Transient compatibility measurements in spacecraft
Transient compatibility measurements in spacecraft electronic equipment
Rogers, P. R.↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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A study of guidance modes for a unified guidance system Interim report
Spacecraft guidance theory applications to development of spacecraft electronic equipment for automatic guidance and navigation
Berry, W. H.↗
A versatile, low cost, fabrication technique for flight hardware
Wiring technique for spacecraft electronic equipment using integrated circuits
Chernikoff, H.↗
A study of voltage breakdown in spacecraft systems from test and flight experience
Voltage breakdown in spacecraft electronic circuitry during tests and flight conditions
Mercy, K. R.↗
Considerations associated with the design of the thermal subsystem of the Orbiting Astronomical Observatory
OAO thermal subsystem design to provide temperature control for experiments and spacecraft electronic devices
Coyle, M. J., Jr.↗
Simulation of radiation from RTG power sources
Simulation of neutron effects from radioisotope thermoelectric power generator on spacecraft electronic components
Newman, P. A., Jr.↗
Structural evaluations and dynamic testing of solar electric propulsion components.
Results of an experimental and analytical study of selected Solar Electric Propulsion (SEP) thrust subsystem components are presented. A mass and center-of-mass mockup of an experimental power conditioning (PC) panel was used for the PC structure evaluation. Test environment was based on that specified for prooftesting the Viking spacecraft electronics. Modal frequencies were surveyed over the range of 0-2000 Hz using both conventional test equipment and the holographic interferometry technique. Results of the forced vibration tests point to the need for some additional stiffening to make the structure qualifiable.
Womack, J. R.↗
Hybrid measurement chains for the SAS-C spacecraft
Spacecraft electronic systems usually demand tight packaging. It was this consideration which initially forced us to consider hybrid circuits for the analog signal processing circuits in the Small Astronomy Satellite-C (SAS-C) scientific payload. We gradually discovered that increased reliability, low power consumption, and reduced program costs all followed. This paper will attempt to share our laboratory's first experience with hybrid circuits and indicate those areas which we found to be important.
Goeke, R. F.↗
A variable conductance heat pipe flight experiment - Performance in space
The Ames Heat Pipe Experiment (AHPE) is a variable conductance heat pipe/radiator system which was launched aboard the OAO-C spacecraft in August, 1972. All available flight data was reviewed and those from a few orbits were selected for correlation with predictions from an analytical model of the system. The principal conclusion of this study is that gas controlled variable conductance heat pipes can perform reliably for long time periods in the space environment and can effectively provide temperature stabilization for spacecraft electronics. Furthermore, the performance of such systems can be adequately predicted using existing analysis tools.
Wanous, D. J.↗
Flight data analysis and further development of variable-conductance heat pipes
Continuing efforts in large gains in heat-pipe performance are reported. It was found that gas-controlled variable-conductance heat pipes can perform reliably for long periods in space and effectively provide temperature stabilization for spacecraft electronics. A solution was formulated that allows the control gas to vent through arterial heat-pipe walls, thus eliminating the problem of arterial failure under load, due to trace impurities of noncondensable gas trapped in an arterial bubble during priming. This solution functions well in zero gravity. Another solution was found that allows priming at a much lower fluid charge. A heat pipe with high capacity, with close temperature control of the heat source and independent of large variations in sink temperature was fabricated.
Enginer, J. E.↗
Plasma charging testing of communication satellites
A discussion is given of ESD as a radiated electromagnetic environment and compares the ESD environment to a standard EMI test environment. An arc generator used to assess the sensitivity of typical spacecraft electronics is described. The results of radiated susceptibility tests conducted on breadboard circuits and a satellite electrical model of a communication satellite are discussed.
Rosen, F.↗
A mechanical, thermal and electrical packaging design for a prototype power management and control system for the 30 cm mercury ion thruster
A prototype electric power management and thruster control system for a 30 cm ion thruster is described. The system meets all of the requirements necessary to operate a thruster in a fully automatic mode. Power input to the system can vary over a full two to one dynamic range (200 to 400 V) for the solar array or other power source. The power management and control system is designed to protect the thruster, the flight system and itself from arcs and is fully compatible with standard spacecraft electronics. The system is easily integrated into flight systems which can operate over a thermal environment ranging from 0.3 to 5 AU. The complete power management and control system measures 45.7 cm (18 in.) x 15.2 cm (6 in.) x 114.8 cm (45.2 in.) and weighs 36.2 kg (79.7 lb). At full power the overall efficiency of the system is estimated to be 87.4 percent. Three systems are currently being built and a full schedule of environmental and electrical testing is planned.
