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Results for “ELECTRONIC EQUIPMENT”

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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At least 19 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1974

Feasibility study of common electronic equipment for shuttle sortie experiment payloads

A study was conducted to determine the feasibility of using standardized electronic equipment on the space shuttle vehicle in an effort to reduce the cost estimates. The standards for Nuclear Instrument Modules (NIM) and CAMAC electronic equipment are presented and described. It was determined that the CAMAC electronic equipment was more suitable for use with the space shuttle systems. Specific applications of the CAMAC equipment are analyzed. Illustrations of the equipment and circuit diagrams of the subsystems are provided.

Source record↗
NASA NTRS2009

Lithium-ion Battery Charge Methodologies Observed with Portable Electronic Equipment

Commercial lithium-ion batteries in portable electronic equipment has been used by NASA for space applications since 1999. First battery that was certified for flight and flown for Shuttle use was the Canon BP 927 (2.7 Ah) battery pack. Since then, numerous portable equipment with li-ion batteries have been certified and flown and remain on-orbit for crew usage. Laptops (two generations with third one being worked on now) Camcorder Camera PDA 2 versions (second one being li-ion polymer cells) Satellite Phone Due to expense and time, certified batteries are used with different equipment with the help of adapters or by working with the manufacturer of the equipment to build the appropriate battery compartment and connector. Certified and dedicated chargers are available on Shuttle and on the ISS for safe charging.

Jeevarajan, Judith↗
NASA NTRS1980

Electronic equipment vulnerability to fire released carbon fibers

The vulnerability of electronic equipment to damage by carbon fibers released from burning aircraft type structural composite materials was investigated. Tests were conducted on commercially available stereo power amplifiers which showed that the equipment was damaged by fire released carbon fibers but not by the composite resin residue, soot and products of combustion of the fuel associated with burning the carbon fiber composites. Results indicate that the failure rates of the equipment exposed to the fire released fiber were consistent with predictions based on tests using virgin fibers.

Pride, R. A.↗
NASA NTRS1969

Proceedings of the Second Workshop on Voltage Breakdown in Electronic Equipment at Low Air Pressure

The Second Workshop on Voltage Breakdown in Electronic Equipment at Low Air Pressure was sponsored by the Jet Propulsion Laboratory, Pasadena, California. It has been three and one-half years since the convening of the first workshop on voltage breakdown. In this interval, gains are evidenced in the progress and sophistication in solving voltage breakdown problems affecting electronic equip­ment operating at high altitudes or other low air pressure environments. Although space applications predominate the area of concern, other projects such as the SST are becoming increasingly involved with voltage breakdown. High-voltage breakdown in spacecraft continues; however, the incidences of occurrence appear to have decreased in spite of an increase in the number of missions flown. This, it is felt, is due to many project managers now requiring all equipment with voltage in excess of 270-V peak to be designed to operate in the critical pressure region without damage, even though its normal functional environment is sea level pressure and the hard vacuum of space. In addition, designers are becoming more aware of the principle of good high-voltage design by selecting void-free components, proper spacing of conductors, isolating high-­voltage circuitry from lower voltage areas, etc. The consensus seems to be that the slight increase in cost to achieve a provable corona-free design is more than offset by the increase in confidence that the equipment will survive accidental loss of vacuum during high-vacuum tests, inadvertent turn on while passing through the critical air-pressure region of earth after launch or outgassing in flight pressurizing the enclosure into the critical pressure region.

E. R. Bunker, Jr.↗
NASA NTRS1997

Hybrid Damping System for an Electronic Equipment Mounting Shelf

The objective of this study was to design and construct a vibration control system for an electronic equipment shelf to be evaluated in the NASA Dryden FTF-11. The vibration control system was a hybrid system which included passive and active damping techniques. Passive damping was fabricated into the equipment shelf using ScothDamp(trademark) damping film and aluminum constraining layers. Active damping was achieved using a two channel active control circuit employing QuickPack(trademark) sensors and actuators. Preliminary Chirp test results indicated passive damping smoothed the frequency response while active damping reduced amplitudes of the frequency response for most frequencies below 500Hz.

Voracek, David↗
NASA NTRS1997

Hybrid Damping System for an Electronic Equipment Mounting Shelf

The objective of this study was to design and construct a vibration control system for an electronic equipment shelf to be evaluated in the NASA Dryden FTF-II. The vibration control system was a hybrid system which included passive and active damping techniques. Passive damping was fabricated into the equipment shelf using ScothDamp(trademark) damping film and aluminum constraining layers. Active damping was achieved using a two channel active control circuit employing QuickPack(trademark) sensors and actuators. Preliminary Chirp test results indicated passive damping smoothed the frequency response while active damping reduced amplitudes of the frequency response for most frequencies below 500Hz.

Voracek, David↗
NASA NTRS1972

Maintainability design criteria for packaging of spacecraft replaceable electronic equipment.

Maintainability must be designed into long-duration spacecraft and equipment to provide the required high probability of mission success with the least cost and weight. The ability to perform repairs quickly and easily in a space environment can be achieved by imposing specific maintainability design criteria on spacecraft equipment design and installation. A study was funded to investigate and define design criteria for electronic equipment that would permit rapid removal and replacement in a space environment. The results of the study are discussed together with subsequent simulated zero-g demonstration tests of a mockup with new concepts for packaging.

Kappler, J. R.↗
NASA NTRS1980

The use of the principle of superposition in measuring and predicting the thermal characteristics of an electronic equipment operated in a space environment

The advantages and possible pitfalls of using a generalized method of measuring and, based on these measurements, predicting the transient or steady-state thermal response characteristics of an electronic equipment designed to operate in a space environment are reviewed. The method requires generation of a set of thermal influence coefficients by test measurement in vacuo. A implified thermal mockup isused in this test. Once this data set is measured, temperatures resulting from arbitrary steady-state or time varying power profiles can be economically calculated with the aid of a digital computer.

Gale, E. H.↗
NASA NTRS1989

Cooling Shelf For Electronic Equipment

Heat-pipe action cools and maintains electronics at nearly constant temperature. System designed to control temperatures of spacecraft shelves or baseplates by combining honeycomb sandwich panel with reservoir of noncondensable gas and processing resulting device as variable-conductance heat pipe. Device provides flat surface for mounting heat-dissipating electronics that is effectively cooled and maintained at nearly constant temperature. Potentially useful in freeze drying, refrigeration, and air conditioning.

Tanzer, Herbert J.↗