin layer of highly textured carbon is applied to a 

copper surface by a triode sputtering process. A carbon target 

and a copper substrate are simultaneously exposed to an argon 

plasma in a vacuum chamber. The resulting carbon surface is 

characterized by a dense, random array of needle like spires or 

peaks which extend perpendicularly from the copper surface. The 

coated copper is especially useful for electrode plates in multistage 

depressed collectors. 

Official Gazette of the U.S. Patent and Trademark Office 

, '4 

20 

16 

N86-29055' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

ANGULAR MEASUREMENT SYSTEM Patent 

J. R. CURRIE and R. R. KISSEL 10 Jun. 1986 6 p Filed 3 

Oct. 1984 Supersedes N85-20298 (23 - 11, p 1635) 

(NASA-CASE-MFS-25825-1; US-PATENT-4,594,540 

US-PATENT-APPL-SN-657309; US-PATENT-CLASS31 8-661 ; 

US-PATENT-CLASS-340-347SY; US-PATENT-CLASS-340-347CC; 

US-PATENT-CLASS-31 8-636; US-PATENT-CLASS-31 8-605) 

Avail: US Patent and Trademark Office CSCL 138 

A system for the measurement of shaft angles is disclosed 

wherein a synchro resolver is sequentially pulsed, and alternately, 

a sine and then a cosine representative voltage output of it are 

sampled. Two like type, sine or cosine, succeeding outputs (V 

sub S1, V sub S2) are averaged and algebraically related to the 

opposite type output pulse (V sub c) occurring between the 

averaged pulses to provide a precise indication of the angle of a 

shaft coupled to the resolver at the instant of the Occurrence of 

the intermediately occurring pulse (V sub c). 

Official Gazette of the U.S. Patent and Trademark Office 

N86-32589'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

REMOTELY CONTROLLABLE MIXING SYSTEM Patent 

Application 

R. R. BELEW, inventor (to NASA) 

1.71:MFS-28153-1) Avail: NTlS HC AOZ/MF A01 CSCL 13H 

This invention relates to a remotely controllable mixing system 

in which a plurality of mixing assemblies are arranged in an annular 

configuration, and wherein each assembly employs a central 

chamber and two outer, upper and lower chambers. Valves are 

positioned between chambers, and these valves for a given mixing 

assembly are operated by upper and lower control rotors, which 

in turn are driven by upper and lower drive rotors. Additionally, a 

hoop is compressed around upper control rotors and a hoop is 

compressed around lower control rotors to thus insure constant 

frictional engagement between all control rotors and drive rotors. 

The drive rollers are driven by a motor. NASA 

18 Jun. 1986 19 p 

(NASA-CASE-MFS-28153-1; US-PATENT-APPL-SN-875891; NAS 

iY86-32587' National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

TEXTURED CARBON SURFACES ON COPPER BY SPUTTERING 

Patent 

32 

COMMUNICATIONS 

A. N. CURAEN, inventor [to NASA): K. A. JENSEN, inventor [to 

NASA), and R. F. ROMAN, inventor (to NASA) 19 Aug. 1986 

8 p Filed 10 Oct. 1984 Supersedes N85-20151 (23 - 11. p 

161 5) 

US-PATENT-APPL-SN-659475; US-PATENT-CLASS-31 5-5.38; N86-24879'# National Aeronautics and Space Administration. 

US-PATENT-CLASS-204-1 92C; US-PATENT-CLASS-204-1 92D; Lyndon B. Johnson Space Center, Houston, Tex. 

US-PATENT-CLASS-204-298; US-PATENT-CLASS31 3-1 06; METHOD AND APPARATUS FOR MEASURING DISTANCE 

Includes land and global communications; communications theory; 

and optical communications. 

(NASA-CASE-LEW-14130-1; US-PATENT-4,607,193; 

~ 

13 
32 COMMUNICATIONS 

n 

7 

74 

c. 

Patent Application of the material according to a derivation of the Raleigh - Jeans 

C. L. LICHTENBERG, inventor (to NASA), P. W. SHORES, inventor approximation for an ideal system free from all uncorrelated 

(to NASA), and H. S. KOBAYASHI. inventor (to NASA) 20 Feb. radiation. NASA 

1986 34 p 

US-PATENT-APPL-SN-831183) Avail: NTlS HC A03/MF A01 

CSCL 171 

The invention employs a continuous wave radar technique and 

apparatus which can be used as a distance measuring system in 

the presence of background clutter, by utilizing small passive 

transponders. A first continuous electromagnetic wave signal S 

sub 1 at a first frequency f sub 1 is transmitted from a first 

location. A transponder carried by a target object positioned at a 

second (remote) location receives the transmitted signal, 

phase-coherently divides the f sub 1 frequency and phase therefore, 

and re-transmits the transmitted signal as a second continous 

electromagnet wave signal S sub 2 at a lower second frequency f 

sub 2 which is a subharmonic of f sub 1. The re-transmitted 

signal is received at the first location where a measurement of 

the phase difference is made between the signals S sub 1 and S 

sub 2, such measurement being indicative of the distance between 

the first and second locations. In a preferred embodiment, the 

transponder is a passive divide-by-two parametric oscillator 

employing the energy from the transmitted signal S sub 1 incident 

thereon to generate the re-transmitted signal S sub 2. NASA 

(NASA-CASE-MS,C-20912-1; NAS 1.71 :MSC-20912-1; 

N86-27513’ National Aeronautics and Space Administration. John 

F. Kennedy Space Center, Cocoa Beach, Fla. 

METHOD AND APPARATUS FOR OPERATING ON COMPANDED 

PCM VOICE DATA Patent 

F. BYRNE. inventor (to NASA) 13 May 1986 8 p Filed 28 

Sep. 1984 Supersedes N85-29120 (23 - 18, p 3089) Sponsored 

by NASA. Kennedy Space Center 

(NASA-CASE-KSC-11285-1; US-PATENT-4,588,986; 

US-PATENT-APPL-SN-655601; US-PATENT-CLASS-340-347DD; 

US-PATENT-CLASS-365-768; US-PATENT-CLASS-I 79-1 8BC) 

Avail: US Patent and Trademark Office CSCL 178 

The method and apparatus constructed in accordance with 

this invention permits a plurality of parties to speak to each other 

on a conference line with a minimum of interference. The apparatus 

digitizes audio signals. Each of the parties has an audio transmitter 

and receiver provided for transmitting and receiving audio signals. 

The audio signals are converted to a PCM companded eight-bit 

parallel signal followed by a conversion to a serial signal for 

transmitting to a remote location and then reconverting each of 

the companded signals to a firsteight-bit parallel signal. The 

eight-bit parallel signal is fed to one input of a pre-programmed 

ROM. This eight-bit signal provides one-half of a sixteen-bit address 

of a lookup ROM. The other half of the sixteen-bit ROM address 

is supplied by another suscriber over an identical circuit. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-24880’# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

MEASUREMENT APPARATION AND PROCEDURE FOR THE 

DETERMINATION OF SURFACE EMISSIVITIES Patent 

Application 

H. J. C. BLUME, inventor (to NASA) 

US-PATENT-APPL-SN-804040) Avail: NTlS HC A03/MF A01 

CSCL 20N 

3 Dec. 1985 27 p 

(NASA-CASE-LAR-13455-1; NAS 1.71:LAR-13455-1; 

A method and apparatus for independently determining the 

is particularly useful in the design of large deployable space 

antennas employing mesh membrane surfaces. The system is a 

closed one with respect to unwanted or uncorrelated radiation 

outside the system. The present embodiment comprises a 

radiometer connected to a horn antenna, a test section sealed to 

the horn antenna and a cryogenically cooled matched load 

(cryoload) exposed to the interior of the system. The material is 

enclosed in a convection test chamber within the test section, 

heated by convection within a test chamber and allowed to radiate 

within the system such that a component of the radiation energy 

of the material is measured by the radiometer in terms of brightness 

temperature. A matched load serves as the stabilized source of 

uncorrelated radiation within the system. The actual physical 

temperature of the material is also measured during the heating 

process with a thermometer. The difference in brightness 

temperature over a selected period of time when divided by the 

physical temperature over the same period of time is the emissivity 

electromagnetic surface emissivity of a material is developed, which 3- vI.l.. II 1- *a 

_i 

_...- .... , 1 3G 

14 
33 ELECTRONICS AND ELECTRICAL ENGINEERING 

which has a better combination of resolution, brightness, contrast 

ratio and fabrication simplicity than any of the prior designs. 

NASA 

33 

ELECTRONICS AND ELECTRICAL ENGINEERING 

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

tunnel diodes and transistors; microminiaturization; and integrated 

circuity. 

N86-24908'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

FLOATING EMITTER SOLAR CELL JUNCTION TRANSISTOR 

Patent Appllcatlon 

C. T. SAH, inventor (to NASA) and L. J. CHENG, inventor (to 

NASA) 11 Mar. 1986 26 p 

(Contract NAS7-919) 

US-PATENT-APPL-SN-838648) Avail: NTlS HC AO3/MF A01 

CSCL 09A 

A front surface contact floating emitter solar cell transistor is 

provided in a semiconductor body (n-type), in which floating emitter 

sections (p-type) are diffused or implanted in the front surface. 

Between the emitter sections, a further section is diffused or 

implanted in the front surface, but isolated from the floating emitter 

sections, for use either as a base contact to the n-type 

(NASA-CASE-NPO-16467-1-CU; NAS 1.71 :NPO-16467-1-CU; 

semiconductor body, in which case the section is doped n+. or 

as a collector for the adjacent emitter sections, in which case the 

section is doped p+. In the first case, the structure is diffused or 

implanted p+ on the back in a section that serves as a collector, 

and in the second case the structure is diffused or implanted n+ 

all across the back to serve as a base contact. In either case, 

the semiconductor material on the back may be a starting substrate 

of suitably doped semiconductor material. A major advantage is 

that no wafer edge groove is necessary since the floating emitter 

solar cell transistors are isolated from saw damge. so long as a 

cut is not made through the well. NASA 

N86-24909'# 

Langley Research Center, Hampton, Va. 

Patent Application 

J. E. ROBERTSON, inventor (to NASA) 3 Dec. 1985 

US-PATENT-APPL-SN-804196) Avail: NTlS HC A02/MF A01 

CSCL 09A 

This invention relates to a flat-panel, electroluminescent display 

capable of achieving full color and is particularly useful in achieving 

a bright display with high resolution. The invention uses red, green 

and blue phosphors in two layers separated by layers of insulating 

material and layers of electrodes that are used to excite the 

electrodes. In operation, the display is addressed by supplying 

sufficient voltage between selected electrodes. This places an 

electric field across the phosphor at each picture element located 

between the overlap of the selected electrodes, causing the 

phosphor to emit light at this location. The display can be addressed 

in line-at-a-time fashion in rapid enough sequence to display 

information at standard TV frame rates. The novelty of this invention 

resides in the combining of a partial side-by-side design with a 

partial stacked layer design to produce a flat-panel, full-color display 

National Aeronautics and Space Administration. 

FLAT-PANEL, FULL-COLOR ELECTROLUMINESCENT DISPLAY 

13 p (NASA-CASE-LAR-13407-1; NAS 1.71:LAR-13407-1; 

0 

N86-32624' National Aeronautics and Space Administration. 

Goddard Space Flight Center, Greenbelt, Md. 

TEMPERATURE SENSITIVE OSCILLATOR Patent 

L. L. KLEINBERG, inventor (to NASA) 29 Jul. 1986 7 p Filed 

25 Apr. 1985 Supersedes N85-30201 (23 - 19, p 3258) 

(NASA-CASE-GSC-12958-1; US-PATENT-4.603.306; 

US-PATENT-APPL-SN-72703$ US-PATENT-CLASS-331-6666; 

US-PATENT-CLASS-331 -1 08D: US-PATENT-CLASS-331 -1 16R: 

US-PATENT-CLASS-374-1 83) ' Avail: US Patent and Trademark 

Office CSCL09A 

An oscillator circuit for sensing and indicating temperature by 

changing oscillator frequency with temperature comprises a 

programmable operational amplifier which is operated on the roll-off 

portion of its gain versus frequency curve and has its output directly 

connected to the inverting input to place the amplifier in a follower 

configuration. Its output is also connected to the non-inverting 

input by a capacitor with a crystal or other tuned circuit also 

being connected to the non-inverting input. A resistor is connected 

to the program input of the amplifier to produce a given set cunent 

at a given temperature, the set current varying with temperature. 

As the set current changes, the gain-bandwidth of the amplifier 

changes and, in turn, the reflected capacitance across the crystal 

changes, thereby providing the desired change in oscillator 

frequency by pulling the crystal. There is no requirement that a 

crystal employed with this circuit display either a linear frequency 

change with temperature or a substantial frequency change with 

temperature. 

Official Gazette of the U.S. Patent and Trademark Office 

15 
33 ELECTRONICS AND ELECTRICAL ENGINEERING 

N86-32626'# 

Langley Research Center, Hampton, Va. 

