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  • Other Sources  (366)
  • ELECTRONICS AND ELECTRICAL ENGINEERING  (191)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (175)
  • 1980-1984  (366)
  • 1950-1954
  • 1982  (366)
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  • Other Sources  (366)
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  • 1980-1984  (366)
  • 1950-1954
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  • 1
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    Measurements by the plasma diagnostics package on STS-3 (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A comprehensive set of measurements about the orbiter environment are provided by the plasma diagnostics package (PDP). Ion and electron particle densities, energies, and spatial distribution functions; ion mass for identification of particular molecular ion species; and magnetic fields, electric fields and electromagnetic waves over a broad frequency range are studied. Shuttle environmental measurements will be made both on the pallet and, by use of the remote manipulator system (RMS), the PDP will be maneuvered in and external to the bay area to continue environmental measurements and to carry on a joint plasma experiment with the Utah State University fast-pulsed electron generator. Results of orbiter environment EMI measurements and S-band field strengths as well as preliminary results from wake search operations indicating wake boundary identifiers are reported.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 8 p
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  • 2
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    Design and development of the ERBE data management system (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The Earth radiation budget experiment (ERBE) software development approach is described. An iterative development approach was adopted which provides for three releases or versions of the processing system, each of increasing levels of complexity and solidity. The final release of the system will be used to process the flight data. The major phases for each iterative release consist of specifications developed in concert with the science team, preliminary design, subsystem reviews, coding, subsystem code walkthroughs, system testing, system documentation, and project status review.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 15 p
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  • 3
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    Outgassing: Its effects on spacecraft. Vibration damping materials (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The correlation of outgassing to the stability of the damping properties of polymer materials to be used in spacecraft structures is discussed. A test series was devised to obtain basic information from off-the-shelf damping materials. The test results could be considered as a guideline toward the application of these materials. Eight materials were selected to form a representative cross section of those polymers having both ready availability as commercial damping materials and desirable properties. A table indicates the temperatures at which peak damping occurs at 1 Hz and the type of beam specimen used in the vacuum exposure tests. These materials as a group cover the temperature range of -85 C to 38 C.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 25 p
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  • 4
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    A facility for the simulation of low orbit atmospheric oxygen bombardment (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A molecular beam facility to simulate the space environment of a spacecraft at low orbit was designed with the intent of studying the effect on the properties of optical elements of oxygen atoms impacting at orbital velocity. The four-stage differentially pumped molecular beam facility includes a variety of oxygen atom beam sources which cover a wide range of velocities (1 km/sec to approximately 8 km/sec), in addition to the ultra-clean experimental environmental of an ultra-high vacuum chamber and an optical diagnostic set-up. The primary oxygen atom beam source used to obtain the 8 km/sec O atoms is an arc heated source. It consists of a modified commercially available plasma torch. The modifications include attachments which provide for a nozzle which is used to expand the atomic beam into the vacuum system, and exhaust channels to dispose of excess torch gas. The torch operates in the 'nontransferred' mode of operation, that is the electric arc is confined within the torch. A plasma is formed in helium by a dc arc. A small amount of O2 is injected downstream from the arc where it is thermally dissociated by the hot He into oxygen atoms. The high temperature and isentropic expansion give the oxygen atoms their velocity. Using seeded beam techniques, oxygen atom beams of approximately 3.5 and approximately 1.5 km/sec, respectively, are obtained.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 1 p
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  • 5
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    Space Shuttle preliminary. Contamination assessment from STS-1 and STS-2 (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A preliminary assessment of the space shuttle contamination environment was made using data from the first two orbital flight tests, STS-1 and STS-2. Data sources consisted of crew observations during flight, postflight vehicle inspection, and the induced environment contamination monitor which was used on STS-2 and consists of 10 instruments. These instruments are used to measure gas phase contaminants, particle population, humidity, and molecular deposition in the orbiter payload bay during ascent and descent and particle population, molecular deposition, and gas cloud during orbital flight. Results of the measurements described are presented in summary form and indicate low molecular deposition rates for both pressurized and orbital flight.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 21 p
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  • 6
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    Environmental test facilities used in Europe for ESA satellite programmes (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The structure of the European Space Agency (ESA) is described. The major test facilities used for ESA programs are described. Facility characteristics and special test methods are described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 28 p
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  • 7
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    Education and training of personnel in space simulation (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The training program and procedures developed and implemented at the space simulation laboratory at Martin Marietta Aerospace in Denver are discussed. The training of technicians and professionals as well as preparation for instructors is covered. Training manuals and their compilation are reported as applicable to the specific needs of the laboratory. The development of a space simulation course as part of the Martin Marietta Continuing Education Night School approaching space simulation from an academic viewpoint is presented. Finally, public relations tours of the facility as an informational/educational tool are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 5 p
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  • 8
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    Cryopump for large pulses of hydrogen (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A test involving a flow of hot hydrazine decomposition products at a rate of 13.6 g/s (0.03 lb/s) established the requirement to maintain pressure in an 11.9-m-(39 ft) diameter space chamber below 200 microns. The flow, 2/3 hydrogen and 1/3 nitrogen by volume, continued for several periods ranging from 3 to 15 min. The pressure requirement was necessary to minimize thermal effects of the gas on the test vehicle but was well beyond the capability of the existing facility pumps. Various methods of obtaining additional temporary jump capacity were considered. From these, the slugged-charcoal approach was selected as the quickest and least expensive method to implement.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 23 p
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  • 9
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    Spacecraft thermal balance testing using infrared sources (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A thermal balance test (controlled flux intensity) on a simple black dummy spacecraft using IR lamps was performed and evaluated, the latter being aimed specifically at thermal mathematical model (TMM) verification. For reference purposes the model was also subjected to a solar simulation test (SST). The results show that the temperature distributions measured during IR testing for two different model attitudes under steady state conditions are reproducible with a TMM. The TMM test data correlation is not as accurate for IRT as for SST. Using the standard deviation of the temperature difference distribution (analysis minus test) the SST data correlation is better by a factor of 1.8 to 2.5. The lower figure applies to the measured and the higher to the computer-generated IR flux intensity distribution. Techniques of lamp power control are presented. A continuing work program is described which is aimed at quantifying the differences between solar simulation and infrared techniques for a model representing the thermal radiating surfaces of a large communications spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 26 p
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  • 10
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    Optical characterization of solar concentrator mirrors using the solar beam of the JPL 25-foot space simulator (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The Jet Propulsion Laboratory 25-foot space simulator with its 5.8-m (19-ft) diameter simulated solar beam provides an excellent facility for measuring the optical characteristics of parabolic solar concentrator panels and gores. The virtual source position and size were determined by using a single lamp of the 37 xenon 30-kW source array with only the center lens in the 19-channel optical mixer. This data was used to define the optical test geometry, and it allowed accurate measurement of focal length and surface deviations of the mirror under test. A flux distribution of a typical solar concentrator placed directly on the solar beam gives measurements of performance at the focal point of the parabolic surface.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 19 p
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  • 11