Sharp, G. R.↗
A mechanical, thermal and electrical packaging design for a prototype power management and control system for the 30 cm mercury ion thruster
A prototype Electric Power Management and Thruster Control System for a 30 cm ion thruster has been built and is ready to support a first mission application. The system meets all of the requirements necessary to operate a thruster in a fully automatic mode. Power input to the system can vary over a full two to one dynamic range (200 to 400 V) for the solar array or other power source. The Power Management and Control system is designed to protect the thruster, the flight system and itself from arcs and is fully compatible with standard spacecraft electronics. The system is designed to be easily integrated into flight systems which can operate over a thermal environment ranging from 0.3 to 5 AU. The complete Power Management and Control system measures 45.7 cm x 15.2 cm x 114.8 cm and weighs 36.2 kg. At full power the overall efficiency of the system is estimated to be 87.4 percent. Three systems are currently being built and a full schedule of environmental and electrical testing is planned.
Sharp, G. R.↗
Advanced Technologies for Commercial Airplanes
263-page report addresses what advanced electrical and electronic spacecraft technologies can be applied in commercial airplanes. Report discusses a study in which technologies used in the Space Shuttle were evaluated for their potential in commercial transports. Describes new technologies, airplanes, tradeoffs and methods of evaluation. Concludes that major beneficiary would be an advanced wide-body transport (500 passenger).
Source record↗
Reactor power system/spacecraft integration
The new national initiative in space reactor technology evaluation and development is strongly tied to mission applications and to spacecraft and space transportation system (STS) compatibility. This paper discusses the power system integration interfaces with potential using spacecraft and the STS, and the impact of these requirements on the design. The integration areas of interest are mechanical, thermal, electrical, attitude control, and mission environments. The mission environments include space vacuum, solar input, heat sink, space radiation, weapons effects, and reactor power system radiation environments. The natural, reactor, and weapons effects radiation must be evaluated and combined to define the design requirements for spacecraft electronic equipment.
Elms, R. V.↗
Electrically-Isolating Analog Amplifier
Signals transmitted between units at different ground potentials. Analog amplifier electrically isolates input from output through use of optoelectronic components. Analog isolation amplifier uses dual-transistor optoisolator, preventing transmission of common-mode voltage from input to output. Circuit useful in spacecraft electronic systems.
Paulkovich, John↗
COBE ground segment gyro calibration
Discussed here is the calibration of the scale factors and rate biases for the Cosmic Background Explorer (COBE) spacecraft gyroscopes, with the emphasis on the adaptation for COBE of an algorithm previously developed for the Solar Maximum Mission. Detailed choice of parameters, convergence, verification, and use of the algorithm in an environment where the reference attitudes are determined form the Sun, Earth, and star observations (via the Diffuse Infrared Background Experiment (DIRBE) are considered. Results of some recent experiments are given. These include tests where the gyro rate data are corrected for the effect of the gyro baseplate temperature on the spacecraft electronics.
Freedman, I.↗
Criticality of Be-7 concentration in LDEF
Heretofore, a number of papers reported the detection of high Be-7 concentration in the LDEF. It sounded alarming for space flight in the LDEF orbit, since Be-7 has a half life of 54 days and emits gamma rays of 0.48 MeV which is ionizing radiation. Two concerns are raised: the high concentration of harmful rays to spacecraft crews; and the concentration damage to spacecraft electronic components. A need was established to estimate the dosage of this concentration and compare the value of the allowed limits. As a result, the dosage was calculated of 0.03 rad. When this is compared with the human limit of 25 rads and the susceptibility requirement of 800 rads, the Be-7 amount should not be considered critical. The calculation of Be-7 dosage is detailed.
Young, Poh Shien↗