ARC LAMP POWER SUPPLY Patent Application 

B. D. LEIGHTY, inventor (to NASA) 26 Jun. 1986 11 p 

1.71:LAR-13202-1) Avail: NTlS HC AOZ/MF A01 CSCL 09A 

A power supply is provided for an arc discharge lamp which 

includes a relatively low voltage high current power supply section 

and a high voltage starter circuit. The low voltage section includes 

a transformer, rectiier, variable resistor and a bank of capacitors, 

while the starter circuit comprises a plurality of diodes and 

capacitors connected as a Cockcroft-Walton multiplier. The starting 

circuit is effectively bypassed when the lamp arc is established 

and serves to automatically provide a high starting voltage to 

re-strike the lamp arc if the arc is extinguished by a power 

interruption. NASA 

National Aeronautics and Space Administration. 

(NASA-CASE-LAR-13202-1; US-PATENT-APPL-SN-879758; NAS 

.) 

./l.<l?l 

i I \-,,'::; 

" +i'J 

! 

.. <' 

5: 

'"' , .< ' I &<? ' 

34 

FLUID MECHANICS AND HEAT TRANSFER 

Includes boundary layers; hydrodynamics; fluidics; mass transfer; 

and ablation cooling. 

N86-24935*# 

Ames Research Center, Moffett Field, Calif. 

LIQUID SEEDING ATOMIZER Patent Application 

H. L. B. SEEGMILLER, inventor (to NASA) 31 Mar. 1986 

US-PATENT-APPL-SN-846428) Avail: NTlS HC AO2/MF A01 

CSCL 20D 

An atomizer for a liquid having an air supply is described. 

Liquid supply tubes extend longitudinally along the air supply tube. 

The air supply tube has at least one air orifice extending from an 

inner surface of the tube through the tube. The liquid supply tubes 

are positioned on either side of the air orifices and the liquid 

tubes are sealed to the air supply tube. The liquid supply tubes 

with facing liquid orifices are positioned adjacent to each of the 

air orifices. The liquid supply tubes are laterally spaced apart at 

the liquid orifices at a distance less than the diameter nf the air 

orifices to enable a beneficial venturi effect when the atomizer is 

in operation. NASA 

National Aeronautics and Space Administration. 

12 p (NASA-CASE-ARC-11631-1; NAS 1.71:ARC-11631-1; 

I2 18 

F' I 7 

N86-26575'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

ACTIVE CONTROL OF BOUNDARY LAYER TRANSITION AND 

TURBULENCE Patent Application 

L. MAESTRELLO, inventor (to NASA) 11 Mar. 1986 13 p 

US-PATENT-APPL-SN-838649) Avail: NTlS HC AO2/MF A01 

CSCL 20D 

The invention is a system and method for controlling boundary 

layer flow such that flow separation can be delayed and skin 

friction drag can be reduced. The invention consists of heater 

elements used to trigger turbulent flow and audio speakers used 

to suppress turbulent oscillations. By inducing turbulent oscillations 

into the fiow in a region of positive pressure gradient, pressure 

patterns became more regular. The suppression of these patterns 

can be accomplished by imposing an out-of-phase suppressing 

wave. This wave is the audio output generated by a feedback 

amplifier using inputs from a hot-wire anemometer reading 

downstream turbulence. The novel features of the present invention 

are the tripping of boundary layer flow in a region of positive 

pressure gradient and the cooperative use of the feedback means 

to control turbulence. The result is a significant reduc!ion in drag 

and separation problems. NASA 

(NASA-CASE-LAR-13532-1; NAS 1.71:LAR-13532-1; 

N86-27593' National Aeronautics and Space Administration. 

Lyndon B. Johnson Space Center, Houston, Tex. 

MULE-LEG iiEAT PiPE E'v'APfrEiATOFi Paieni 

J. P. ALARIO (Grumman Aerospace Corp., Bethpage. N.Y.) and 

R. A. HASLETT, inventors (to NASA) 22 Apr. 1986 7 p Filed 

31 May 1984 Supersedes N84-32748 (22 - 22, p 3592) Sponsored 

by NASA. Johnson Space Center 

(NASA-CASE-MSC-20812-1; US-PATENT-4,583,587; 

US-PATENT-APPL-SN-616002; US-PATENT-CLASS-1 65-1 04.26; 

US-PATENT-CLASS-1 22-366; US-PATNET-CLASS1 65-41 ; 

US-PATENT-CUSS-1 65-1 04.1 4) 

Trademark Office CSCL 20D 

A multileg heat pipe evaporator facilitates the use and 

application of a monogroove heat pipe by providing an evaporation 

section which is compact in area and structurally more compatible 

with certain heat exchangers or heat input apparatus. The 

evaporation section of a monogroove heat pipe is formed by a 

series of parallel legs having a liquid and a vapor channel and a 

communicating capillary slot therebetween. The liquid and vapor 

channels and interconnecting capillary slots of the evaporating 

section are connected to the condensing section of the heat Pipe 

by a manifold connecting liquid and vapor channels of the parallel 

Avail: US Patent and 

16 
35 INSTRUMENTATION AND PHOTOGRAPHY 

evaporation section legs with the corresponding liquid and vapor 

channels of the condensing seCtiOn. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-32661'# National Aeronautics and Space Administration. 

Lyndon B. Johnson Space Center, Houston, Tex. 

MONOGROOVE COLD PLATE Patent Appllcatlon 

F. EDELSTEIN, inventor (to NASA) (Grumman Aerospace Cop., 

Bethpage. N.Y.) and R. F. BROWN, inventor (to NASA) 18 Jun. 

1986 14 p Sponsored by NASA 

1.71:MSC-20946-1) Avail: NTlS HC A02/MF A01 CSCL 20D 

(NASA-CASE-MSC-20946-1; US-PATENT-APPL-SN-875799; NAS 

The coolant fluid evaporated in a compact heat absorbing panel 

utilizing monogroove heat pipes in a pumped two-phase system is 

replenished through a liquid inlet control valve under the control 

of an ultrasonic liquid presence detector which is connected to 

the panel. The detector maintains the desired liquid quantity in 

the panel's liquid coolant channels, thereby dynamically responding 

to varying heat loads. NASA 

10. 

The electron bombardment furnace consists of two confinement 

grid sections which may be moved and separated from each other. 

Inside the bombardment furnace, a tungsten element is enclosed. 

The material specimen is located within the tungsten element and 

grounded by means of grounded support wires connected to the 

respective sections of the furnace. The material specimen is 

supported on the ground wires and heated by electron 

bombardment until melt occurs. The furnace sections are separated 

in opposite directions causing the ground wires to pull from the 

surfaces of the specimen, leaving the specimen freely suspended 

in the process chamber without the action of external forces. The 

specimen remains in its melt condition in the processing chamber 

where it can be undercooled without external forces acting on the 

specimen, which would cause dynamic nucleation. NASA 

35 

INSTRUMENTATION AND PHOTOGRAPHY 

Includes remote sensors; measuring instruments and gages; 

detectors; cameras and photographic supplies; and' holography. 

N86-23899*# National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

APPARATUS AND FURNACE FOR CONTAINERLESS 

PROCESSING OF HIGH TEMPERATURE MATERIALS IN SPACE 

Patent Appllcatlon 

M. B. ROBINSON and L. L. LACY, inventors (to NASA) 5 Dec. 

1985 13p 

US-PATENT-APPL-SN-805010) Avail: NTlS HC AO2/MF A01 

CSCL 146 

(NASA-CASE-MFS-28087-1; NAS 1.71 :MFS-28087-1; 

N86-24960'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

INDUCTIVE ENERGY FOR RAPID STRAIN GUAGE 

AmACHMENT Patent Appllcatlon 

T. D. SCHOTT, inventor (to NASA), R. L. FOX, inventor (to NASA), 

and J. D. BUCKLEY, inventor (to NASA) 20 Feb. 1986 11 p 

US-PATENT-APPL-SN-831372) Avail: NTlS HC AOS/MF A01 

CSCL 146 

A new method of bonding strain gauges to base structures 

was found. Induction heating is used to concentrate high 

temperature levels in the bonding of a strain gauge to a substrate. 

By using new method embodiments, the adhesive curing schedules 

of the prior art ware reduced from a matter of hours to a matter 

of minutes. A method is provided for installing a strain gauge 

device on a base. According to another aspect of the present 

method invention, the layer of ferric material is a thin plate of 

ferric material which is placed substantially adjacent to the upper 

surface of the strain gauge device prior to the heating of the 

layer of ferric material by induction heating. By utilizing the separate 

plate of ferric material, the present invention may be utilized to 

(NASA-CASE-LAR-13237-1; NAS 1.71-LAR-13237-1; 

17 
35 INSTRUMENTATION AND PHOTOGRAPHY 

bond strain gauges to low reluctance bases such as aluminum or 

to no reluctance bases such as fiberglass. NASA 

PI @ 56 12 

N86-25752' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

FLUID FLOW METER FOR MEASURING THE RATE OF FLUID 

FLOW IN A CONDUIT Patent 

P. R. WHITE, inventor (to NASA) 25 Feb. 1986 8 p Filed 4 

Apr. 1985 Supersedes N85-30286 Sponsored by NASA 

Avail: US Patent and Trademark Office CSCL 148 

A tube fluid flow rate meter consists of a reservoir divided by 

flexible diaphragm into two separate isolated compartments. The 

incoming and outgoing tubes open into the compartments. The 

orifice is sized to allow maximum tube fluid flow. Opposing 

compression springs are secured within the two compartments on 

opposite sides of the orifice to maintain orifice position when the 

tube fluid pressure is zero. A tapered element is centered in, and 

extends through the orifice into the compartment, leaving an 

annular opening between the element and the perimeter of the 

oriface. The size varies as the diaphragm flexes with changes in 

the tube fluid pressure to change the fluid flow through the opening. 

The light source directs light upon the element which in turn scatters 

the light through the opening into the compartment. The light 

detector in the compartment senses the scattered light to generate 

a signal indicating the amount of fluid. 

Official Gazette of the U.S. Patent and Trademark Office 

(NASA-CASE-MFS-28030-1; US-PATENT-4,572,004; 

US-PATENT-APPL-SN-719799; US-PATENT-CLASS-73-861 58) 

/ 

.7 

N86-25753' National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

DISCHARGE CELL FOR OPTOGALVANIC SPECTROSCOPY 

HAVING ORTHOGONAL RELATIONSHIP BETWEEN THE 

PROBE LASER AND DISCHARGE AXIS Patent 

C. R. WEBSTER, inventor (to NASA) (Jet Propulsion Lab., California 

Inst. of Tech., Pasadena.) 29 Apr. 1986 12 p Filed 30 Nov. 

1983 Sponsored by NASA 

US-PATENT-CLASS-356-31 8) 

Office CSCL 148 

A method and apparatus for an optogalvanic spectroscopy 

system are disclosed. Orthogonal geometry 'exists between the 

axis of a laser probe beam and the axis of a discharge created 

by a pair of spaced apart and longituduinally aligned high voltage 

electrodes. The electrodes are movable to permit adjustment of 

the location of a point in the discharge which is to irradiated by a 

laser beam crossing the discharge region. The cell dimensions 

are selected so that the cross section of the discharge region is 

substantly comparable in size to the cross section of the laser 

beam passing orthogonally through the discharge region. 

Official Gazette of the U.S. patent and Trademark Office 

(NASA-CASE-NPO-16271-1; US-PATENT-4,585,344; 

US-PATENT-APPL-SN-556514; US-PATENT-CLASS-356-31 1 ; 

Avail: US Patent and Trademark 

N86-26595' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

SOLID SORBENT AIR SAMPLER Patent 

T. J. GALEN, inventor (to NASA) (Northrop Services, Inc., Houston, 

Tex.) 29 Apr. 1986 7 p Supersedes N85-20301 Filed 10 Oct. 

1984 Sponsored by NASA Sponsored by NASA 

(NASA-CASE-MSC-20653-1; US-PATENT-4,584,887; 

US-PATENT-APPL-SN-659474; US-PATENT-CLASS-73-863.31 ; 

US-PATENT-CLASS-73-863.21 ; US-PATENT-CLASS-73-864.34; 

US-PATENT-CLASS-73-863.72) Avail: US Patent and Trademark 

Office CSCL 148 

A fluid sampler for collecting a plurality of discrete samples 

over separate time intervals is described. The sampler comprises 

a sample assembly having an inlet and a plurality of discreet 

sample tubes each of which has inlet and outlet sides. A multiport 

dual acting valve is provided in the sampler in order to sequentially 

pass air from the sample inlet into the selected sample tubes. 

The sample tubes extend longitudinally of the housing and are 

located about the outer periphery thereof so that upon removal of 

an enclosure cover, they are readily accessible for operation of 

18 
35 INSTRUMENTATION AND PHOTOGRAPHY 

the sampler in an analysis mode. 