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    Detection and analysis of radio frequency lightning emissions (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The feasibility study of detection of lightning discharges from a geosynchronous satellite requires adequate ground-based information regarding emission characteristics. In this investigation, a measurement system for collection of S-band emission data is set up and calibrated, and the operations procedures for rapid data collection during a storm activity developed. The system collects emission data in two modes; a digitized, high-resolution, short duration record stored in solid-state memory, and a continuous long-duration record on magnetic tape. Representative lightning flash data are shown. Preliminary results indicate appreciable RF emissions at 2 gHz from both the leader and return strokes portions of the cloud-to-ground discharge with strong peaks associated with the return strokes.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program; 20 p
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  • 12
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    The design and evaluation of superconducting connectors (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The development of a superconducting connector for superconducting circuits on space flights is described. It is proposed that such connectors be used between the superconducting readout loop and the SQUID magnetometer in the Gravity Probe B experiment. Two types of connectors were developed. One type employs gold plated niobium wires making pressure connections to gold plated niobium pads. Lead-plated beryllium-copper spring contacts can replace the niobium wires. The other type is a rigid solder or weld connection between the niobium wires and the niobium pads. A description of the methods used to produce these connectors is given and their performance analyzed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program; 10 p
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  • 13
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    Fuel optimal maneuvers for spacecraft with fixed thrusters (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Several mathematical models, including a minimum integral square criterion problem, were used for the qualitative investigation of fuel optimal maneuvers for spacecraft with fixed thrusters. The solutions consist of intervals of "full thrust" and "coast" indicating that thrusters do not need to be designed as "throttleable" for fuel optimal performance. For the primary model considered, singular solutions occur only if the optimal solution is "pure translation". "Time optimal" singular solutions can be found which consist of intervals of "coast" and "full thrust". The shape of the optimal fuel consumption curve as a function of flight time was found to depend on whether or not the initial state is in the region admitting singular solutions. Comparisons of fuel optimal maneuvers in deep space with those relative to a point in circular orbit indicate that qualitative differences in the solutions can occur. Computation of fuel consumption for certain "pure translation" cases indicates that considerable savings in fuel can result from the fuel optimal maneuvers.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program; 21 p
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  • 14
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    Attitude control of the space construction base: A modular approach (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A planar model of a space base and one module is considered. For this simplified system, a feedback controller which is compatible with the modular construction method is described. The systems dynamics are decomposed into two parts corresponding to base and module. The information structure of the problem is non-classical in that not all system information is supplied to each controller. The base controller is designed to accommodate structural changes that occur as the module is added and the module controller is designed to regulate its own states and follow commands from the base. Overall stability of the system is checked by Liapunov analysis and controller effectiveness is verified by computer simulation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program; 35 p
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  • 15
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    Automating a residual gas analyzer (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A residual gas analyzer (RGA), a device for measuring the amounts and species of various gases present in a vacuum system is discussed. In a recent update of the RGA, it was shown that the use of microprocessors could revolutionize data acquisition and data reduction. This revolution is exemplified by the Inficon 1Q200 RGA which was selected to meet the needs of this update. The Inficon RGA and the Zilog microcomputer were interfaced in order the receive and format the digital data from the RGA. This automated approach is discussed in detail.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 16 p
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  • 16
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    Remote sensing of tornadic storms from space (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: By using infrared images obtained from GOES satellite, the digital count values of pixels representing blackbody temperatures of the cloud top, convective storms are observed throughout their life cycles. Clouds associated with a tornadic storm are compared with those without a tornadic storm to illustrate how the infrared and visible observations from a geosynchronous satellite can be used to study the differences in their life cycles.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 11 p
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  • 17
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    Environmental noise assessment STS-1 Columbia launch (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: An environmental noise assessement of the initial launch of the Space Transportation System, STS-1 Columbia was conducted. The principal objective of the environmental noise assessment was to measure the noise generated during the initial launch of the space shuttle to ascertain the validity of the levels predicted in the 1979 environmental impact statement. In the 1979 study information obtained for expendable launch vehicles, Titan, Saturn and Atlas was used to predict the noise levels that would be generated by the simultaneous firing of the two solid rocket boosters and the three space shuttle main engines. Fifteen monitoring sites were established in accessable areas located from 4,953 to 23,640 meters from the launch pad. Precision sound level meters were used to capture the peak level during the launch. Data obtained was compared to the predicted levels and were also compared to the identified levels, standards and criteria established by the federal agencies with noise abatement and control responsibilities.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 16 p
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  • 18
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    Improved multilayer insulation applications (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Multilayer insulation blankets used for the attenuation of radiant heat transfer in spacecraft are addressed. Typically, blanket effectiveness is degraded by heat leaks in the joints between adjacent blankets and by heat leaks caused by the blanket fastener system. An approach to blanket design based upon modular sub-blankets with distributed seams and upon an associated fastener system that practically eliminates the through-the-blanket conductive path is described. Test results are discussed providing confirmation of the approach. The specific case of the thermal control system for the optical assembly of the Space Telescope is examined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 8 p
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  • 19
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    Durability of spacecraft materials (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Research efforts are reviewed on the space durability of materials, including radiation effects on polymer matrix composites and films, dimensional stability of polymer matrix composites and tension-stabilized cables, and thermal control coatings. Research to date has concentrated on establishing a fundamental understanding of space environmental effects on current graphite-reinforced composites and polymer systems, and development of analytical models to explain observed changes in mechanical, physical, and optical properties. As a result of these research efforts, new experimental facilities have been developed to simulate the space environment and measure the observed property changes. Chemical and microstructural analyses have also been performed to establish damage mechanisms and the limits for accelerated testing. The implications of these results on material selection and system performance are discussed and additional research needs and opportunities in the area of tougher resin/matrix and metal/matrix composites are identified.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Advan. Mater. Technol.; p 357-380
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  • 20
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    Smokeless wire insulation (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA Technol. Appl. Team; p 37
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  • 21
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    Integrating 128 element InSb array - Recent results (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: There has been a continuing evolution toward larger arrays of infrared detectors, and the technology base derived from the Galileo Near Infrared Mapping Spectrometer (NIMS) has been expanded to linear arrays including from 128 to 512 elements. This advance is based on the commercial availability of high-quality InSb photodiodes and 128/256 element FET switch MUX's (multiplexing elements). The present investigation is concerned with an experimental 128-element linear imager using InSb detectors and silicon MUX for readout. Attention is given to detector array electrical characteristics, the detector readout architecture, noise, and special effects.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
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  • 22
