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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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At least 199 records · Page 11
All sourcesNASA NTRSDOE OSTI
NASA NTRS1976

Use of calibration maneuvers for improved performance of strapdown attitude reference systems

Conventional strapdown configurations require precise knowledge of the orientation of the gyro input axes as well as a moderately large, fast computer to provide inertial attitude. This paper presents the mechanization and discusses the operation and performance of an omnidirectional, strapdown pointing control system called All Sky Pointer which does not require precise gyro alignment or a sophisticated computer. Errors caused by gyro-optical sensor misalignment, gyro-integrator bias, and scale factor error are compensated for by the use of calibration maneuvers. Control and computation are provided by an electronics package utilizing technology similar to that found in hand-held calculators. Simulation results indicate that sub arc-minute pointing performance is possible and pointing errors are reduced by as much as an order of magnitude compared with uncompensated systems.

Lorell, K. R.↗
NASA NTRS1977

Connector with cable-to-chassis strain relief

Electronic connector adapted from readily available components simplifies electronic packaging and interconnection wiring in assemblies that consist of several identical printed-wiring boards.

Tuskind, K. W.↗
NASA NTRS1976

NASA atomic hydrogen standards program - An update

Some of the design features of NASA hydrogen masers are discussed including the large hydrogen source bulb, the palladium purified, the state selector, the replaceable pumps, the small entrance stem, magnetic shields, the elongated storage bulb, the aluminum cavity, the electronics package, and the autotuner. Attention is also given to the reliability and operating life of these hydrogen atomic standards.

Reinhardt, V. S.↗
NASA NTRS1977

Evaluation of thermal soak times

A mathematical model for the heat transfer within the electronics package of a Chaparral missile was performed. The Grashof number for this configuration was less than 2000 which indicated that the primary mode of heat transfer was conduction. The Vodicka theory for heat conduction in laminated composite media was utilized to obtain the solution for the model.

Mulholland, G. P.↗
NASA NTRS1979

The Addition of EI/CI Capability to the Mattauch-herzog Spectrograph with EOID

A modification was made to the Mattauch-Herzog Spectrograph with an electro-optical ion detector (EOID) previously designed and constructed, so that it would be capable of operating not only in the electron-impact (EI) mode of ionization, but also in the chemical ionization (CI) mode. This modification necessitated an effort in three specific design areas: (1) sample inlet; (2) ion source and analyzer regions; and (3) the pumping system. In addition, an appropriate electronics package had to be designed to control and operate the combined EI/CI source.

Fergusson, G. J.↗
NASA NTRS1980

Electronic and software subsystems for an autonomous roving vehicle

The complete electronics packaging which controls the Mars roving vehicle is described in order to provide a broad overview of the systems that are part of that package. Some software debugging tools are also discussed. Particular emphasis is given to those systems that are controlled by the microprocessor. These include the laser mast, the telemetry system, the command link prime interface board, and the prime software.

Doig, G. A.↗
NASA NTRS1981

Diagnostic system design for the Ion Auxiliary Propulsion System (IAPS). Flight tests of two 8 cm mercury ion

The mechanical, thermal, electrical design and the ground test results of four types of detectors are explained. The DSS is designed to measure the thruster efflux material deposition and S/C potential relative to the local plasma in the vicinity of two 8 cm mercury ion thrusters. The DSS consists of two quartz crystal microbalance (QCM) detectors, one potential probe, nine solar cell arrays, seven ion collectors and two electronic packages.

Hurst, E. B.↗
NASA NTRS1983

Adapter for mounting a microphone flush with the external surface of the skin of a pressurized aircraft

A mounting device for securing a microphone pick up head flush with respect to the external surfaces of the skin of an aircraft for detecting shock waves passing thereover is described. The mount includes a sleeve mounted internally of the aircraft for capturing and supporting an electronics package having the microphone pick up head attached thereto in a manner such that the head is flush with the external surface of the aircraft skin and a pressure seal is established between the internal and external surfaces of the aircraft skin.

Cohn, R. B.↗
NASA NTRS1983

Development of an autonomous video rendezvous and docking system, phase 2

The critical elements of an autonomous video rendezvous and docking system were built and used successfully in a physical laboratory simulation. The laboratory system demonstrated that a small, inexpensive electronic package and a flight computer of modest size can analyze television images to derive guidance information for spacecraft. In the ultimate application, the system would use a docking aid consisting of three flashing lights mounted on a passive target spacecraft. Television imagery of the docking aid would be processed aboard an active chase vehicle to derive relative positions and attitudes of the two spacecraft. The demonstration system used scale models of the target spacecraft with working docking aids. A television camera mounted on a 6 degree of freedom (DOF) simulator provided imagery of the target to simulate observations from the chase vehicle. A hardware video processor extracted statistics from the imagery, from which a computer quickly computed position and attitude. Computer software known as a Kalman filter derived velocity information from position measurements.