Official Gazette of the US. Patent and Trademark Office 

N86-26598'# National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

PLANAR OSCILLATORY STIRRING APPARATUS Patent 

Appllcatlon 

M. F. WOLF, inventor (to NASA) (Stanford Univ., Calif.) 15 Aug. 

1985 15p 

(Contract NAS8-34872) 

US-PATENT-APPL-SN-765991) Avail: NTlS HC AO2/MF A01 

CSCL 148 

The present invention is directed to an apparatus for stirring 

materials using planar orthogonal axes oscillations. The apparatus 

has a movable slide plate sandwiched between two fixed parallel 

support plates. Pressurized air is supplied to the movable slide 

plate which employs a tri-arm air bearing vent structure which 

allows the slide plate to float and to translate between the parallel 

support plates. The container having a material to be stirred is 

secured to the upper surface of the slide plate through an aperture 

in the upper support plate. A motor driven eccentric shaft loosely 

extends into a center hole bearing of the slide plate to cause the 

horizontal oscillations, Novelty lis in the combination of elements 

which exploits the discovery that low frequency, orthogonal 

oscillations applied horizontally to a Bridgman crucible provides a 

very rigorous stirring action, comparable with and more effective 

by an order of magnitude than the accelerated crucible rotation 

technique. NASA 

(NASA-CASE-MFS-26002-1-CU; NAS 1.71 :MFS-26002-1-CU 

N86-29174' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

NEBULIZATION REFLUX CONCENTRATOR Patent 

V. G. COLLINS and W. R. COFER. 111 (College of William and 

Mary, Newport News, Va.) 17 Jun. 1986 6 p Filed 5 Nov. 

1984 Supersedes N85-20154 (23 - 11, p 161 5) 

(NASA-CASE-LAR-13254-1 CU; US-PATENT-4,595,399; 

US-PATENT-APPL-SN-668432; US-PATENT-CLASS-55-255; 

US-PATENT-CLASS-55-259; US-PATENT-CLASS-55-521 ; 

US-PATENT-CLASS-55-528; US-PATENT-CLASS-261 -78A) 

Avail: US Patent and Trademark Office CSCL 148 

A nebulization reflux concentrator for removing trace gas 

contaminants from a sample gas is described. Sample gas from a 

gas supply is drawn by a suction source into a vessel. The gas 

enters the vessel through an atomizing nozzle, thereby atomizing 

and entraining a scrubbing liquid solvent drawn through a siphon 

tube from a scrubbing liquid reservoir. The gas and entrained 

liquid rise through a concentrator and impinge upon a solvent 

phobic filter, whereby purified gas exits through the filter housing 

and contaminated liquid coalesces on the solvent phobic filter 

and falls into the reservoir. 

Official Gazette of the US. Patent and Trademark Office 

N86-32695'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

FLUIDIC ANGULAR VELOCITY SENSOR Patent 

C. M. BERDAHL. inventor (to NASA) 29 Jul. 1986 9 p Filed 

4 Apr. 1985 Supersedes N85-29219 (23 - 18, p 3104) 

US-PATENT-CLASS-73-521) Avail: US Patent and Trademark 

Office CSCL 148 

A fluidic sensor providing a differential pressure signal 

proportional to the angular velocity of a rotary input is described. 

In one embodiment the sensor includes a fluid pump having an 

impeller coupled to a rotary input. A housing forming a constricting 

fluid flow chamber is connected to the fluid input of the pump. 

The hesing is previded vri?h a !!uid !!ew restrictive input t~ the 

flow chamber and a porl communicating with the interior of the 

flow chamber. The differential pressure signal measured across 

the flow restrictive input is relatively noise free and proportional 

to the square of the angular velocity of the impeller. In an alternative 

embodiment, the flow chamber has a generally cylindrical 

configuration and plates having flow restrictive apertures are 

disposed within the chamber downstream from the housing port. 

(NASA-CASE-NPO-16479-ICU; US-PATENT-4.602.509; 

US-PATENT-APPL-SN-719794; US-PATENT-CLASS-73-502; 

19 
35 INSTRUMENTATION AND PHOTOGRAPHY 

In this embodiment. the differential pressure signal IS found to be 

approximately linear with the angular velocity of the impeller 

Official Gazette of the U S Patent and Trademark Office 

described These velocimeters measure fluid velocity by observing 

the light scattered by particles in the fluid stream Moving fluid 

particulates are simulated by fine taut wires that are radially 

mounted on a disk that is rotated at a known velocity. The laser 

beam intersection locus is first aimed at the very center of the 

disk and then the disk is translated so that the locus is swept by 

the rotating wires The radial distance traversed is precisely 

measured so that the velocity of the wires (pseudo particles) may 

be calculated NASA 

N86-32696' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

TWO-AXIS, SELF-NULLING SKIN FRICTION BALANCE Patent 

T. PING, inventor (to NASA) and F. H. SUPPLEE, JR., inventor 

(to NASA) 12 Aug. 1986 5 p Filed 28 Feb. 1985 Supersedes 

N85-21610 (23 - 12, p 1851) 

(NASA-CASE-LAR-13294-1; US-PATENT-4.604,903; 

US-PATENT-APPL-SN-706681; US-PATENT-CLASS-73462.04; 

US-PATENT-CLASS-73-1 47; US-PATENT-CLASS-73-862.61) 

Avail: US Patent and Trademark Office CSCL 148 

A skin friction force measuring device is described which is 

comprised of a first pivoted L shaped arm, a second arm pivoted on one end of the L shaped arm with a sensing element attached 

to an end of the second arm. In response to skin friction forces 

on the sensing element the arms are pivoted about the two pivots 

and two nulling means force the pivots back to their zero position. 

The outputs of the two nulling means are indicative of the skin 

friction forces along two perpendicular axes in the plane of the 

sensing element. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-32698' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

APPARATUS AND METHOD FOR INSPECTING A BEARING 

BALL Patent 

B. F. BANKSTON, inventor (to NASA) 5 Nov. 1985 7 p Filed 

09 Mar. 1983 Supersedes N83-21316 (21 - 11, p 1699) 

(NASA-CASE-MFS-25833-1; US-PATENT-4,551.677; 

US-PATENT-APPL-SN-473827; US-PATENT-CLASS-324-226; 

US-PATENT-CLASS-324-238; US-PATENT-CLASS-324-240; 

US-PATENT-CLASS-324-262; US-PATENT-CLASS-73-37.5) 

Avail: US Patent and Trademark Office CSCL 148 

A method and apparatus for inspecting the surface of a ball 

bearing is disclosed which includes a base having a high friction 

non-abrasive base scanning surface. A holding device includes a 

cone-shaped cup recess in which a ball element is received. Air 

is introduced through a passage to relieve friction between the 

wall of the recess and the ball element and facilitate rolling of the 

ball over the high friction base surface. The holding device is 

moved over the base scanning surface in a predetermined pattern 

such that the entire surface of the ball element is inspected byan 

eddy current probe which detects any surface defects. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-32697' National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

SPINNING DISK CALIBRATION METHOD AND APPARATUS 

FOR LASER DOPPLER VELOCIMETER Patent 

P. K. SNYDER, inventor (to NASA) 15 Jul. 1986 8 p Filed 19 

Apr. 1984 Supersedes N84-25015 (22 - 15. p 2335) 

(NASA-CASE-ARC-1 151 0-1; US-PATENT-4,600.301 ; 

US-PATENT-APPL-SN-602049; US-PATENT-CLASS-356-28.5; 

US-PATENT-CLASS-356-72; US-PATENT-CLASS-356-73; 

US-PATENT-CLASS-434-4; NAS 1.71:ARC-11510-1) Avail: US 

Patent and Trademark Office CSCL 148 

A method and apparatus for calibrating laser Doppler 

velocimeters having one or more intersecting beam pairs are 

20 
36 LASERS AND MASERS 

N86-32700'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

ULTRASONIC DEPTH GAUGE FOR LIQUIDS UNDER HIGH 

PRESSURE Patent Application 

A. J. ZUCKERWAR and D. S. MAZEL, inventors (to NASA) (Old 

Dominion Univ.. Norfolk, Va.) 13 Feb. 1986 11 p 

US-PATENT-APPL-SN-829042) Avail: NTlS HC A02/MF A01 

CSCL 148 

The invention relates to an ultrasonic depth gauge for liquids 

under high pressure and is particularly useful in the space industry 

where it is necessary to use a pressurized gas to transfer a liquid 

from one location to another. Conventional liquid depth gauges 

do not have the capability to operate under extreme high pressures 

(Le.: exceeding 300 p.s.i.). An ultrasonic depth gauge capable of 

withstanding high pressure according to the present invention is 

comprised of a transducer assembly and a supporting electronics 

unit. The transducer assembly is mounted into the bottom wall of 

a storage vessel with its resonating surface directly exposed to 

the highly pressurized liquid in the vessel. In operation, the 

ultrasonic pulse propagates upward through the liquid to the 

liquid-gas interface in the storage vessel. When the ultrasonic 

echo returns from the liquid-gas interface, it re-excites the 

composite resonator into vibration. The supporting electronics unit 

measures the round-trip transmit time for the ultrasonic pulse and 

computing process used makes the device simple, inexpensive to 

manufacture and easy to calibrate. NASA 

(NASA-CASE-LAR-13300-1CU; NAS 1.71:IAR-13300-CU; 

r-7 DISPLAY 

its return echo to traverse the depth of the highly pressurized 

liquid. The novelty of this invention resides in the use of a 

conventional transducer rigidly bonded to the inside wall of a bored 

out conventional high-pressure plug to form a composite resonator 

capable of withstanding extremely high pressure. NASA 

N86-32701'# 

Langley Research Center, Hampton, Va. 

IMPROVED FLUXGATE MAGNETOMETER Patent Application 

H. D. GARNER, inventor (to NASA) 

1.1 1:LAii-i356O-ij Avail: =TIS HC AGSiMF M1 CSCL 148 

The invention relates to a fluxgate magnetometer type device 

in which the directions and relative magnitudes of the components 

of the Earth's magnetic field, lying parallel to the longitudinal and 

to the transverse axes of the vehicle in which the device is mounted, 

are measured and used to calculate the heading of the vehicle 

with respect to magnetic north. The manner in which the 

components of the Earth's magnetic field are measured and the 

National Aeronautics and Space' Administration. 

16 Jul. 1986 16 p 

(NASA-CASE-LAR-I 3560-1 ; US-PATENT-APPL-SN-886123; NAS . -- 

36 

LASERS AND MASERS 

Includes parametric amplifiers. 

N86-24977'# National Aeronautics and Space Administration. 

Lyndon 8. Johnson Space Center, Houston, Tex. 

LASER RANGING AND VIDEO DISPLAY SYSTEM Patent 

Application 

J. K. RUSSELL, inventor to (NASA) (Lockheed Engineering and 

Management Services Co., Inc., Houston, Tex.) 18 Mar. 1986 

US-PATENT-APPL-SN-840825) Avail NTlS HC AO2/MF A01 

CSCL 171 

Ranging data and video display systems, and, more particularly, 

methods and apparatus for generating measurements of range 

and range rate and display in conjunction with video imagery are 

developed. Method and apparatus are disclosed for deriving laser 

ranging information and generating a video display combining an 

image of the target with alpha-numeric indications of the ranging 

information. A television camera and laser ranger are boresighted 

parallel to one another and aimed at a remote target object. An 

infrared laser diode in the ranger is pulsed. Corresponding light 

pulses reflected from the target are detected by the ranger. Elapsed 

time between transmission of each of a plurality of such pulses 

and receipt by the ranger is measured and an average time derived. 

Processor circuitry derives ranges and range rate of the target 

from the time average, generates alpha-numeric indications, and 

superimposes them with target video images generated by the 

television camera on a television monitor. NASA 

23 P 

(NASA-CASE-MSC-20870-1; NAS 1.71 :MSG20870-1; 

21 
36 LASERS AND MASERS 

N86-24978'# National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

DUAL MODE LASER VELOCIMETER Patent Application 

W. D. GUNTER, JR., inventor (to NASA), R. W. DONALDSON, 

inventor (to NASA), and A. G. ANDERSON, JR., inventor (to 

NASA) 31 Mar. 1986 16 p 

US-PATENT-APPL-SN-846427) Avail: NTlS HC AO2/MF A01 

CSCL 20E 

This invention relates to a laser Doppler velocimeter (LDV) 

that is capable of operating with a small focus diameter for 

analyzing fluid flows at low velocity with high spatial resolution, or 

with a larger focus diameter to measure fluid flows at higher 

velocities accurately. More particularly, it relates to such an LDV 

in which a simple reversal of a lens pair will allow the LDV to 

operate in the two focus diameter modes. NASA 

(NASA-CASE-ARC-1 1634-1; NAS 1.71 :ARC-1 1634-1; 

N86-29204' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

LONG GAIN LENGTH SOLAR PUMPED BOX LASER Patent 

R. J. DEYOUNG 10 Jun. 1986 4 p Filed 18 Jun. 1985 

Supersedes N86-19596 (24 - 10, p 1581) 

1.71:LAR-13256-1) Avail: US Patent and Trademark Office 

CSCL 20E 

A solar pumped laser has its lasing path lengthened by forming 

a square loop in the lasing path by means of bending mirrors. 