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    The containment set approach to digital system tolerance of lightning-induced transient faults (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A fault model and a system model are necessary to assess the tolerance or resilience of a digital system to lightning-induced transients. It is noted that these models are usually developed separately. A new approach is outlined here for this assessment problem which combines the fault and system models into an overall model. With this approach, referred to as the containment set approach, an assessment of the effects of lightning-induced transients can be made in terms of a state transition matrix. This matrix can be generated by means of fault injection experiments. In addition, certain nonredundancy-oriented design alternatives to the achievement of lightning-induced transient tolerance in digital systems are indicated by the containment set approach.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
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  • 23
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    Advanced rocket propulsion technology assessment for future space transportation (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Single-stage and two-stage launch vehicles were evaluated for various levels of propulsion technology and payloads. The evaluation included tradeoffs between ascent flight performance and vehicle sizing that were driven by engine mass, specific impulse, and propellant requirements. Numerous mission, flight, and vehicle-related requirements and constraints were satisfied in the design process. The results showed that advanced technology had a large effect on reducing both single- and two-stage vehicle size. High-pressure hydrocarbon-fueled engines that were burned in parallel with two-position nozzle hydrogen-fueled engines reduced dry mass by 23% for the two-stage vehicle and 28% for the single-stage vehicle as compared to an all-hydrogen-fueled system. The dual-expander engine reduced single-stage vehicle dry mass by 41%. Using advanced technology, the single-stage vehicle became comparable in size and sensitivity to that of the two-stage vehicle for small payloads.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets; 19; July-Aug
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  • 24
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    Effect of storable propellants on single-stage earth-to-orbit vehicles (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A comparison is made between the storable-propellant engine and an equivalent dual-expander engine using oxygen, propane, and hydrogen propellants. The propane and hydrogen dual-expander engine is then compared with previous results with separate propane and hydrocarbon engines. It is shown that the dual-expander reduces vehicle dry mass from 94 to 89 Mg, or 5%. The hydrogen-only thrust of the dual-expander is 0.4 MN, while the separate hydrogen engines have a thrust of 2.3 MN. The low thrust level increases the difficulty of cooling the dual-expander engine, and additional hydrogen flow is added for transpirational cooling. This additional hydrogen flow leads to an increase in the hydrogen tank size. It is also shown that storable propellants increase the dry mass of single-stage earth-to-orbit vehicles by about 20% and the gross mass by about 54%. It is concluded that dual-expander engines should be studied with several thrust splits and thrust levels.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets; 19; May-June
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  • 25
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    SETI downconverter (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The SETI (Search for Extraterrestrial Intelligence) breadboard subsystem was begun in order to develop the technology to efficiently implement a SETI instrument capable of searching wide bandwidth with high resolution. The downconverter covered is the interface hardware between the receiver IF output and ADC used as the input to the spectrum analyzer.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Telecommun. and Data Acquisition Rept.; p 1-5
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  • 26
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    The 400-Hertz constant-speed electrical generation systems (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Materials illustrating a presentation on 400 Hz constant speed generation systems are presented. The system features are outlined, components and functioning described, and display graphics illustrated.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Langley Research Center Elec. Flight Systems; p 125-146
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  • 27
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    Test chips for custom ICs - Six kinds of test structures (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Microelectronic test chips contain a number of test structures that are used for a variety of purposes in fabricating integrated circuits. For convenience, their use is divided into six groups: layout-rule evaluating, process-parameter extraction, device-parameter extraction, circuit-parameter extraction, initial-fabrication failure analysis, and reliability failure analysis. A given test structure can be used to gather information in a number of these groups. Examples are given here of the kinds of parameters that can be obtained in each of these groups. A table is included summarizing various device failures common to bulk CMOS and indicating failure mechanisms appearing after wafer fabrication and after stress.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Circuits Manufacturing; June 198
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  • 28
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    Worst case earth charging environment (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The Applications Technology Satellite-6 (ATS-6) geosynchronous satellite charged up to -2200 V in sunlight on day 178, 1974. This event, being the highest known spacecraft charging event in sunlight, is used to estimate a worst case geosynchronous plasma environment for predicting the spacecraft potential in eclipse. The advantage of using this sunlight spectrum as opposed to an eclipse case is that the ion and electron fluxes to the detectors are shifted only slightly due to the spacecraft potential. After correcting the available data for satellite potential and missing data above 81 KeV, it is found that the plasma can be characterized by a single Maxwellian approximation having an electron density of 1.22/cu cm, electron temperature of 16 KeV, hydrogen ion density of 0.24/cu cm, and hydrogen ion temperature of 29 KeV. In eclipse the spacecraft would have charged up to -28 kV, the highest estimated potential to date in the earth's plasma environment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets; 19; Sept
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  • 29
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    Unsteady aerodynamics and motions of the Pioneer Venus probes (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Helicopter drop tests were made of models of the Pioneer Venus probe descent configurations to characterize their unsteady forces and angular dynamics in equilibrium descent. The axial and normal forces were found to be unsteady in magnitude by about 10 and 5% of the mean axial force, respectively. A cycle of the axial variation takes place in flight distances of from 15 to 40 diameters. The unsteadiness almost certainly is associated with the wake. Angular motions which do not converge to zero angle of attack even in very long duration descent are excited by the unsteady pitching moments. The nearly spherical large probe model was aerodynamically more unsteady than the round-nosed conical small probe model. Data returned from Venus by the Pioneer Venus probes show unsteady axial forces and angular motions similar to those seen in the drop tests.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets; 19; Sept
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    Harmonic analysis approach to the 'TunneLadder' - A modified Karp circuit for millimeter-wave TWTA's (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A field approach to the summed harmonic analysis of the TunneLadder structure, or modified forward-wave Karp circuit, is developed by combining TM(01) and TE(11) modes. Results suggest the suitability of this structure as a high-impedance, about 1-% bandwidth circuit, millimeter-wave forward-wave-type amplifier that is voltage tunable over about a 5-% frequency range and has excellent power handling ability. Theory gives good agreement with experimental results obtained by Karp in omega-beta dispersion and predicts qualitatively the appearances of the antisymmetric mode discussed and of the so called Hightron mode that was discussed earlier in White, Enderby and Birdsall (1964), and Enderby (1964), in addition to the desired symmetric mode.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: IEEE Transactions on Electron Devices; ED-29; May 1982
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  • 31
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    Single event upset sensitivity of low power Schottky devices (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Data taken from tests involving heavy ions in the Berkeley 88 in. cyclotron being directed at low power Schottky barrier devices are reported. The tests also included trials in the Harvard cyclotron with 130 MeV protons, and at the U.C. Davis cyclotron using 56 MeV protons. The experiments were performed to study the single event upsets in MSI logic devices containing flip-flops. Results are presented of single-event upsets (SEU) causing functional degradation observed in post-exposure tests of six different devices. The effectiveness of the particles in producing SEUs in logic device functioning was found to be directly proportional to the proton energy. Shielding was determined to offer negligible protection from the particle bombardment. The results are considered significant for the design and fabrication of LS devices for space applications.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
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  • 32
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    The damage equivalence of electrons, protons, and gamma rays in MOS devices (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The results of laboratory tests to determine the radiation damage effects induced on MOS devices from Co-60, electron, and proton radiation are reported. The tests are performed to establish the relationship between the Co-60 gamma rays and the level of damage to the MOS devices in regards to different damages which can be expected with the electron and particle bombardments experienced in space applications. CMOS devices were exposed to the Co-60 gamma rays, 1 MeV electrons, and 1 MeV protons while operating at 3, 10, and 15 V. The test data indicated that the Co-60 source was reliable for an initial evaluation of the electron damages up to 2 MeV charge. A correction factor was devised for transferring the Co-60 measurements to proton damages, independent of bias and transistor types, for any orbit or environment.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