Tietz, J. C.↗
NASA NTRS1984

Thermal energy management process experiment

The thermal energy management processes experiment (TEMP) will demonstrate that through the use of two-phase flow technology, thermal systems can be significantly enhanced by increasing heat transport capabilities at reduced power consumption while operating within narrow temperature limits. It has been noted that such phenomena as excess fluid puddling, priming, stratification, and surface tension effects all tend to mask the performance of two-phase flow systems in a 1-g field. The flight experiment approach would be to attack the experiment to an appropriate mounting surface with a 15 to 20 meter effective length and provide a heat input and output station in the form of heaters and a radiator. Using environmental data, the size, location, and orientation of the experiment can be optimized. The approach would be to provide a self-contained panel and mount it to the STEP through a frame. A small electronics package would be developed to interface with the STEP avionics for command and data handling. During the flight, heaters on the evaporator will be exercised to determine performance. Flight data will be evaluated against the ground tests to determine any anomalous behavior.

Ollendorf, S.↗
NASA NTRS1984

A simplified GPS C/A reciever front end with low noise performance

A redesign of the antenna electronics package for the NBS/GPS C/A receiver has resulted in significantly reduced cost and improved performance. Major improvements include a simplified and more reliable multiplier/mixer, elimination of all twelve piston trimmer tuning capacitors in the original design, elimination of expensive bandpass filters, less expensive antenna and a simplified packaging scheme.

Davis, D. D.↗
NASA NTRS1986

Measuring Water-Layer Thickness

Technique uses optical proximity detector. Detector consists of sensing probe, cartridge containing photocell and light source, and electronics package, housed in metal carrying case. Light transmitted from fiber-optic probe reflected by observed surface and transmitted back through probe to photoreceiver, output of which indicated on digital voltmeter or other suitable instrument. Sensor used to detect presence of bubbles or particles in water stream or to trigger alarm when condensing water becomes present in bottom of supposedly dry tank. Fiber-optic probes of sizes up to 0.285 in. (7.24 mm) with varying sensitivities and configurations available for use with system.

Faulcon, N.↗
NASA NTRS1986

Thermal analysis of radiometer containers for the 122m hoop column antenna concept

A thermal analysis was conducted for the 122 Meter Hoop Column Antenna (HCA) Radiometer electronic package containers. The HCA radiometer containers were modeled using the computer aided graphics program, ANVIL 4000, and thermally simulated using two thermal programs, TRASYS and MITAS. The results of the analysis provided relationships between the absorptance-emittance ratio and the average surface temperature of the orbiting radiometer containers. These relationships can be used to specify the surface properties, absorptance and reflectance, of the radiometer containers. This is an initial effort in determining the passive thermal protection needs for the 122 m HCA radiometer containers. Several recommendations are provided which expand this effort so specific passive and active thermal protection systems can be defined and designed.

Dillon-Townes, L. A.↗
NASA NTRS1987

The first products made in space - Monodisperse latex particles

Monodisperse latex particles developed by seeded emulsion polymerization on various Space Shuttle flights are analyzed. The flight hardware was composed of a monodisperse latex reactor and a support electronics package, and the particles were examined by optical microscopy and TEM. Data on the particle size distributions, larger and smaller off-size particles, and conversion-time curves for the particles are examined and compared to ground-based results. It is observed that the ground-based polymerizations have more coagulum than the flight polymerizations; the flight latex particles have narrower size distributions than the ground particles; and the number of off-size larger particles in the flight particles is smaller than in the ground data.

Vanderhoff, J. W.↗
NASA NTRS1985

The Galileo attitude and articulation control system - A radiation-hard, high precision, state-of-the-art control system

The Galileo mission and spacecraft, consisting of a Jupiter-orbiter and an atmospheric entry probe, are discussed. Components will include: magnetometers and plasma-wave antennas on a boom, high-gain antenna, probe vehicle, two different bus electronics packages, and a radioisotope thermoelectric generator. Instruments, investigators and objectives are tabulated for both probe science and orbiter science investigations. Requirements in the design of the attitude and articulation control system are very stringent because of the complex dynamics, flexible body effects, the need for autonomy, and the severe radiation environment in the Jupiter nighborhood. Galileo was intended to be ready for launch via Space Shuttle in May of 1986.

Stephenson, R. Rhoads↗
NASA NTRS1989

Biomedical Telectrodes

Compact transmitters eliminate need for wires to monitors. Biomedical telectrode is small electronic package that attaches to patient in manner similar to small adhesive bandage. Patient wearing biomedical telectrodes moves freely, without risk of breaking or entangling wire connections. Especially beneficial to patients undergoing electrocardiographic monitoring in intensive-care units in hospitals. Eliminates nuisance of coping with wire connections while dressing and going to toilet.

Shepherd, C. K.↗
NASA NTRS1988

Technology thrust areas for mass constrained spacecraft

This paper discusses a study that identifies technology thrust areas that could yield significant mass reductions for future spacecraft programs. The work involved analyzing past Jet Propulsion Laboratory interplanetary spacecraft mass data to determine how spacecraft mass is distributed by technology area. It was discovered that over a 22-yr period an almost constant 64 percent of the total spacecraft dry mass is concentrated in the two technology areas of structure and packaged electronics. Also discussed are the methods for achieving significant mass reductions through advances in materials, integration, design, and miniaturization of electronics.

Muirhead, B.↗