Solar radiation is collected and concentrated into a donut shaped 

intensity pattern. This intensity pattern is directed onto the lasing 

path such that there is a maximum fit of the solar intensity pattern 

to the square loop laser cavity. 

Official Gazette of the U.S. Patent and Trademark Office 

(NASA-CASE-LAR-13256-1; US-PATENT-4,594.720; 

US-PATENT-APPL-SN-745973; US-PATENT-CLASS-372-79; NAS 

37 

MECHANICAL ENGINEERING 

Includes auxiliary systems (non-power); machine elements and 

processes; and mechanical equipment. 

N86-24993'# National Aeronautics and Space Administration. 

Langley Research Center, Harnpton, Va. 

ADJUSTABLE MOUNT FOR ELECTRO-OPTIC TRANSDUCERS 

IN AN EVACUATED CRYOGENIC SYSTEM Patent Application 

E. A. CROSSLEY, JR., inventor (to NASA), D. P. HAYES, inventor 

(to NASA), H. C. JONES, inventor (to NASA), and I. W. JONES, 

inventor (to NASA) 20 Feb. 1986 16 p 

US-PATENT-APPL-SN-831377) Avail: NTlS HC AO2/MF A01 

CSCL 131 

The invention is a five-degree of freedom adjustable mounting 

device for positioning an electro-optic transducerr in an evacuated, 

cryogenic chamber. Electro-optic transducers are used in this 

manner as high sensitivity detectors of gas emission lines in 

spectroscopic analysis. The mount is made up of an adjusting 

mechanism and a transducer mount. This combination avoids many 

difficulties with prior devices by permitting the use of an internal 

lens and allowing independent adjustment of each degree of 

freedom. The transducer mount, although attached to the adjusting 

mechanism, is isolated thermally such that a cryogenic environment 

can be maintained at the transducer while the adjusting mechanism 

remains at room temperature. Radiation shields also are 

incorporated to further reduce heat flow to the transducer location. 

Features of this invention include the use of an internal lens and 

mechanizing of an adjustment device which allows for independent 

adjustments. An adjustment of one parameter will not affect the 

setting of any other parameter. This result is achieved by locating 

the centers of rotation of the angular adjustment at the focal 

point of the internal lens. NASA 

(NASA-CASE-LAR-13100-1; NAS 1.71:LAR-13100-1; 

2 

0 

N86-25789' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

SYNCHRONOUSLY DEPLOYABLE TRUSS STRUCTURE Patent 

H. G. BUSH, inventor (to NASA), M. MIKULAS. JR., inventor (to 

NASA), and E. WALLSOM, inventor (to NASA) (Kentron 

International, Inc., Hampton, Va.) 1 Apr. 1986 8 p Filed 30 

Nov. 1983 Sponsored by NASA 

(NASA-CASE-LAR-13117-1; US-PATENT-4,578,920; 

US-PATENT-APPL-SN-556512; US-PATENT-CLASS-52-65; 

US-PATENT-CLASS-52-1 1 1 ; US-PATENT-CLASS-52 648; 

US-PATENT-CLASS-244-1 59; US-PATENT-CLASS-244-1 73; 

US-PATENT-CIA S-343-881; US-PATENT-CLASS-343-882) 

Avail: US Patent and Trademark Office CSCL 131 

A collapsible-expandable truss structure. including first and 

second spaced surface truss layers having an attached core layer 

22 
37 MECHANICAL ENGINEERING 

is described. The surface truss layers are composed of a plurality 

of linear struts arranged in multiple triangular configurations. Each 

linear strut is hinged at the center and hinge connected at each 

end to a nodular joint. A passive spring serves as the expansion 

force to move the folded struts from a stowed collapsed position 

to a deployed operative final truss configuration. A damper controls 

the rate of spring expansion for the synchronized deployment of 

the truss as the folded configuration is released for deployment 

by the restrain belts. The truss is synchronously extended under 

the control of motor driven spools. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-25790' National Aeronautics and Space Administration. 

Lewis Research Center. Cleveland, Ohio. 

VARIABLE FRICTION SECONDARY SEAL FOR FACE SEALS 

Patent 

E. DIRUSSO, inventor (to NASA) 8 Apr. 1986 5 p Filed 16 

Nov. 1984 Supersedes N85-20377 Sponsored by NASA 

US-PATENT-CLASS-227-28) Avail: US Patent and Trademark 

Office CSCL 11A 

Vibration and stability of a primary seal ring is controlled by a 

secondary seal system. An inflatable bladder which forms a portion 

of the secondary seal varies the damping applied to this seal 

ring. The amplitude of vibration of the primary seal ring is sensed 

with a proximity probe that is connected to a microprocessor in a 

control system. The bladder pressure is changed by the control 

system to mitigate any sensed instability or vibration. 

Official Gazette of the U.S. Patent and Trademark Office 

(NASA-CASE-LEW-14170-1; US-PATENT-4,580-791; 

US-PATENT-APPL-SN-672224; US-PATENT-CLASS-227-27; 

N86-25791' 

Langley Research Center, Hampton. Va. 

COLUMNS USEFUL IN SATELLITE CONSTRUCTION Patent 

E. L. AHL, JR., inventor (to NASA) 6 May 1986 11 p Filed 2 

May 1984 Supersedes N84-25063 Sponsored by NASA 

National Aeronautics and Space Administration. 

LATCHING MECHANISM FOR DEPLOYABLE/RE-STOWABLE 

(NASA-CASE-LAR-1 31 69-1 ; US-PATENT-4.587.526; 

US-PATENT-APPL-SN-606431; US-PATENT-CLASS-343-8; 

US-PATENT-CLASS-343-DIG.2; US-PATENT-CLASS52-I 10) 

Avail: US Patent and Trademark Office CSCL 131 

A column longeron latch assembly provides the securing 

mechanism for the deployable, telescoping column of a 

hoop/column antenna. The column is an open lattice structure 

with three longerons disposed 120 deg apart as the principle load 

bearing member. The column is deployed from a pair of eleven 

nested bays disposed on opposite sides of a center section under 

the influence of a motor-cable-pulley system. The longeron latch 

is a four bar linkage mechanism using the over-center principle 

for automatically locking the longeron sections into position during 

deployment. The latch is unlocked when the antenna is to be 

restowed. A spring pack disposed in the end of each longeron 

serves to absorb stress forces on the deployed column through 

the cam head piston and abutting latch from an adjacent 

longeron. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-27629' National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

LOAD POSITIONING SYSTEM WITH GRAVITY COMPENSATION 

Patent 

R. H. HOLLOW 12 Dec. 1984 9 p 

(NASA-CASE-ARC-1 1525-1 ; US-PATENT-4,591,772; 

US-PATENT-APPL-SN-681041; US-PATENT-CLASS-31 8-6321 

US-PATENT-CLASS-31 8-8; US-PATENT-CLASS-3 18-40 

US-PATENT-CLASS-31 8-663) Avail: US Patent and Trademark 

Office CSCL 131 

A load positioning system with gravity compensation has a 

servomotor, position sensing feedback potentiometer and velocity 

sensing tachometer in a conventional closed loop sew0 

arrangement to cause a lead screw and a ball nut to vertically 

position a load. Gravity Compensating components comprise the 

DC motor, y6aiS. which coiiple toiqiie fr~m !he mo!cr != !!?e !ead 

screw, and constant current power supply. The constant weight 

of the load applied to the lead screw via the ball nut tend to 

cause the lead screw to rotate, the constant torque of which is 

opposed by the constant torque produced by the motor when fed 

from the constant current source. The constant current is preset 

as required by the potentiometer to effect equilibration of the load 

which thereby enables the positioning servomotor to see the load 

23 
37 MECHANICAL ENGINEERING 

as weightless under both static and dynamic conditions. Positioning 

acceleration and velocity performance are therefore symmetrical. 

Official Gazette of the US. Patent and Trademark Office 

welded or brazed to both the insert and the tube. The result is a 

permanent repair having great structural integrity. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-27630' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

OPTIMIZED BOLTED JOINT Patent 

L. J. HART-SMITH (McDonnell-Douglas Corp., Long Beach, Calif.), 

B. L. BUNIN, and D. J. WATTS, inventors (to NASA) 1 Apr. 

1986 9 p Filed 23 Jan. 1984 Supersedes N84-20859 (22 - 11, 

p 1664) Sponsored by NASA. Langley Research Center 

(NASA-CASE-LAR-13250-1; US-PATENT-4,579,475; 

US-PATENT-APPL-SN-573162; US-PATENT-CLASS-403-312; 

US-PATENT-CLASS-403-388; US-PATENT-CLASS-403-408.1) 

Avail: US Patent and Trademark Office CSCL 131 

A method is disclosed for joining segments of the skin of an 

aircraft. The ends of the skin are positioned in close proximity or 

abutt each other. The skin is of constant thickness throughout 

the joint and is sandwiched between splice plates, which taper in 

thickness from the last to the first bolt rows in order to reduce 

the stiffness of the splice plate and thereby reduce the load transfer 

at the location where bypass loads are the highest. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-32737' National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

DEPLOYABLE M-BRACED TRUSS STRUCTURE Patent 

M. M. MIKULAS, JR., inventor (to NASA) and M. D. RHODES, 

inventor (to NASA) 12 Aug. 1986 8 p Filed 30 Jul. 1985 

Supersedes N86-20799 (24 - 11, p 1783) 

(NASA-CASE-LAR-13081-1; US-PATENT-4,604,844; 

US-PATENT-APPL-SN-760378; US-PATENT-CLASS-52-632; 

US-PATENT-CLASS-52-1 1 1 ; US-PATENT-CLASS-52-645; 

US-PATENT-CLASS-52-646) 

Office CSCL 131 

A deployable M-braced truss structure, efficiently packaged into 

a compact stowed position and expandable to an operative position 

at the use site is described. The M-braced configuration effectively 

separates tension compression and shear in the structure and 

permits efficient structural design. Both diagonals and longerons 

telescope from an M-braced base unit and deploy either 

pneumatically, mechanically by springs or cables, or by powered 

reciprocating mechanisms. Upon full deployment, the diagonals 

and longerons lock into place with a simple latch mechanism. 

Official Gazette of the US. Patent and Trademark Office 

Avail: US Patent and Trademark 

N86-32736'# National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

METHOD OF REPAIRING HIDDEN LEAKS IN TUBES Patent 

J. D. DUESBERG, inventor (to NASA) and R. C. MILLS, SR., 

inventor (to NASA) 12 Aug. 1986 5 p Filed 30 Aug. 1985 

Supersedes N86-20802 (24 - 1 1, p 1783) 

(NASA-CASE-MFS-I 9796-1 ; US-PATENT-4,605.155; 

US-PATENT-APPL-SN-770920; US-PATENT-CLASS-228-1 19; 

US-PATENT-CLASS-1 38-97; US-PATENT-CLASS1 65-76; 

US-PATENT-CLASS-29-402.1 6) Avail: US Patent and Trademark 

Office CSCL 131 

A method of repairing a tubular assembly in which access to a 

defect in the tube is limited includes the steps of cutting an opening 

in the tube on the side opposite the defect so as to expose the 

defect from the inside of the tube. A tubular insert is inserted into 

the tube to cover the defect and is secured in place by means of 

brazing or welding. The remaining space between the opening 

and insert is closed by means of close-out patches which are 

N86-32738' National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

REMOTELY OPERABLE PERISTALTIC PUMP Patent 

R. R. BELEW, inventor (to NASA) 5 Aug. 1986 11 p Filed 08 

Mar. 1985 Supersedes N85-29288 (23 - 18. p 3116) 

Avail: US Patent and Trademark Office CSCL 13K 

A peristaltic pump is disclosed which includes a roller assembly 

on which is mounted a series of pump rollers. As the roller assembly 

is rotated by a drive gear the pump rollers are driven in reverse 

(NASA-CASE-MFS-28059-1; US-PATENT-4.604.038; 

US-PATENT-APPL-SN-709255; US-PATENT-CLASS-41 7-475) 

24 
rotation by means of a stationary ring gear and pump roller gears. 

An upper pressure shoe plate and a lower pressure shoe plate 

are positioned above sets of flexible tubing. The tubing is 

sandwiched between the pressure shoe plates and the pump 

rollers. A highly compact pump is provided having twice as many 

fluid channel lines as is conventional. The peristaltic pump device 

may be remotely operated by means of a rotary actuator which 

rotates a driving hub to move the shoe plates by means of 

eccentrically mounted links. The pressure shoe plates may be 

moved by the rotary actuator to a loaded position in which the 

fluid lines are pinched by the pump rollers and fluid is pumped to 

an unloaded position in which the fluid lines are maintained in an 

undeformed, uncrimped configuration so that no creases or crimps 

are set into the fluid lines during periods of prolonged nonuse. 