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  • 33
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    Thermal annealing of radiation damage in CMOS ICs in the temperature range -140 C to +375 C (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Annealing of radiation damage was investigated in the commercial, Z- and J-processes of the RCA CD4007A ICs in the temperature range from -140 C to +375 C. Tempering curves were analyzed for activation energies of thermal annealing, following irradiation at -140 C. It was found that at -140 C, the radiation-induced shifts in the threshold potentials were similar for all three processes. The radiation hardness of the Z- and J-process is primarily due to rapid annealing of radiation damage at room temperature. In the region -140 to 20 C, no dopant-dependent charge trapping is seen, similar to that observed at higher temperatures. In the unbiased Z-process n-channels, after 1 MeV electron irradiation, considerable negative charge remains in the gate oxide.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
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  • 34
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    Annual Conference on Nuclear and Space Radiation Effects, 19th, Las Vegas, NV, July 20-22, 1982, Proceedings (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The results of research concerning the effects of nuclear and space radiation are presented. Topics discussed include the basic mechanisms of nuclear and space radiation effects, radiation effects in devices, and radiation effects in microcircuits, including studies of radiation-induced paramagnetic defects in MOS structures, silicon solar cell damage from electrical overstress, radiation-induced charge dynamics in dielectrics, and the enhanced radiation effects on submicron narrow-channel NMOS. Also examined are topics in SGEMP/IEMP phenomena, hardness assurance and testing, energy deposition, desometry, and radiation transport, and single event phenomena. Among others, studies are presented concerning the limits to hardening electronic boxes to IEMP coupling, transient radiation screening of silicon devices using backside laser irradiation, the damage equivalence of electrons, protons, and gamma rays in MOS devices, and the single event upset sensitivity of low power Schottky devices.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
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  • 35
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    The dependence of single event upset on proton energy /15-590 MeV/ (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Low earth orbit satellite and Jupiter orbiter probe semiconductor devices may incur soft errors or single event upsets, manifested as bit flips, during exposure to such nuclear particles or heavy ions as trapped protons with energies ranging up to 1000 MeV. Experimental data is given on the average proton fluence needed to cause a bit flip as a function of proton energy for isoplanar bipolar TTL RAMs. Error dependence data shape and threshold energy can be related to the existing body of theoretical data on energy deposition following proton nuclear reactions. Experimental data also show that the relative cross sectional amplitude for functionally identical devices can be related to the device's power consumption.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
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  • 36
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    Simple phenomenological modeling of transition-region capacitance of forward-biased p-n junction diodes and transistor diodes (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The derivation of a simple expression for the capacitance C(V) associated with the transition region of a p-n junction under a forward bias is derived by phenomenological reasoning. The treatment of C(V) is based on the conventional Shockley equations, and simpler expressions for C(V) result that are in general accord with the previous analytical and numerical results. C(V) consists of two components resulting from changes in majority carrier concentration and from free hole and electron accumulation in the space-charge region. The space-charge region is conceived as the intrinsic region of an n-i-p structure for a space-charge region markedly wider than the extrinsic Debye lengths at its edges. This region is excited in the sense that the forward bias creates hole and electron densities orders of magnitude larger than those in equilibrium. The recent Shirts-Gordon (1979) modeling of the space-charge region using a dielectric response function is contrasted with the more conventional Schottky-Shockley modeling.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Journal of Applied Physics; 53; Nov. 198
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  • 37
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    ORION downconverter and power supply (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The receiver subsystem supplies the front end assembly (downconverter) and power supply for the ORION Mobile Station. These assemblies are designed to withstand severe environmental conditions. The mechanical, electronic, environmental and maintenance design considerations encountered during the design phase of this project are discussed. The two channel S/X downconverter has a 400 MHz bandwidth channel. Phase stability of 2 and 7 deg at S- and X-bands, respectively, is achieved with a temperature stabilized first local oscillator.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Telecommun. and Data Acquisition Rept.; p 3-9
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  • 38
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    Electric flight systems (1982)
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    Publication Date: 2011-08-18
    Description: Materials used to illustrate a presentation on the development of electric flight systems are presented. Systems concepts are outlined.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Langley Research Center Elec. Flight Systems; p 213-234
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  • 39
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    Electronics materials research (1982)
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    Publication Date: 2011-08-18
    Description: The electronic materials and is aimed at the establishment of quantitative relationships underlying crystal growth parameters, materials properties, electronic characteristics and device applications. The overall program evolves about the following main thrust areas: (1) crystal growth novel approaches to engineering of semiconductor materials; (2) investigation of materials properties and electronic characteristics on a macro and microscale; (3) surface properties and surface interactions with the bulk and ambients; (4) electronic properties controlling device applications and device performance.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Mater. Process Res. Base of the Mater. Process. Center; p 23-46
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  • 40
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    Potential reduction of DSN uplink energy cost (1982)
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    Publication Date: 2011-08-18
    Description: DSN Earth stations typically transmit more power than that required to meet minimum specifications for uplink performance. Energy and cost savings that could result from matching the uplink power to the amount required for specified performance are studied. The Galileo mission was selected as a case study. Although substantial reduction in transmitted energy is possible, potential savings in source energy (oil or electricity) savings are much less. This is because of the rising inefficiency in power conversion and radio frequency power generation that accompanies reduced power output.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Telecommun. and Data Acquisition Rept.; p 151-166
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  • 41
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    A new high-power klystron for the DSN (1982)
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    Publication Date: 2011-08-18
    Description: A very high reliability 100 kW klystron for the Deep Space Network (DSN) high power transmitters in support of spacecrafts to the distant planets was studied. The last phases included electron gun fabrication and beam analyzer evaluation and klystron prototype fabrication, mechanical and electrical design improvements resulted in the delivery of a prototype klystron meeting all requirements. It is concluded that the development of a new high power klystron for the DSN was very successful as demonstrated by the prototype results.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Telecommun. and Data Acquisition Rept.; p 157-173
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  • 42
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    A comparison of radiation damage in transistors from cobalt-60 gamma rays and 2.2 MeV electrons (1982)
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    Publication Date: 2011-08-18
    Description: The total ionizing dose response of ten bipolar transistor types has been measured using Co-60 gamma rays and 2.2 MeV electrons from exposure levels of 750, 1500, and 3000 Gy(Si). Gain measurements were made for a range of collector-emitter voltages and collector currents.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
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  • 43
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    Portable design rules for bulk CMOS (1982)
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    Publication Date: 2011-08-18
    Description: It is pointed out that for the past several years, one school of IC designers has used a simplified set of nMOS geometric design rules (GDR) which is 'portable', in that it can be used by many different nMOS manufacturers. The present investigation is concerned with a preliminary set of design rules for bulk CMOS which has been verified for simple test structures. The GDR are defined in terms of Caltech Intermediate Form (CIF), which is a geometry-description language that defines simple geometrical objects in layers. The layers are abstractions of physical mask layers. The design rules do not presume the existence of any particular design methodology. Attention is given to p-well and n-well CMOS processes, bulk CMOS and CMOS-SOS, CMOS geometric rules, and a description of the advantages of CMOS technology.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: VLSI Design; 1982