Official Gazette of the US. Patent and Trademark Office 

N86-32740*# National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

THERMAL STRESS MINIMIZED, TWO COMPONENT, TURBINE 

SHROUD SEAL Patent Appllcatlon 

R. F. HANDSCHUH, inventor (to NASA) 18 Jun. 1986 17 p 

1.71:LEW-14212-1) Avail: NTlS HC AO2/MF A01 CSCL 11A 

In a turbine machine, a two component shroud seal which 

maximizes insulation and sealing around the rotating tuhine blades 

and made by independently fabricating each of the two components 

then joining them together is disclosed. The two components may 

be joined together at room temperature. The resulting shroud seal 

provides greater engine efficiency and thrust. NASA 

(NASA-CASE-LEW-14212-1; USPATENT-APPL-SN-875798; NAS 

I I_ I 

‘30 

25 

44 ENERGY PRODUCTION AND CONVERSION 

39 

STRUCTURAL MECHANICS 

Includes structural element design and weight analysis; fatigue; 

and thermal stress. 

N86-32770‘# National Aeronautics and Space Administration. 

Marshall Space Flight Center, Huntsville, Ala. 

FATIGUE TESTING A PLURALITY OF TEST SPECIMENS AND 

METHOD Patent Appllcatlon 

J. D. HODO, inventor (to NASA), D. R. MOORE, inventor (to NASA), 

T. F. MORRIS, inventor (to NASA), and N. G. TILLER, inventor 

(to NASA) 16 Jul. 1986 12 p 

1.71:MFS-28118-1) Avail: NTlS HC AOP/MF A01 CSCL 20K 

This invention relates to a fatigue testing apparatus for 

simultaneously subjecting a plurality of material test specimens to 

cyclical tension loading to determine the fatigue strength of the 

material. The fatigue testing apparatus includes a pulling head 

having cylinders defined therein which carry reciprocating pistons. 

The reciprocation of the pistons is determined by cyclical supplies 

.of pressurized fluid to the cylinders. Piston rods extend from the 

pistons through the pulling head and are attachable to one end 

of test specimens, the other end of the test specimens being 

attachable to a fixed base, causing test specimens attached 

between the piston rods and the base to be subjected to cyclical 

tension loading. Because all of the cylinders share a common 

pressurized fluid supply, the breaking of a test specimen does not 

substantially effect the pressure of the fluid supplied to the other 

cylinders nor the tension applied to the other test specimens. 

NASA 

(NASA-CASE-MFS-28118-1; US-PATENT-APPL-SN-886121; NAS 

44 

ENERGY PRODUCTION AND CONVERSION 

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

batteries; global sources of energy; fossil fuels; geophysical 

conversion; hydroelectric power; and wind power. 

N86-25874’ National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

OXYGEN RECOMBINATION IN INDIVIDUAL PRESSURE 

VESSEL NICKEL-HYDROGEN BAlTERlES Patent 

J J. SMITHRICK, inventor (to NASA! 22 Apr. 1986 6 p Filed 

27 Jun. 1984 Supersedes N84-29084 Sponsored by NASA 

US-PATENT-CLASS-429-27; US-PATENT-CLASS-42-1 01) Avail: 

US Patent and Trademark Office CSCL 1OC 

A metal-hydrogen cell is described which avoids damage and 

retards flooding of the hydrogen electrodes by providing for 

(NASA-CASE-LEW-13822-1; US-PATENT-4.584,249 

US-PATENT-APPL-SN-625077; US-PATENT-CLASS-429-57; 
44 ENERGY PRODUCTION AND CONVERSION 

chemical recombination of oxygen and hydrogen in areas or sites 

remote from the hydrogen electrodes. In the metal-hydrogen cell, 

a plurality of electrical cell units are place in a back to back 

relationship. The cells may be lined with a wick, having one or 

more catalyzed sites on the inner surface of the cell. Separators 

disposed between the respective metal and hydrogen electrodes 

of each cell unit are provided with gas directing notches around 

their peripheries to facilitate the desired movement of gasses within 

the metal-hydrogen cell. Any two metal electrodes separated by a 

gas screen are provided with gas tight sealing means between 

the electrodes at each aperature. The sealing means may be a 

fing of rubber or elastomeric material which is somewhat 

compressible but nonreactive with other materials in the cell. 

Official Gazette of the U.S. Patent and Trademark Office 

f 

N86-27706' National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

PRQTECT!VE ?ELESCQP!NG SHlELD FOR SOUR 

CONCENTRATOR Patent 

M. J. ARGOUD (Jet Propulsion Lab., California Inst. of Tech., 

Pasadena), W. L. WALKER, and L. V. BUTLER, inventors (to 

NASA) 6 May 1986 7 p Filed 22 Feb. 1984 Supersedes 

N84-25164 (22 - 15, p 2361) Sponsored by NASA. Pasadena 

Office 

(NASA-CASE-NPO-16236-1; US-PATENT-4,586,487; 

US-PATENT-APPL-SN-582495; US-PATENT-CLASS-1 26-41 8; 

US-PATENT-CLASS1 26-41 9; US-PATENT-CLASS-1 26-438) 

Avail: US Patent and Trademark Office CSCL 10A 

An apparatus is described for use with a solar concentrator 

such as a parabolic dish which concentrates sunlight onto a small 

opening of a solar receiver, for protecting the receiver in the event 

of a system failure that could cause concentrated sunlight to 

damage the receiver. The protective apparatus includes a structure 

which can be moved to a stowed position where it does not 

block sunlight, to a deployed position. In this position, the structure 

forms a tube which substantially completely surrounds an axis 

connecting the receiver opening to the center of the concentrator 

at locations between the receiver and the concentrator. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-32875' National Aeronautics and Space Administration. 

Lewis Research Center, Cleveland, Ohio. 

LITHIUM COUNTERDOPED SILICON SOLAR CELL Patent 

I. WEINBERG, inventor (to NASA) and H. W. BRANDHORST, JR., 

inventor (to NASA) 26 Aug. 1986 7 p Filed 07 Nov. 1984 

Supersedes N85-20535 (23 - 11, p 1672) 

(NASA-CASE-LEW-14177-1; US-PATENT-4,608,452; 

US-PATENT-APPL-SN-669140; US-PATENT-CLASS-1 36-261 ; 

US-PATENT-CLASS-29-572; US-PATENT-CLASS-29-5766; 

US-PATENT-CUSS-I 48-1.5; US-PATENT-CLASS-357-30; 

US-PATENT-CLASS-357-91) Avail: US Patent and Trademark 

Office CSCL 10A 

The resistance to radiation damage of an n(+)p boron doped 

silicon solar cell is improved by lithium counterdoping. Even though 

lithium is an n-dopant in silicon, the lithium is introduced in small 

enough quantities so that the cell base remains p-type. The lithium 

is introduced into the solar cell wafer by implantation of lithium 

ions whose energy is about 50 keV. After this lithium implantation, 

the wafer is annealed in a nitrogen atmosphere at 375 C for two 

hours. Official Gazette of the U.S. Patent and Trademark Office 

18' 

26 
54 MANBYSTEM TECHNOLOGY AND LIFE SUPPORT 

54 

MANBYSTEM TECHNOLOGY AND LIFE 

SUPPORT 

Includes human engineering; biotechnology; and space suits and 

protective clothing. 

N86-28618' National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

TORSO SIZING RING CONSTRUCTION FOR HARD SPACE SUIT 

Patent 

H. C. VYKUKAL 10 Jun. 1986 9 p Filed 20 Dec. 1984 

Supersedes N85-21987 (23 - 12, p 1910) 

(NASA-CASE-ARC-1 161 6-1 ; USPATENT-4,593.41 5; 

US-PATENT-APPL-SN-684193; US-PATENT-CLASS-2-2.1A 

USPATENT-CLASS-2-2.1 R; US-PATENT-CLASS-126-202.11; 

US-PATENT-CLASS-414-1; US-PATENT-CLASS-414-5; 

US-PATENT-CLASS-414-7; US-PATENT-CLASS-414-8) Avail: 

US Patent and Trademark Office CSCL 06Q 

A hard suit for use in space or diving applications having an 

adjustable length torso covering that will fit a large variety of 

wearers is described. The torso covering comprises an upper 

section and a lower section which interconnect sa that the covering 

will fit wearers with short torsos. One or more sizing rings may be 

inserted between the upper and lower sections to accomodate 

larger torso sizes as required. Since access of the astronaut to 

the torso covering is preferably through an opening in the back of 

the upper section (which is closed off by the backpack), the rings 

slant upward-forward from the lower edge of the opening. The 

lower edge of the upper covering section has a coupler which 

slants upward-forward from the lower edge of the back opening. 

The lower torso section has a similarly slanted coupler which may 

interfit with the upper section coupler to accomodate the smallest 

torso size. One or more sizing rings may be inserted between the 

coupler sections of the upper and lower torso sections to 

accomodate larger torsos. Each ring has an upper coupler which 

may interfit with the upper section coupler and a lower coupler 

which may interfit with the lower section coupler. 

Official Gazette of the U.S. Patent and Trademark Office 

N86-28619' National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

ELBOW AND KNEE JOINT FOR HARD SPACE SUITS Patent 

H. ,C. WKUKAL 8 Jul. 1986 13 p Filed 30 Dec. 1984 

Supersedes N85-20666 (23 - 11, p 1697) 

(NASA-CASE-ARC-I 1610-1 ; US-PATENT-4,598,427; 

US-PATENT-APPL-SN-684190 US-PATENT-CLASS-2-2.1 A 

US-PATENT-CLASS-2-2.1 R: US-PATENT-CLASS-285-1 68: 

US-PATENT-CLASS-1 38-1 20) Avail: US Patent and Trademark 

Office CSCLOGO 

An elbow or knee joint for a hard space suit or similar usage 

is formed of three serially connected rigid sections which have 

truncated spherical configurations. The ends of each section form 

solid geometric angles, and the sections are interconnected by 

hermetically sealed ball bearings. The outer two sections are fixed 

together for rotation in a direction opposite to rotation of the center 

section. A preferred means to make the outer sections track each 

other in rotation comprises a rotatable continuous bead chain which 

engages sockets circumferentially spaced on the facing sides of 

the outer races of the bearings. The joint has a single pivot point 

and the bearing axes are always contained in a single plane for 

any articulation of the joint. Thus flexure of the joint simulates the 

coplanar flexure of the knee or elbow and is not susceptible to 

lockup. Official Gazette of the US. Patent and Trademark Office 

N86-28620' National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

SHOULDER AND HIP JOINT FOR HARD SPACE SUITS Patent 

H. C. WKUKAL 17 Jun. 1986 11 p Filed 20 Dec. 1984 

Supersedes N85-21986 (23 - 12, p 1910) 

(NASA-CASE-ARC-11543-1; US-PATENT-4,594,734; 

US-PATENT-APPL-SN-684192 US-PATENT-CLASS-2-2.1A 

US-PATENT-CLASS-414-7; US-PATENT-CLASS-285-168; 

US-PATENT-CLASS-I 38-1 20) Avail: US Patent and Trademark 

Office CSCL 06Q 

Shoulder and hip joints for hard space suits are disclosed which 

are comprised of three serially connected truncated spherical 

sections, the ends of which converge. gall bearings between the 

sections permit relative rotation. The proximal end of the first 

section is connected to the torso covering by a ball bearing and 

!he dista! end of the entermost sec!ior! is ceanec!ed !s the elbow 

or thigh covering by a ball bearing. The sections are qui-angular 

and this alleviates lockup, the condition where the distal end of 

the joint leaves the plane in which the user is attempting to flex. 

The axes of rotation of the bearings and the bearing mid planes 

are arranged to intersect in a particular manner that provides the 

joint with a minimum envelope. In one embodiment, the races of 

the bearing between the innermost section and the second section 

27 
54 MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT 

is partially within the inner race of the bearing between the torso 

and the innermost spherical section further to reduce bulk. 

Official Gazette of the U.S. Patent and Trademark Office 

7 

N86-29507'# National Aeronautics and Space Administration. 

Ames Research Center, Moffett Field, Calif. 

SHOULDER AND HIP JOINTS FOR HARD SPACE SUITS AND 

THE LIKE Patent 

H. C. VYKUKAL 8 Jul. 1986 12 p Filed 20 Aug. 1984 

Supersedes N84-33021 (22 - 22, p 3633) 

(NASA-CASE-ARC-1 1534-1; US-PATENT-4,598,428; 

US-PATENT-APPL-SN-642602; US-PATENT-CLASS-2-2.1 A; 

US-PATENT-CLASS-285-1 68; US-PATENT-CLASS-285-1 84; 

US-PATENT-CLASS-285-227; US-PATENT-CLASS-138-120; 

US-PATENT-403-1 64) Avail: US Patent and Trademark Office 

CSCL 06Q 

For use in hard space suits and the like, a joint between the 

torso covering and the upper arm covering (Le., shoulder) or 

between the torso covering and upper leg covering (i.e., hip) is 

disclosed. Each joint has an outer covering and a inner covering. 

The outer covering has plural perferably truncated toroidal sections 

decreasing in size proceeding outwardly. In one embodiment at 

each joint there are two bearings, the first larger than the second. 