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  • 44
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    Off-line, built-in test techniques for VLSI circuits (1982)
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    Publication Date: 2011-08-18
    Description: It is shown that the use of redundant on-chip circuitry improves the testability of an entire VLSI circuit. In the study described here, five techniques applied to a two-bit ripple carry adder are compared. The techniques considered are self-oscillation, self-comparison, partition, scan path, and built-in logic block observer. It is noted that both classical stuck-at faults and nonclassical faults, such as bridging faults (shorts), stuck-on x faults where x may be 0, 1, or vary between the two, and parasitic flip-flop faults occur in IC structures. To simplify the analysis of the testing techniques, however, a stuck-at fault model is assumed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Computer; June 198
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  • 45
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    Analytical and experimental evaluations of Space Shuttle TPS tile vibration response (1982)
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    Publication Date: 2011-08-18
    Description: Analytical studies and laboratory experiments have been performed to evaluate the vibration response of the Space Shuttle Thermal Protection System (TPS) tiles due to the intense rocket generated acoustic noise during lift-off. The TPS tiles are mounted over the exterior of the Space Shuttle Orbiter structure through Strain Isolation Pads (SIP) which protect the tiles from thermal induced shear loads at their interface. The analytical predictions indicate that the response of a typical tile is governed by the structural vibration inputs through the SIP under the tile at frequencies below 250 Hz, and by the direct acoustic excitation over the exterior surface of the tile at frequencies above 250 Hz. An evaluation of the laboratory test data for this same tile, in which conditioned (partial) coherent output spectral analysis procedures were used, leads to exactly the same conclusion. The results demonstrate the power of conditioned spectral analysis procedures in identifying vibration response mechanisms when two or more of the inputs are highly correlated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Sound and Vibration; 83; July 8
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  • 46
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    The measurement of lightning environmental parameters related to interaction with electronic systems (1982)
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    Publication Date: 2011-08-18
    Description: The measurement of electromagnetic fields and related quantities in a lightning environment is a challenging problem, especially at high frequencies and/or in the immediate vicinity of the lightning arcs and corona. This paper reviews the techniques for accomplishing such measurements in these regimes with examples. These sensors are often the same as for the nuclear electromagnetic pulse (EMP), but significant differences also appear.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: IEEE Transactions on Electromagnetic Compatibility; EMC-24; May 1982
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  • 47
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    Partial discharge testing under direct voltage conditions (1982)
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    Publication Date: 2011-08-18
    Description: DC partial discharge (PD) (corona) testing is performed using a multichannel analyzer for pulse storing, and data is collected during increase of voltage and at quiescent voltage levels. Thus high voltage ceramic disk capacitors were evaluated by obtaining PD data interspersed during an accelerated life test. Increased PD activity was found early in samples that later failed catastrophically. By this technique, trends of insulation behavior are revealed sensitively and nondestructively in high voltage dc components.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: IEEE Transactions on Aerospace and Electronic Systems; 18; Jan. 198
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  • 48
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    Modern multistage depressed collectors - A review (1982)
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    Publication Date: 2011-08-18
    Description: The design and performance of the Lewis Research Center (LeRC) electrostatic collector and the associated passive permanent magnetic beam reconditioning (refocusing) are discussed and compared with numerous experimental results on wide- and narrow-band TWT and two klystron cases. Universal designs for efficient collectors for TV klystrons are presented. Collectors other than those based on the symmetric LeRC concept are reviewed only briefly, either because they have not been treated analytically or because only sporadic or incomplete experimental evaluation results are available. It is concluded that significant, a priori predictable performance improvements for TWTs have been demonstrated and that a substantial reduction in the dc power input to TV klystron transmitters could be effected by using well-designed multistage depressed collectors.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: IEEE; vol. 70
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  • 49
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    An optimization technique for lumped-distributed two ports (1982)
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    Publication Date: 2011-08-18
    Description: A frequency domain direct efficient analysis and an optimization technique of a large class of lumped-distributed networks containing active elements are presented. Sensitivity and Hessian matrix calculations are performed using truncated Taylor series expansion of two-port parameters of subnetworks. An interactive computer program was developed to demonstrate the application of the method. Examples of network optimizations are included to illustrate the powerfulness of the technique.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: IEEE Transactions on Microwave Theory and Techniques; MTT-30; Dec. 198
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  • 50
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    A decoupling approach to the control of large spaceborne antenna systems (1982)
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    Publication Date: 2011-08-18
    Description: A simple practical method for designing antenna-feed positioning control systems for large deployable spaceborne antenna systems with flexible booms is proposed. The approach is based on the mechanical decoupling of the antenna-feed from the boom so that the positioning control system can be designed without taking boom dynamics into consideration, thus avoiding a complex infinite dimensional control problem. The basic idea is illustrated by a simple angular positional control system attached to a flexible boom restricted to torsional motion only. The application of this approach to more complex situations is discussed briefly.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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    Intermediate power conditioners - Where are we now? (1982)
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    Publication Date: 2011-08-18
    Description: It has been recognized in the photovoltaic (PV) industry that even in the event of a dramatic reduction in the price of generating PV cells, the costs for the other components of the system represent still a major obstacle towards commercialization. A project was, therefore, initiated with the aim to develop baseline and conceptual power conditioner designs which would attempt to meet a specified set of cost and performance goals in the 30 to 200 kW (Intermediate) size. Resulting Intermediate Size Power Conditioner Studies led to a number of conclusions. There is a need for a set of guidelines or standards for utility interconnection. The advent of new devices with more power handling capability will change the desired topology.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
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  • 52
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    Salyut-7 (1982)
    In:  CASI
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    Publication Date: 2013-08-29
    Description: The differences between the orbital scientific station "Salyut-7" and "Salyut-6" are discussed. It is noted that the greatest changes have occurred in the scientific instrument compartment. The changes in the food supplied to the cosmonauts are also described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-77177 , NAS 1.15:77177
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  • 53
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    Life test of 50 AH NiH2 battery (1982)
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    Publication Date: 2016-06-07
    Description: Life cycle testing on a battery is reported. The cells were built in 1975, put into battery in 1976, and flown in 1977 in low Earth orbit.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 487-499
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  • 54
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    Cycling characteristics on NiH2 cells in standard and daily energy balance Leo orbits (1982)
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    Publication Date: 2016-06-07
    Description: A plot of end-of-charge and end-of-discharge voltage versus the number of cycles completed, and end-of-charge and end-of-discharge pressure versus cycles completed are presented.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 501-512
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  • 55
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    Chargeability of nickel electrodes studied by optical microscopy (1982)
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    Publication Date: 2016-06-07
    Description: Some of the operational characteristics of some nickel hydrogen cells are explained. Some strange capacity excursions with cycling were seen.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 459-470
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  • 56
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    A method for battery activation (1982)
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    Publication Date: 2016-06-07
    Description: A technique to activate nickel cadmium batteries is described. The method shortened the time required for activation, eliminated the temperature rise in the batteries, and produced a voltage on the discharge that was better than when the C/20 was run for 48 hours during tests. Various methods of activation are described and evaluated. Results of alternate conditioning charge schemes are presented along with voltage/temperature characteristics for multiple level nickel cadmium battery chargers.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The 1981 GSFC Battery Workshop; p 423-433
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  • 57
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    Effects of the mode of storage on the capacity fading of the sintered nickel electrodes (1982)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: A systematic investigation of the effect of temperature and two conditions of storage, shortened and open circuit, on the capacity fading of sintered nickel electrodes in NiCd batteries was conducted. All testing was done on sintered electrodes in flooded cells. Cycling tests to measure the capacity were performed at room temperature. The capacity out to one volt, a capacity useful for satellite applications. Test results indicated that: the shortened electrode showed a higher rate of loss than the open circuit electrodes; there was an increase in both modes with an increase in temperature; there was a loss of capacity with time of storage; a general degradation was observed as a function of time; shortened electrodes showed a higher end of charge than the open circuit ones; and at room temperature there was a lower loss in the open circuit electrode than in the shortened one.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 367-386
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  • 58
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    SMM parallel battery operation in orbit (1982)
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    Publication Date: 2016-06-07
    Description: A parallel battery system for the SMM spacecraft is described. The battery system performance as a function of lifetime over orbit was evaluated. The following equipment performance specifications were examined during a typical orbit: battery current and discharges, voltage limitations, battery temperature variations, and current sensor performance. Tabulated battery performance data is also included.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The 1981 GSFC Battery Workshop; p 305-315
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  • 59
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    NiCd cell reversals during reconditioning (1982)
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    Publication Date: 2016-06-07
    Description: An accelerated battery test with 15 periods of cell reversals during reconditioning was performed. The nature and extent of hydrogen generation was examined, and the effects of reversals on battery performance were determined.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 271-284
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  • 60
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    NiCd battery cycle life prediction equation for low Earth orbit (1982)
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    Publication Date: 2016-06-07
    Description: Cycle life analysis of the nickel cadmium battery is given. The life prediction equation is limited to spacecraft in low Earth orbits.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 213-222
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  • 61
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    Electrochemical models for the discharge characteristics of the NiCd cell (1982)
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    Publication Date: 2016-06-07
    Description: Models are developed and discussed as a technique for evaluating the discharge characteristics of the nickel cadmium battery. Results are compared with available experimental data.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 177-188
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  • 62
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    Recent test results on lithium BCX cells (1982)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Texts included: short circuit analysis, voltage reversal, high temperature exposure, parallel loading sharing, capacity tests, shock and vibration tests, and assembly tests. Both the AA and D cell configurations were tested. Certification of the cells is discussed and applications are highlighted.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 55-75
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  • 63
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    New NiCd Battery Standard and Guide (1982)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The preparation and contents guides designed to provide specifications and standards for NiCd batteries for space missions are discussed. Requirements were established to assure proper in orbit performance and compliance with handling procedures to minimize degradation. The guides were designed to benefit both industries and the military. The surveys include: reasons given for and against the use of flight batteries in systems tests; use of rechargeable batteries during space vehicle testing; and military standards and specifications.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 353-366
    Format: application/pdf
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    GPS on-orbit battery performance (1982)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Three batteries designed for the GPS system were evaluated. The batteries were wired together, and during the eclipse period were discharged through parallel diodes into a boost converter which then boosted the battery voltage up to the totally regulated bus voltage. Each battery, with a system life of approximately five years, had its own charger. During testing the battery was maintained or used on trickle charge. Data are presented for the battery capacity during the reconditioning. Raw data for each eclipse period and calculations for the average discharge voltage for each battery are given. Thermal cycling for one of the batteries and reconditioning cycles and regimes for all of the batteries are discussed. A reconditioning discharge curve is also given. The problem of temperature cycling in one of the batteries was resolved by redesigning the battery radiator system.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 341-352
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  • 65
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    Progress in secondary lithium batteries (1982)
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    Publication Date: 2016-06-07
    Description: The lithium/molybdenum trisulfide system is discussed. This system has a higher potential energy density than that of lithium/titanium disulfide. Possible energy densities and performance values for cells, projected from preliminary data obtained on small cells, are summarized. The electrode structure is emphasized as an important factor in the decreasing of capacity upon cycling.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 141-148
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  • 66
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    Heat generation rates in lithium thionyl chloride cells (1982)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: An empirical equation that is useful for good first approximation in thermal modeling is presented. Indications and measurements of electrochemical heat effects were investigated. The particular cells of interest are of the D size, with spiral wound configuration and were instrumented with a thermocouple. It is found that cathode limited cells can explode on reversal at moderate temperatures.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 91-99
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  • 67
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    Alternate seal configuration for lithium primary cells (1982)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The problem of glass degradation in the glass-to-metal seals in lithium/sulfur dioxide cells is discussed. The glass degradation mechanism is attributed to lithium reacting with glass which is a result of deposition of lithium at the glass/metal/electrolyte interface. The worst degradation was observed when cells were stored in the inverted position. Alternate sealing methods were examined and a modified Ziegler seal is considered to be one of the best possible methods. The seal consists of a crimp type soft seal using a plastic annulus and a metal tube. Results of degradation tests are presented.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 45-54
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  • 68
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    Accelerating rate calorimetry: A new technique for safety studies in lithium systems (1982)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The role of exothermic reactions in battery test modes is discussed. The exothermic reactions are characterized with respect to their time-temperature and time-pressure behavior. Reactions occuring for any major exotherm were examined. The accelerating rate calorimetry methods was developed to study lithium cells susceptibility to thermal runaway reactions following certain abuse modes such as forced discharge into reversal and charging.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 31-44
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  • 69
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    Comparisons of different plate treatment and designs: An update (1982)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Nine groups of cells were studied. The first group was the control. The basic design was cadmium in the positive plate, and no negative treatment. The plate loading level was the IUE. The separator was pellon. The test regime for the remaining cells was a 90 minute cycle with 40% depth of discharge and a temperature of 20 C. The charge rate was 9.6 amps to a voltage limit. The discharge rate was 9.6 amps.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The 1981 GSFC Battery Workshop; p 435-442
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  • 70
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    Sintered plaque characteristics (1982)
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    Publication Date: 2016-06-07
    Description: The structural transformations occurring during sintering, the fabrication of a slurry produced sintered plaque, are detailed. Degradation of the positive electrode in performance in cycling in a nickel hydrogen battery were traced to the quality of the sintered plaque. Electrode degradation was found to be a limiting factor in the battery cycle life. Details of microstructural characterization and distribution of pores, examination of plastic flow during shrinkage, and observations of the rounding of nickel powder particles during the slurry process are presented.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 387-402