The outer race of the larger bearing is attached to the outer edge 

of the smaller end of each section and the inner race of the 

larger bearing is attached to the end wall. The inner race of the 

smaller bearing is attached to the end wall. The outer race of the 

smaller bearing is attached to the larger end of the next section. 

Each bearing hask appropriate seals. Between each section is a 

rubber ring for the comfort of the wearer. Such rubber rings have 

radial flanges attached to the inner races of two adjacent bearings. 

Matching semicircular grooves are formed in the abutting 

overlapping surfaces. Bellows-like inner walls are also provided 

for each section fixed at one end to an inner cylindrical flange 

and, at the opposite end, to an end wall. Each outer section may 

rotate 360 deg relative to the next outer section, whereas the 

bellows sections do not rotate, but rather expand or contract locally 

as the rigid sections rotate relative to each other. 

Official Gazette of the US. Patent and Trademark Office 

60 

COMPUTER OPERATIONS AND HARDWARE 

Includes computer graphics and data processing. 

N86-23283'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

PROGRAMMABLE PIPELINED IMAGE PROCESSOR Patent 

Application 

D. B. GENNERY and B. WILCOX, inventors (to NASA) 31 Dec. 

1985 31 p 

(Contract NAS7-918) 

(NASA-CASE-NPO-I 6461-1 CU; NAS 1.71 :NPO-16461-1 CU; 

US-PATENT-APPL-SN-815103) Avail: NTlS HC AO3/MF A01 

CSCL 098 

A pipelined image processor selectively interconnects modules 

in a column of a two dimensional array to modules of the next 

column of the array of modules 1,l through M,N, where M is the 

number of modules in one dimension and N is the number of 

modules in the other direction. Each module includes two input 

selectors for A and B inputs, two convolvers, a binary function 

operator, a neighborhood comparison operator which produces 

an A output and an output selector which may select as a B 

output the output of any one of the components in the module, 

including the A output of the neighborhood comparison operator. 

Each module may be connected to as many as eight modules in 

the next column, preferably with the majority always in a different 

row that is up (or down) in the array for a generally spiral data 

path around the torus thus formed. The binary function operator 

is implemented as a look-up table addressed by the most significant 

8 bits of each 12-bit argument. The table output includes a function 

a function value and the slopes for interpolation of the two 

arguments by multiplying the 4 least significant bits in multipliers 

and adding the products to the function value through adders. 

NASA 

PO, 

hl 

N86-24224'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

NEIGHBORHOOD COMPARISON OPERATOR Patent 

Application 

D. B. GENNERY, inventor (to NASA) (JPL, Pasadena, Calif.) 31 

Dec. 1985 13 p 

(Contract NAS7-918) 

(NASA-CASE-NPO-16464-1CU; NAS 1.71 :NPO-16464-1CU; 

US-PATENT-APPL-SN-815099) Avail: NTlS HC AO2/MF A01 

CSCL 096 

28 
Digital values in a moving window are compared by an operator 

having nine comparators connected to line buffers for receiving a 

succession of central pixels together with eight neighborhood pixels. 

A single bit of program control determines whether the 

neighborhood pixels are to be compared with the central pixel or 

a threshold value. The central pixel is always compared with the 

threshold. The omparator output plus 2 bits indicating odd-even 

pixel/line information about the central pixel addresses a lookup 

table to provide 14 bits of information, including 2 bits which control 

a selector to pass either the central pixel value, the other 12 bits 

of table information, or the bit-wise logical OR of all nine pixels 

through circuit that implements a very wide OR gate. NASA 

I' -- ' I 

72 ATOMIC AND MOLECULAR PHYSICS 

72 

ATOMIC AND MOLECULAR PHYSICS 

Includes atomic structure and molecular spectra. 

N86-27055'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

VARIABLE ENERGY, HIGH FLUX, GROUND-STATE ATOMIC 

OXYGEN SOURCE Patent Application 

A. CHUTJIAN, Inventor (to NASA) (Jet Propulsion Lab., Caliornia 

Inst. of Tech., Pasadena.) and 0. J. ORIENT, Inventor (to NASA) 

10 Apr. 1986 17 p Sponsored by NASA 

US-PATENT-APPL-SN-852468) Avail: NTlS HC AO2/MF A01 

CSCL 20H 

A variable energy, high flux atomic oxygen source is described 

which is comprised of a means for producing a high density beam 

3f molecules which will emit 0(-) ions when bombarded with 

electrons; a means for producing a high current stream of electrons 

at a low energy level passing through the high density beam of 

molecules to produce a combined stream of electrons and O(-) 

ions; a means for accelerating the combined stream to a desired 

energy level; a means for producing an intense magnetic field to 

confine the electrons and 0(-) ions; a means for directing a multiple 

pass laser beam through the combined stream to strip off the 

excess electrons from a plurality of the 0(-) ions to produce 

ground-state 0 atoms within the combined stream; an electrostatic 

deflection means for deflecting the path of the 0(-) ions and the 

(NASA-CASE-NPO-16640-1-CU; NAS 1.71 :NPO-16640-1-CU; 

N86-24225.# National Aeronautics and Space 

Pasadena Office, Calif. 

CONVOLVER Patent Application 

8. WILCOX, inventor (to NASA) (JPL, Pasadena, Calif.) 

19A5 140 

electrons in the combined stream; and a means for stopping the 

0(-) ions and the electrons and for allowing only the ground-state 

0 atoms to continue as the source of the atoms of interest. The 

Kt$sgt ~~~~~~~/~~m~t~u;ptab'e for producing NASA Other 31 Dec. 

. . 

(Contract kAS7-918) 

(NASA-CASE-NPO-16462-1CU; NAS 1.71 :NPO-16462-1CU; 

US-PATENT-APPL-SN-815106) Avail: NTlS HC AO2/MF A01 

CSCL 096 

A 3-by-3 convohrer utilizes 9 binary arithmetic units connected 

in cascade for multiplying 12-bit binary pixel values P sub i which 

are positive or two's complement negative binary numbers by 5-bit 

magnitude (plus sign) weights W sub i which may be positive or 

negative. The weights are stored in registers including the sign 

bits. For a negative weight, the one's complement of the pixel 

value to be multiplied is formed at each unit by a bank of 17 

exclusive or gates G sub i under control of the sign of the 

corresponding weight w sub i, and a correction is made by adding 

the sum of the absolute values of all the negative weights for 

each 3x3 kernel. Since this correction value remains constant as 

long as the weights are constant, it can be precomputed and 

stored in a register as a value to be added to the product PW of 

the first arithmetic unit. NASA 

,._ 

'13. 

'. lillll 

I I 

N86-33127' 

Pasadena Office, Calif. 

AS A LONG-LIVED SUBMILLIMETER DETECTOR Patent 

A. N. CHUTJIAN. inventor (to NASA) i5 hi. 1986 8 p Filed 

21 Feb. 1985 Supersedes N85-30779 (23 - 19, p 3352) 

National Aeronautics and Space Administration. 

DOUBLE PHOTON EXCITATION OF HIGH-RYDBERG ATOMS 

(NASA-CASE-NPO-16372-1; US-PATENT-4,600,840; 

US-PATENT-APPL-SN-703847; US-PATENT-CLASS-250-338; 

US-PATENT-CLASS-250-336.1 ; US-PATENT-CLASS-250-340) 

Avail: US Patent and Trademark Office CSCL 20H 

A method and apparatus for detecting submillimeter or IR 

radiation is disclosed. A rare gas, such as xenon, is supplied at 

29 
74 OPTICS 

its ground state via a pressurized cylinder and an adjustable leak 

valve into a cryogenically cooled detection area. The ground state 

of xenon is double photon excited to a particularized level of the 

Rydberg series by a resonance lamp and a laser. The doubly 

excited gas is then further excited by the radiation to be measured. 

A field ionization and an ion measurement indicative of the radiation 

intensity is achieved. 

Official Gazette of the US. Patent and Trademark Office 

L! 

74 

OPTICS 

Includes light phenomena. 

N86-26190' National Aeronautics and Space Administration. 

Goddard Space Flight Center, Greenbelt, Md. 

OPTICAL MULTIPLE SAMPLE VACUUM INTEGRATING SPHERE 

Patent 

C. L. BUTNER, inventor (to NASA) 22 Apr. 1986 6 p Filed 

30 Nov. 1983 Supersedes N84-15960 Sponsored by NASA 

(NASA-CASE-GSC-12849-1; US-PATENT-4,583,860; 

US-PATENT-APPL-SN-556481; US-PATENT-CLASS-356-446; 

US-PATENT-CLASS-250-228; US-PATENT-CLASS-56-73; 

US-PATENT-CLASS-356-236; US-PATENT-CLASS-356-244) 

Avail: US Patent and Trademark Office CSCL 20F 

An integrating sphere comprised of a uniform difusely reflecting 

spherical cavity, having mutually transverse input and output ports, 

and a linear sample transport mechanism is described. The sample 

transport mechanism is secured so that the multiple samples can 

be brought into registration with the input port, one at a time, 

without having to open or disassemble the apparatus when a 

change of sample is desired. A vacuum tight seal is provided 

between the cavity and the transport mechanism. This maintains 

the integrity of a vacuum generated with the sphere when attached 

to the source of optical energy. The device is utilized to test 

emissive characteristics such as the relative fluorescence quantum 

efficiency of a dye sample placed in the path of a monochromatic 

optical energy source coupled to the input port while having a 

light detector coupled to the output port. 

Oiiiciai Gazeire of the US Patent and Trademark Office 

=a 

N86-28732' 

Goddard Space Flight Center, Greenbelt, Md. 

WIDE-ANGLE FLAT FIELD TELESCOPE Patent 

K. L. HALLAM, B. J. HOWELL, and M. E. WILSON 

7 p Filed 5 Feb 1985 Supersedes N85-20868 (23 - 11, p 1728) 

National Aeronautics and Space Administration. 

8 Jul. 1986 

(NASA-CASE-GSC-12825-1; US-PATENT-4,598,981; 

US-PATENT-APPL-SN-698641; US-PATENT-CLASS-350-505 

US-PATENT-CLASS-350-276R; US-PATENT-CLASS-354-479 

US-PATENT-CLASS-358-222) 

Office CSCL 20F 

Described is an unobscured three mirror wide angle telescopic 

imaging system comprised of an input baffle which provides a 20 

deg (Y axis) x 30 deg (X axis) field of view, a primary mirror 

having a convex spherical surface, a secondary mirror having a 

concave ellipsoidal reflecting surface, a tertiary mirror having a 

concave spherical reflecting surface. The mirrors comprise mirror 

elements which are offset segments of parent mirrors whose axes 

and vertices commonly lie on the system's optical axis. An iris 

diaphragm forming an aperture stop is located between the 

secondary and tertiary mirror with its center also being coincident 

with the optical axis and being further located at the beam waist 

of input light beams reflected from the primary and secondary 

mirror surfaces. At the system focus following the tertiary mirror 

is located a flat detector which may be. for example, a TV imaging 

tube or a photographic film. When desirable, a spectral transmission 

filter is placed in front of the detector in close proximity thereto. 

Official Gazette of the U.S. Patent and Trademark Office 

Avail: US Patent and Trademark 

N86-29650'# National Aeronautics and Space Administration. 

Gcddard Space Flight Center, Greenbelt, Md. 

MULTISPECTRAL L!NEAFI ARRAY &L!LT!El!!Jn SELECT!=?! 

DEVICE Patent 

H. L. RICHARD 8 Jul. 1986 8 p Filed 2 May 1984 Supersedes 

N84-25016 (22 - 15. p 2335) 

(NASA-CASE-GSC-12911-1; US-PATENT-4,599,001; 

US-PATENT-APPL-SN-606426; US-PATENT-CLASS-356-41 9; 

US-PATENT-CLASS-356-402; US-PATENT-CLASS-350-31 5; 

US-PATENT-CLASS-350-31 8) Avail: US Patent and Trademark 

Office CSCL2OF 

An apparatus for detecting multiple spectral bands, individually 

or concurrently, using linear detector arrays is described. The 

system employs a beamsplitter to divide the optical source into 

two or more optical beams which are directed at the linear detector 

arrays. Filter trays are positioned in the focal planes of the optical 

beams so that the beams pass through the filter trays prior to 

impinging upon the detector arrays. Multiple filters are placed on 

the filter trays. Linear actuators positioned adjacent the filter trays 

translate the trays across the focal planes of the optical beams 

so that individual filters are positioned in the path of beams such 

that those frequencies of the beams that fall within the spectral 

ranges of the individual bandpass filter through which it passes 

30 
74 OPTICS 

may be detected by the detector arrays for further examination 

and analysis. 

Official Gazette of the US. Patent and Trademark Office 

N86-32266' National Aeronautics and Space Administration. 

Goddard Space Flight Center, Greenbelt, Md. 