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  • 71
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    Update: Viking Lander NiCd batteries. Year six (1982)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The performance of NiCd batteries on the Viking Mars landers is discussed. During evaluation, three of the four batteries were maintained in the discharged state. Battery charge regimes and close-together, deep-discharge, reconditioning cycles to retard degradation of batteries are discussed. The effect of elevated temperatures during Martian summer on battery performance were also considered. Tabulated data for average battery capacity as a function of time are given. A design uplink to allow more frequent, greater depth of discharge reconditioning cycles was proposed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 327-339
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  • 72
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    Space station preliminary design report (1982)
    In:  CASI
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    Publication Date: 2019-06-28
    Description: The results of a 3 month preliminary design and analysis effort is presented. The configuration that emerged consists of a very stiff deployable truss structure with an overall triangular cross section having universal modules attached at the apexes. Sufficient analysis was performed to show feasibility of the configuration. An evaluation of the structure shows that desirable attributes of the configuration are: (1) the solar cells, radiators, and antennas will be mounted to stiff structure to minimize control problems during orbit maintenance and correction, docking, and attitude control; (2) large flat areas are available for mounting and servicing of equipment; (3) Large mass items can be mounted near the center of gravity of the system to minimize gravity gradient torques; (4) the trusses are lightweight structures and can be transported into orbit in one Shuttle flight; (5) the trusses are expandable and will require a minimum of EVA; and (6) the modules are anticipated to be structurally identical except for internal equipment to minimize cost.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-87521 , NAS 1.15:87521
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  • 73
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    Shape control of large space structures (1982)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A survey has been conducted to determine the types of control strategies which have been proposed for controlling the vibrations in large space structures. From this survey several representative control strategies were singled out for detailed analyses. The application of these strategies to a simplified model of a large space structure has been simulated. These simulations demonstrate the implementation of the control algorithms and provide a basis for a preliminary comparison of their suitability for large space structure control.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Marshall Space Flight Center The 1982 NASA(ASEE Summer Fac. Fellowship Program; 28 p
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  • 74
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    Fuel optimal maneuvers of spacecraft about a circular orbit (1982)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Fuel optimal maneuvers of spacecraft relative to a body in circular orbit are investigated using a point mass model in which the magnitude of the thrust vector is bounded. All nonsingular optimal maneuvers consist of intervals of full thrust and coast and are found to contain at most seven such intervals in one period. Only four boundary conditions where singular solutions occur are possible. Computer simulation of optimal flight path shapes and switching functions are found for various boundary conditions. Emphasis is placed on the problem of soft rendezvous with a body in circular orbit.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Marshall Space Flight Center The 1982 NASA(ASEE Summer Fac. Fellowship Program; 22 p
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  • 75
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    Nickel system manufacturing update (1982)
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    Publication Date: 2016-06-07
    Description: The electrochemical positive electrode was used in nickel hydrogen for six or seven years with very good results, primarily because of the dimensional stability and the high electrical utilization of the active material.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 547-549
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  • 76
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    Positive electrode processing for Hughes NiH2 cells (1982)
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    Publication Date: 2016-06-07
    Description: The basic procedures were developed for the manufacture of nickel cadmium batteries. An electrochemical impregnation in an aqueous ethanol solution is used in this process. Several additional controls were instituted for production of flight electrodes, including a Hughes controlled MCD, a solution reserved exclusively for the impregnation of Hughes positive electrodes a system of complete traceability for individual electrodes, an electrical characterization test to provide information on weight and capacity at the plaque level, and a stress test to provide data on capacity, weight, and physical parameters at the electrode level.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 471-480
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  • 77
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    RCA SATCOM in-orbit experience: An update (1982)
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    Publication Date: 2016-06-07
    Description: The SATCOM in-orbit battery performance was evaluated. The capacitance and constant current charge rates for each of the three batteries were monitored. A typical eclipse discharge profile was generated and attendant reconditioning recharge conditions were considered. Battery temperatures, pressures, and average battery voltages are presented in tabular form. In-orbit data from monitoring the end of discharge voltage during eclipses, a key performance parameter, are also given.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 317-326
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  • 78
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    DSCS 3 life test progress report (1982)
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    Publication Date: 2016-06-07
    Description: Life test considerations for a spacecraft power supply system, a battery system, designed for synchronous communication satellites for the Defense Satellite Communication System are described. The following equipment specifications considered in the life tests were: the nickel cadmium cells; bus conductors; diodes; battery casings; electric discharges; voltage drops; pressure, and temperature measurements. Battery performance data collected during eclipse periods is presented in tabular form.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 293-304
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  • 79
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    An improved equation for discharge voltage (1982)
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    Publication Date: 2016-06-07
    Description: An improved equation for battery discharge voltage was developed. By looking at the voltage discharge curves, some prediction of cell life could be made.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 257-269
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  • 80
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    Time-to-failure analysis for NiCd batteries in a CPS orbit (1982)
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    Publication Date: 2016-06-07
    Description: Cells operating at five degrees Celsius or less, and going to 60 to 65 percent depth of discharge, were studied as to whether they could achieve a useful working life of 7.5 years in a GPS orbit. The characteristics of various orbits were compared and it is noted that the GPS orbit experiences only 220 cycles a year and must be treated as a geosynchronous rather than a low Earth orbit. Cell degradation is considered to be the result of both trickle-charge degradation and degradation due to cycling. Time-to-failure values are presented for selected temperatures and depth of discharges.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 223-236
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  • 81
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    Navy position on lithium safety (1982)
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    Publication Date: 2016-06-07
    Description: The Navy's position on safety of lithium batteries is discussed. Testing includes: short circuit with all fuses bypassed; forced discharge at the fuse value; and a modified incineration test.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 157-163
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  • 82
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    Factors affecting cycle life in ambient temperature of secondary lithium batteries (1982)
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    Publication Date: 2016-06-07
    Description: Three major factors are discussed: electrode integrity, electrolyte stability, and dendrite formation. It is concluded that elastomers can function as improved binders for rechargeable cathodes. The cathodes can retain integrity under long cycle life with no visual deteriorations. It is found that microelectrodes can be made from powdery cathode materials for voltammetry studies.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 123-140
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  • 83
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    Case-positive versus case-negative designs for low-rate lithium thionyl chloride cells (1982)
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    Publication Date: 2016-06-07
    Description: Case polarity design choices are discussed. Two examples of case-negative designs are presented. One battery is thionyl chloride limited and the other is lithium limited. The case-positive design is thionyl chloride limited. It is found that the case-positive/case-negative design consideration does not seem to have much bearing on storage. However, during low rate discharge, the case-negative cells show a steadily decreasing capacity as you go to lower and lower rates.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 77-90
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  • 84
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    Galileo battery (1982)
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    Publication Date: 2016-06-07
    Description: A general discussion of the battery requirements for the Galileo probe is presented. Problems arising from mission changes are emphasized.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 237-256
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  • 85
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    Life prediction model comparisons (1982)
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    Publication Date: 2016-06-07
    Description: Predictive failure models for nickel cadmium batteries are discussed. Emphasis is given to the McDermott model, the Lander model, and the JPL failure model.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 201-212
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  • 86
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    Nickel-hydrogen flight relay and cell shorting test (1982)
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    Publication Date: 2016-06-07
    Description: A relay used on a standard flight configuration of nickel-hydrogen cells is discussed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 525-532
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  • 87
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    OAO-C end-of-mission power subsystem engineering evaluation (1982)
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    Publication Date: 2016-06-07
    Description: The battery performance on both Orbiting Astronomical Observatory missions was excellent. The end-of-mission power subsystem tests on the battery and the solar arrays provides a real-time degradation analysis for these two components.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The 1981 GSFC Battery Workshop; p 285-292
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  • 88
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    Destruct/non-destruct evaluation of cycled NiCd cells (1982)
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    Publication Date: 2016-06-07
    Description: AC impedance techniques are discussed for a non-destruct analysis of nickel cadmium batteries. A technique for determining battery cycle life is the ultimate goal.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 165-176
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  • 89
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    Discharge of 1400 AH lithium thionyl chloride cells into voltage reversal (1982)
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    Publication Date: 2016-06-07
    Description: The development of a high energy density battery is discussed. Tests were conducted on a 1400 AH cell and they include: drop tests, crush tests, vibration and shock tests, hydrostatic pressure effects, charge current tests, and discharge tests. None of these tests led to a venting or explosion of the cell. Criteria are presented for extending RV safety of a 1400 AH cell.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 101-112
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  • 90
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    High rate, high reliability Li/SO2 cells (1982)
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    Publication Date: 2016-06-07
    Description: The use of the lithium/sulfur dioxide system for aerospace applications is discussed. The high rate density in the system is compared to some primary systems: mercury zinc, silver zinc, and magnesium oxide. Estimates are provided of the storage life and shelf life of typical lithium sulfur batteries. The design of lithium cells is presented and criteria are given for improving the output of cells in order to achieve high rate and high reliability.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 15-30
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  • 91
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    Identification and control of spacecraft (1982)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Information on the identification and control of spacecraft is given. Maximum likelihood estimation, identification accuracy issues, steady state identifiability analysis and stochastic error with process noise are among the topics addressed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Structural Dyn. and Control of Large Space Struct., 1982; p 79-90
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  • 92
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    Some properties of NiH2 cells (1982)
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    Publication Date: 2016-06-07
    Description: Different tests on a flight type cell are discussed. The temperature was measured at the cell flange. The cell was charged to rollover at .75 C rate at 40 degrees C for the first temperature. At that point a voltage reading was taken. Charging was done for an arbitrary ten seconds at .75 C, 30 C, 20 C, 10 C and zero C to obtain momentarily stable voltages.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 513-524
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  • 93
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    NiH2 cell test update (1982)
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    Publication Date: 2016-06-07
    Description: Testing at 9500 cycles on one cell and at 7500 on a second is reported. A third cell failed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 533-545
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  • 94
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    COMSAT Labs life test data for NiH2 cells (1982)
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    Publication Date: 2016-06-07
    Description: Data concerning a ten cell nickel hydrogen battery are presented. The plates are electrochemically impregnated using slurry plaque.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 481-485
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  • 95
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    Comparisons of different plate treatments and designs: Analysis (1982)
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    Publication Date: 2016-06-07
    Description: The design and process changes on cell performance and life were studied. The merits of each design were analyzed physically, chemically, and electrochemically. A teardown analysis of each cell was carried out. On opening the cell it was found that the cell pack was moist with the electrolyte, the extent varying from one cell to another. The cell components, the positives, the negatives, and the separators, could be separated easily for cell pack of an uncycled cell. The separators from the uncycled cell were clean and white. In the case of cycled cells the separators were stuck to the surface of the negative plates. During the removal of these separators from the negative plates invariably a thin layer of the separator material was strongly adhering to the surface of the negative plates and could not be removed as easily as in the case of the uncycled cells. The separators had dark patches due to cadmium migration.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 443-458
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  • 96
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    Recent developments in the NSWC composite electrode (1982)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: A characterization of the physical parameters and life cycle data on nickel composite electrodes was conducted. Attempts to improve the nickel composite electrodes with respect to longevity, light weight, and low cost were made. The physical characteristics of a group of electrodes were examined with emphasis on the porosity of the plaques, the thickness of the electrodes, and the potential presence of electrolytes contamination. It was concluded that the nickel composite electrodes exhibit good life cycle characteristics and that their fabrication seems to present real possibilities for the future as a method of making electrodes that are durable, lightweight, and low cost.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 403-414
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  • 97
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    NiCd battery failure analysis (1982)
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    Publication Date: 2016-06-07
    Description: The failure of a nickel cadmium battery undergoing tests is discussed. Reasons for the complete destruction of the battery while undergoing preparation for thermal vacuum testing are given.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 189-200
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  • 98
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    Army position on lithium battery safety (1982)
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    Publication Date: 2016-06-07
    Description: User requirements for lithium sulfur batteries are presented. They include careful analysis of design and quality control, along with certain equipment specifications. Some of the specifications include: hermetically sealed cells; lithium limited cells with stoichiometry of lithium to sulfur dioxide as a ratio of one; low moisture content in the cells; and battery capacity.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 149-156
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  • 99
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    High-rate lithium thionyl chloride cells (1982)
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    Publication Date: 2016-06-07
    Description: A high-rate C cell with disc electrodes was developed to demonstrate current rates which are comparable to other primary systems. The tests performed established the limits of abuse beyond which the cell becomes hazardous. Tests include: impact, shock, and vibration tests; temperature cycling; and salt water immersion of fresh cells.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 113-122
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  • 100
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    Origin and control of instability in SCR/triac three-phase motor controllers (1982)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The energy savings and reactive power reduction functions initiated by the power factor controller (PFC) are discussed. A three-phase PFC with soft start is examined analytically and experimentally to determine how well it controls the open loop instability and other possible modes of instability. The detailed mechanism of the open loop instability is determined and shown to impose design constraints on the closed loop system. The design is shown to meet those constraints.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center The 1982 NASA(ASEE Summer Fac. Fellowship Program; 30 p
    Format: application/pdf
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