OPTICAL DISTANCE MEASURING INSTRUMENT 

J. E. ABSHIRE, inventor (to NASA) 15 Jul. 1986 10 p Filed 

10 Aug. 1982 Supersedes N83-13982 (21 - 04, p 600) 

US-PATENT-CLASS-356-4.5) Avail: US Patent and Trademark 

Office CSCL 20F 

An optical instrument, such as a stabili monitor or a target 

range finder, uses an unstabilized laser to project a composite 

optical signal of coherent light having two naturally occurring 

longitudinal mode components. A beamsplitter divides the signal 

into a reference beam which is directed toward one photodetector 

and a transmitted beam which illuminates and is reflected from a 

distant target onto a second photodetector optically isolated from 

the first Photodetector. Both photodetectors are operated on the 

square law principle to provide electrical signals modulated at a 

frequency equal to the separation between the frequencies of the 

two longitudinal mode components of the optical signal projected 

by the laser. Slight movement of the target may be detected and 

measured by electrically monitoring the phase difference between 

the two signals provided by the photodetectors and the range of 

the target measured with the aid of a microprocessor by changing 

the separation between the longitudinal modes by shifting the length 

of the resonator cavity in an iterative series of increments. 

Official Gazette of the US. Patent and Trademark Office 

(NASA-CASE-GSC-12761-1; US-PATENT-4,600,299; 

US-PATENT-APPL-SN-406820; US-PATENT-CLASS-356-5; 

A ->- 

-.+I . 

N8&33137*# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

PHOTODETECTOR ARRAY WITH IMAGE PLANE PROCESSING 

Patent Appllcatlon 

D. J. JOBSON, inventor (to NASA) 16 Jul. 1986 11 p 

1.71:LAR-13391-1) Avail: NTlS HC AO2/MF A01 CSCL 20F 

An apparatus is provided for merging image detection provided 

by an array of photodetector elements and local neighborhood 

processing of the outputs of photodetector elements which is useful 

in applications requiring high speed extraction of meaningful 

information from raw detector signals. The apparatus combines 

relatively large photodetector elements with small electronic 

processing elements located between the photodetector elements 

on the same chip. The close proximity of the photodetector and 

signal processing elements increases the speed of information 

acquisition and minimizes undesirable signal noise. NASA 

(NASA-CASE-LAR-13391-1; US-PATENT-APPL-SN-886133; NAS 

(VOLTAGE 

MSTRIBUTION 

POINT 

N86-33138'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

COMPENSATION FOR PRIMARY REFLECTOR WAVEFRONT 

ERROR Patent Application 

A. E. MEINEL, inventor (to NASA), M. P. MEINEL. inventor (to 

NASA), and J. E. STACY, inventor (to NASA) 16 

P 

(Contract NAS7-918) 

(NASA-CASE-NPO-16869-1 CU; US-PATENT-APPL-SN-867986 

NAS 1.71:NPO-16869) Avail: NTlS HC AO2/MF A01 CSCL 

20F 

The object of the invention is to compensate for errors in a 

large telescope primary reflector by making certain compensating 

deviations in a smaller, auxiliary reflector of the telescope. At 

least one intermediate element forms an image of the primary 

surface onto the secondary surface, so each point on the secondary 

surface corresponds to a point on the primary surface. The 

secondary surface is formed with a deviation from an ideal 

secondary surface, with the piston distance of each point on the 

actual secondary surface equal to the piston distance of a 

corresponding piston on the actual primary surface from the ideal 

primary surface. It is found that this results in electromagnetic 

(e.g., light) rays which strike a deviating area of the actual primary 

surface being brought to the same focus as if the actual primary 

surface did not have a dviation from an ideal primary surface. 

NASA 

29 May 1986 

31 
76 SOLID-STATE PHYSICS 

76 

SOLID-STATE PHYSICS 

Includes superconductivity. 

N86-25269'# National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

METHOD OF MEASURING FIELD FUNNELING AND RANGE 

STRAGGLING IN SEMICONDUCTOR CHARGECOLLECTING 

JUNCTIONS Patent Application 

J. A. ZOUTENDYK, inventor (to NASA) 19 p 

(Contract NAS7-918) 

(NASA-CASE-NPO-16584-1-CU; NAS 1.71 :NPO-16584-1-CU; 

US-PATENT-APPL-SN-802769) Avail: NTlS HC AO2/MF A01 

CSCL 20L 

Electric-field funneling length is measured while irradiating a 

semiconductor charge-collecting junction with electron-hole-pair 

generating charged particles at a first junction bias voltage. The 

bias voltage is then reduced to a second level in order to reduce 

the depth of the depletion region such that the total charge can 

no longer be collected by drift and measured in the energy band 

previously displayed in the multichannel analyzer. This is 

representative of the maximum electric field funneling length which 

may be calculated by measuring the difference at the second 

bias voltage level of the depletion width and the ion penetration 

range. The bias voltage is further lowered to a third level at which 

the particles are collected over a spread of energy levels while at 

least some of the particles are still collected at the selected energy 

level. From this the different depths of penetration of the particles 

are determined while additional effects due to diffusion are 

minimized. NASA 

27 Nov. 1985 

I I 

N86-28760' National Aeronautics and Space Administration. 

Pasadena Office, Calif. 

METHOD OF MAKING MACROCRYSTALLINE OR SINGLE 

CRYSTAL SEMICONDUCTOR MATERIAL Patent 

P. J. SHLICHTA, inventor (to NASA) and R. J. HOLLIDAY, inventor 

(to NASA) 24 Jun. 1986 4 p Filed 10 Feb. 1983 Supersedes 

N83-21993 (21 - 11, p 1796) 

(NASA-CASE-NPO-15904-1; US-PATENT-4,596,626; 

US-PATENT-APPL-SN-465369; US-PATENT-CLASS-1 56-61 0; 

US-PATENT-CLASS-1 56-DIG.88; US-PATENT-CLASS-1 56-624) 

Avail: US Patent and Trademark Office CSCL 20L 

A macrocrystalline or single crystal semiconductive material is 

formed from a primary substrate including a single crystal or several 

very large crystals of a relatively low melting material. This primary 

substrate is deposited on a base such as steel or ceramic, and it 

may be formed from such metals as zinc, cadmium, germanium, 

aluminum, tin, lead, copper, brass, magnesium silicide. or 

magnesium stannide. These materials generally have a melting 

point below about 1000 C and form on the base crystals the size 

of fingernails or greater. The primary substrate has an epitaxial 

relationship with a subsequently applied layer of material, and 

because of this epitaxial relationship, the material deposited on 

the primary substrate will have essentially the same crystal size 

as the crystals in the primary substrate. If required, successive 

layers are formed, each of a material which has an epitaxial 

relationship with the previously deposited layer, until a layer is 

formed which has an epitaxial relationship with the semiconductive 

material. This layer is referred to as the epitaxial substrate, and 

its crystals serve as sites for the growth of large crystals of 

semiconductive material. The primary substrate is passivated to 

remove or otherwise convert it into a stable or nonreactive state 

prior to deposition of the seconductive material. 

Official Gazette of the U.S. Patent and Trademark Office 

82 

DOCUMENTATION AND INFORMATION SCIENCE 

Includes information storage and retrieval technology; micrography; 

and library science. 

N86-25292'# National Aeronautics and Space Administration. 

Langley Research Center, Hampton, Va. 

BRAILLE READING SYSTEM Patent Application 

H. D. GARNER, inventor (to NASA) 31 Mar. 1986 11 p 

Sponsored by NASA 

US-PATENT-APPL-SN-846430) Avail: NTlS HC AO2/MF A01 

CSCL 058 

A Braille reading system wherein the display of characters is 

controlled by moving a position sensor is developed. A text 

recorded on a cassette tape is removed by a cassette player 

under the control of loading logic. The logic controls the cassette 

player to remove one or two pages of the text at a time. The 

removed text is stored in buffer memory. One character at a time 

is retrieved from memory and received by solenoid drivers. These 

drivers control a series of solenoids and pins to present a standard 

Braille representation of the character selected. The Braille display 

is mounted on a mouse which may be manually moved by the 

operator. When the mouse is moved, an optical pickoff determines 

the amount of movement of the mouse and forwards signals to 

an up down counter to record its position. When the mouse is 

moved a predetermined distance, the character to be displayed is 

changed to the next character in the text. NASA 

(NASA-CASE-LAR-13306-1; NAS 1.71 :LAR-13306-1; 

I I. 

1- I 

32 
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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 availability 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 subscriber. 
NASA Case 

Number 

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 

LE W-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 

21000 Brookpark Road 

Cleveland, Ohio 44135 

Telephone: (216) 433-5753 

Lyndon 8. 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 ADYINISTRATION 

14 CFR Part 1245 

Lkenilng of NASA Inventions 

AQENCV: National Aeronautics and 

Space Administration. 

ACTION: Interim regulation with 

comments requested. 

SUYYARV: This National Aeronautics 

and Space Administration (NASA) is 

revising its patent licensing regulations 

to conform with Pub L. 96-517. This 

interim regulation provides policies and 

proreclurcs applicable to the IicenRing of 

federally owned inventions in the 

custody of the National Aeronautics and 

Spa( c' Administration. and implements 

Puh L 96-517. The object of this subpart 

is to use the patent system to promote 

the utilization of inventions arising from 

NASA supportcd research and 

development. 

EFFECTIVE DATE: july 1.1981. Coniments 

must be received in writing by 

December 2.1981. Unless a notice is 

published in the Federal Register after 

the conimeiit period indicating changes 

to be made, this interim regulation shall 

become n final regulation. 

ADDRESS: Mr. John G. hlannix. Director 

of Patent Lirenshg, GP-4. NASA, 

Washington. D.C. 20546. 

Mr john G Mannix, (202) 755-3954. 

FOR FWTHER INFORNATlON COLIIACI: 

SUPPUMEICIARV IWTO(IYATK)W: 

PART 1245-PATENTS AND OTHER 

INTELLECTUAL PROPERTY RIGHTS 

Subpart 2 of Part 1245 is revised to 

read as follows 

..... 

cubpw(2-u--ml~n*sl\ 

lnventbn 

Set 

1245.3XJ Scope nf subpart. 

1245 201 Po!icy end objective. 1245 202 Definitions. ?245 ZIJ~ Aorhority to grnnt licenqcs. 

Resfrictions and caodilions 

1245 2111 

sithpart. 

Type of LiLcnser 

1L45 20s Nonexclusive licenses. 

1245 u)b; Exclusive and partially exclusive 

All licenses grznled tinder this 

hensrs. 

Procedurws 

1245 207 

1245 208 Proccssing bpplicationr. 1245.209 Nl~tice lo Attorney General 

Application for a license. 

1245 210 Modification and termination of 

licenses 

1245 211 Appeals. 

212 Protection and iidminictration uf 

invenlions. 1245.213 Tmiisfer of custody. 

1245 214 Confidentiality of information. 

51.11 3023 and 3024. 

Authority: 35 U.S.C. Section 207 and 2M). BI 

..... 

Sum 2-Lk~nolng of NASA 

Inventions 

f 1245.100 Sc- of subpart. 

This subpart prescribe6 the terms. 

ronclitione. and procedures upon which ti NASA invention may be licensed. It 

does not affect licenses which (a) were in effect prior to July 1.1881; [b) may 

exist at the time of the Government's 

acqiiisition of title to the invention. 

including those resulting from the 

allocation of rights to inventionr made 

under Government resrarch and 

development contracts; (c) are the result 

of nn authorized exchange of rights in 

the settlement of putent disputes: or (d) are otherwise authorized by law or lrenty. 

§ 1215.201 Poky and obMthw. 

It is the policy and objective of thin 

subpart to use the patent system to 

promote the utilization of inventionr 

arising from NASA supported research 

and development. 

412ac.202 D-O~S. 

(a) "Federally owned invention" means an invention, plant. or deslgn 

which is covere-d by a patent, or patent 

application in the United States. or a 

patent. patent application. plant variety 

protection. or other form of protection, 

in a foreign country. title to which hai 

been assigned to or otherwire vested m 

the United States Government. 

executive 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. titlr or interest in such 

inv~ntion on behalf of the United States 

Government. 

(d) "Small business firm" means a small business concern as defined at 

section 2 of Pub. L 85-536 (15 U.S.C. 632) 

and implementing regiilations of the 

Administrator of the Small Business 

Admlnistration. For the purpose of these 

regulations. the size itandard for small 

business concerns involved in 

Gobernrnent procurement. contained in 

(b) "Federal agency" means an 

(c) "NASA Invention" means a 

13 (.I R 121 3-8. and in subcontracting. 

contamed in 13 CFR 121.3-12. will be 

used 

(e) Practical application" means to 

manufacture in the caae of a 

composition or product. to practice in 

thr cdse of a process or method, or to 

operate in the case 01 a machine or system; and. in each case, under ruch 

conditions as to establish that the 

Invention is beiry utilized and that ita 

benefits are to the extent permitted by 

law or Government mgulatians 

available to the public on rerronablc 

terms. 

States of America, ita territories and 

possessions, the District of Columbia. 

and the Commonwealth of Puerto Rim. 

0 1245.203 nuthocity to gmnl Wcmroa 

available for licenang as deemed 

appropriate in the public interest. NASA 

may grant nc~nexclurive, partially 

exclusive, or exclusive licenses thereto 

under this subpart on inventions in its 

custody. 

Restrictions and Cunditioas 

Q 124~2~ AM wnan gmnbd under thb 

rubpart. 

(a) Reshctim. (1) A licerue may be 

granted only if the applicant has 

supplied NASA witb a satisfactory plan 

for developmeat or marketing of the 

invention, or both, and with information 

about the applicant's capability to fulfii 

the plan. 

(2) A Uccnse granting *ts to use or sell under a NASA invention in the 

United States shall normally be granted 

only to a licensee who agrees that any 

products embodying the invention or produced through the use of the 

invention will be manufactured 

subst~ntinlly h the United States. 

(b) Conditions. Licenses shalJ contain 

such terms and conditirxy I NASA 

determines are appropriatJfor the 

protection of the interests of the Fderal 

Government and the public and are not 

in conflict witb law or this subpert The 

followily terms and conditions apply to 

any license: 

for a period specified in the license 

agreement, 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 bf the !icenrcc 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 the licensee's business to which 

the invention pertains. 

(fj "United Statas" means the United 

NASA inventionr rhd be made 

(1) The duration of the licenee shall be 

(3) The license may extend to 
PATENT LICENSING REGULATIONS 

(41 The license may provide the 

licensee the right to grant sublicenses 

undcr the licensefsublect to the 

dpproval of NASA. Ench sublicense 

shall mdke reference to the license. 

includmg 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 mmketing of the 

invention, or both, to bring the invention 

to practical appllcation 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 licensee shall normally require 

royaltier or other consideration. 

(8) Where an agreement is obtained 

pursuant to i 1245.204(a)(2) that any 

products embodying the invention or produced through use of the invention 

will be manufactured substantially in 

the United Statee. 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 determines that the licensee 

is not executiq the plan submitted with 

its request for I license 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 effective steps to 

achieve practical application of the 

invention: 

is necessary to meet requirements for 

public use specified by Federal 

regulations isnued after the date of the 

license and such requirements are not 

reasonably satisfied by the Iicennee; 

[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 Licensee 

0 1245.205 IlocnXCbIW IkOWS. 

(a) A vaihbility of licenses. 

Nonexclusive licenses may be granted 

under NASA inventions without 

publication of availability or notice of a 

prospective license. 

(bj Condifions. In addition tu the 

provisions of 0 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 reasonably 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. 

0 f245.106 Exduslve and p.r(klly 

rxcluslvr Ucenres. 

(a) Domestic licenses. 

(1) Availobility of licenses. 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 Register; or [ii] without such 

notice where NASA determine: that 

expeditious granting of such a license 

will best serve the interests of the 

Federal Government and the public; and 

(iii) in either situation, specified in 

(a)(l)[i) or (ii) of this section only if: 

(A) Notice of a prospective license, 

identifying the invention and the 

prospective licensee. has been published 

in the Federal Register. providing 

opportunity for filing written objections 

within a 60-day period; 

(B) After expiration of the period in 

0 1245.206(a) (I)(iii)(A) and 

consideration of nay written objections 

received during the perlod. NASA has 

determined that: 

Government and the publiowill best be 

scned by the proposed license. in view 

of the applicant's intentions, plans, and 

tlbility to bring the invention to ractical 

invention's utilization by the public: 

(2) The desired practial application 

has 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 

application or otherwise promo P e the 

(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's 

utilization by the public: and 

(4) 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 plans submitted by 

applicants that are not small business 

firms. 

(2) Conditions. In addition to the 

provisions of 0 1245.204, the following 

terms and conditione apply to domestic 

exclusive and partially exclusive 

licenses: 

(i) The license shalI be subject to the 

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 responslble applicants, on reasonable terms, when necessary to 

fulfill health or safety needs. 

(iii) The license ohall be subject to any 

licenses in force at the time of the grant 

of the exclusive or partially exclusive 

license. 

the right of enforcenient 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 

(iv) The license may grant the licensee 

(b) Foreign licenses. 

(1) Availability 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 

prospective 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 

rection of the United States in any line 

of commerce to which the technology to 

be licensed relates. or to craate or 

maintain other situationr inconriatent 

with antitrust laws. 

(2) Conditions. In addition to the 

provisions of i 1245.201, the followins 

terms and conditions apply to foreign 

exclusive and partially exclusive 

licenses: 

irrevocable, royalty-free right of the 

Government of the United States to 

practice end 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 be subject to any 

licenses in force at the time of the grant 

of the exclusive or partially exclusive 

license. 

(iii) The license may grant the licensee 

the right to take any suitable and 

necessary actions to protect the licensed 

property. on behalf of the Federal 

Government. 

(c) Record of determinations. NASA 

shall maintain a record of 

determinations to grant exclusive or partially exclusive licenses. 

Rodurn 

(ii) NASA has considered whether the 

(i) The license shall be subject to the 

fi 1245.207 AppUc.nOn tor a krm. 

An application for a license should bo 

addresred to the Patent Counsel at the 

NASA installation having responribility 

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 license 

for which the application is submitted; 

(c] Name and address of the person, 

company, or organization applying for 

the license and the citizenship or place 

of incorporation of the applicant; 

(Jb Name. address. and telephone 

number of representative of applicant (0 

whom correspondence should be rent; 

(e) Natura and type of applicant's 

businers. identifying products or services which the applicant has 

successfully commeicirlised. and 

appmxlmtr number of appliunt'r em loyoe~ (6 source ot information mncemiq 

the avaUaWty of a liconso on tho 

invention; 

(e) A rtatment indlcrthq whether 

applicant la a mull bwinru firm as 

defined in i 1Uaac); 

(h) A detailed descriptloa of 

applicant'r plan for bvelopment or 

marketin8 of tho iavontloa, or both 

which should indudc 

amount of antldpatd investment of 

capital and other reaourcer whlch 

applicant believes will be requlred to 

bring the invention to practical 

applicatioa; 

(2) A statement aa to applicant's 

capability and intentlon to fulfill tho 

plan. indudtry Infommtlon regmanufacturing, market@ financial. and 

technical reaourceL; 

which applicant Intenda to practice the 

invention; and 

(4) A statement of the gwgraphlc 

areas in which applicant iutradr to 

manufacture any products rmktodyh~ 

the invention and #eo#mphlc -88 

where applicant Intends to w or SOU 

the invention, or bo& 

(i) Identification of liconaor pmvlously 

granted to applicant der Fdually 

owned Inventioonr; 

(j) A statement cont.iahg applicant's 

best Imowledge of the oxtent to whlch 

the invenhon is beii practiced by 

private industry or Government or both or is otherwho available mmraercldl~ 

and 

applicant believer wlU ru 

determination to grant the come to 

applicant. 

)1248.2om Procesw*- 

(a) Appllcationa for licenser will be 

initially revlewd by the P8ht Counsel 

of the NASA InrtaUaUon havb 

nrponsibility for the inventlon. "be 

Patent Counsel shall make a preUmlnary 

recommendation to tho Dlrwctor of 

Licensiq, NASA Headquarten, whethu 

to: (1) grant the llcenm as requestad. (2) 

grant the license with modification after 

negotiation with the licensee. or (3) deny 

the license. The Director of Licensing 

shall review the preliminary 

recommendation of the Patent Counsel 

and make a final mmmendaHon to the 

NASA Assistant General Counsel for 

Patent Matters. Such review and final 

rewmmend8Hon may include, and be 

based on. any additional information 

obtained from applicant and other 

sources that the Patent Counsel and the 

(1) A statement of tho time. IU- and 

(3) A rtat-nt Of the field8 Of UIC fOr 

(It) Any other Infomution which 

'E"' 

Director of Ucenriq doan rdcvant to 

the license requerted. Tho determination 

to pant or dmy tho li- rhaU be 

made by tlw Assistant General Counsel 

rot paw Matterr bared on th. final 

recommendation of th Director of 

Ucendq. 

(b) When notice of a prospactlve 

exclusiw a putialb .rdUrlvo Ucrnrr 

ir published In the PM R.drc.r Ln 

accord.IIcI with t I~mHlMlUMA) 

or i luawS(bHlMi)! any writton 

objectioos redd m nrpoalr thereto 

will bo coaribnd by th Mmta of 

recommendatha to the Assistant 

General couwl for Patent Mattar. 

(c) If tho requostod liemu. Mudln) 

any nelptiatod Iwdifiutloa* is dmld 

by the Assistant General couwl for 

Patent Mattar. the rppliunt my 

request recoosideration by filiq a 

written request for reconrideration 

within 30 days after receiving notice of 

denial. This 3hday period may be 

extended for good cause. 

(d) In addition to, or in lieu of 

requesting reconrideration. the 

applicant may ah appeal the denid of 

the license in accordance with 

i 1246.2ll. 

1 124Noa Motice to A#otney Olllsral. 

A copy of the notice provided for in 

8 1Z45.zoS(a)(l)(iii)(A), and 

ius.Z06(b)(l)[i) will be sent to the 

Attorney Coned 

1 12U)lO Modlfloation and WnnhUon of 

kumos. 

license. other than by mutual aIp.ecment 

NASA shall furnlrh the licenree and any 

sublicewee of record a written notice of 

intention to modUy or terminate the 

license, and the licensee and any 

sublicenoso shall b allowed 90 days 

after such notice to remedy any breach 

of the licecue or rhow cause wby the 

license should not be modified or terminated 

#124&811 hppe&. 

(a) Iho followiq putter may appeal 

to the NASA Adminirtrator or dareany decision or determination 

concemtq the pant. denial. 

interpretation. modification, or termination of a license: 

(I) A person whow application for a 

license has been denied; 

(2) A Ilcansea whoso license has been 

modified or terminated, in whole or In 

part or (3) A person who timely filed a 

written objection In response to the 

notice required by I i 124Szoa(a)(l)(iii)(A) or 

fhlUitJ8 th. fid 

Before modifyQ or terminating a 
PATENT LICENSING REGULATIONS 

1245.Zoe(b)(l)(i) and who can 

demonstrate to the satisfaction of NASA 

that such person ma- damaged by 

the Agency action. 

(b) Written notiu, of appeal murt be 

filed within 30 days (or such other time 

as may be authorized for ,pod cause 

shown) after receiw notice of the 

adverse decision or determination; 

Indud@ an adverse decision following 

the requert for reconsideration under 

I 1245.208(c). The notice of appeal, 

along with all supportiq documentation 

should be addressed to the 

Adminirtralor, National Aeronautics 

and Space Admlnistration, Washington. 

DC 20548. Should the appeal raise a genuine dispute over material fad, factfinding will be conducted by the NASA 

Inventions and Contributions Board. The 

pereon filing the appeal shall be 

afforded an opportunity to be heard and 

to offer evidence in support of the 

appeal. The Chairperson of the 

Inventions and Contributions Board 

rhall prepare mitten findings of fact 

and transmit them to the Administrator 

or designee. The decirion 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. 

8 1245.212 Prohction and admlnistntion 

ol imentionr. 

NASA may take any suitable and 

necessary steps to protect and 

administer rights to NASA inventions. 

either directly or through contract. 

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. 

1 1245.214 cOntid.ntwCty Of infWMtlon 

Title 35. United States Code, section 

209, provides that any plan submitted 

pursuant to 0 1245.207(h) and any report 

required by 0 1?.45.zw(b](e] may be 

treated by NASA as commercial and 

1 i24saia tnn~t.r of custody. 

financialinformation obtained from a 

person and privileged and confidential 

and not subject to disclosure under 

section 552 of Title 5 of the United 

States Code. 

I.- M. wwl 

Administrator. 

October 15.1981. 

pn Dor MJleOD Pi*d 10-~0-P: &* .nq 

ULUNO cool! nNJM 
1. Report No. 

NASA SP-7039 (30) 

2 Government Accession No. 3. Recipient's Camlag No. 

~~ ~ 

4. Title and Subtitle 

NASA Patent Abstracts Bibliography 

A Continuing Bibliography 

Section 1: Abstracts (Supplement 30) 

7. AuthodsJ 

5. Report Date 

January 1997 

8. Performing Organization Report No. 

6. Performing Organization Code I 

21. No. of Pages 

50 

22. Rice' 

A03/HC 

National Aeronautics and Space Administration 

Washington. D.C. 20546 

10. Work Unit No. 

11. Contract or Grant No. 

13. Type of Report and Period Covered 

14. Sponsoring Agency Code 

15. su~ernentarv NoSection 1: Abstracts 

16. Abstract 

Abstracts are provided for 105 patents and patent applications entered into the 

NASA scientific and technical information system during the period July 1986 

through December 1986. Each entry consists of a citation, an abstract, and in 

most cases, a key illustration selected from the patent or patent appl ication. 

~~ 

17. Key Words (SuQgested by Authoris) J 

Bib1 iographies 

Patent Pol icy 

NASA Programs 

18. Distribution Statement 

Unclassified - Unlimited 

19. Security Classif. (of this report) 

Unclassified 

20. Security Clanif. (of this page) 

Uncl ass i f ied I 

I 

For sale by the National Technical Information Service, Springfield, Virginia 221 61 NASA-L~~+,,, 1987