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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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Zinc-oxygen primary cell yields high energy density for battery used as an auxiliary power source in space vehicle systems. Maximum reliability and minimum battery weight is achieved by using a stacking configuration of 23 series-connected modules with 6 parallel-connected cells per module.
Multiple access communication satellite systems providing reliable speech communication for low density use in remote areas
Improving load capacity and fatigue life of rolling element systems in rockets and missiles
Power conditioning electronics for integrally regulated and controlled high voltage solar array spacecraft power system, increasing reliability and reducing weight
Modular design techniques improve methods of error detection, diagnosis, and recovery. Theoretical computer (MARCS (Modular Architecture for Reliable Computer Systems)) study deals with postulated and modeled technology indigenous to 1975-1980. Study developments are discussed.
Failure mode frequency ratios, environmental adjustment factors, and failure rates for mechanical and electromechanical component families are presented. The failure rates and failure rate modifiers resulted from a series of studies whose purpose was to provide design, tests, reliability, and systems engineers with accurate, up-to-date failure rate information. The results of the studies were achieved through an extensive engineering analysis of the Saturn Program test data and Unsatisfactory Condition Reports (UCR's) and the application of mathematical techniques developed for the studies.
Technical data, and experiment and spacecraft alternatives are presented in support of the HEAO-C, whose primary objective is a detailed study of the more interesting high energy sources, using grazing incidence X-ray telescopes and a spacecraft pointing accuracy of + or - 1 arc minute. The analyses presented cover the mission analysis and launch vehicle; thermal control trade studies and supporting analyses; attitude sensing and control analyses; electrical systems; and reliability analysis. The alternate experiments which were considered are listed, and the advantages and disadvantages of several alternate observatory configurations are assessed.
A new concept for astronaut maneuvering in space is proposed, and an experimental study undertaken to test this concept is described. The series of experiments performed appear to promise advantages over previously proposed schemes in terms of propellant economy, system weight, reliability, and safety. The simulation tests established the feasibility of the proposed maneuvering concept by showing that test subjects were able to place their bodies sufficiently near the reference position to avoid excessive angular momentum build-up; no difficulties were encountered in selecting self-rotation maneuvers suitable for effecting desired changes in orientation; and the execution of these maneuvers produced predicted reorientations without tiring the test subject significantly.
A data dump is presented containing space shuttle orbiter maneuvering engine performance, weight, envelope, and interface pressure requirements for candidate propellant combinations (NTO/MMH, NTO50-50, LOX/MMH, LOX/50-50, LOX/N2H4, LOX/C3H8, and LOX/RP-1) and cooling concepts (regenerative and dump/film). These data are presented parametrically for the thrust, chamber pressure, nozzle expansion ratio, and engine mixture ratio ranges of interest. Also included is information describing sensitivity to system changes; reliability, maintainability and safety; development programs and associated critical technology areas; engine cost comparisons during development and operation; and ecological effects.
The feasibility of modifying an existing supersonic drone into a free-flight research vehicle is examined. Appropriate structural and control system modifications, reliability and operational considerations, and ROM costs indicate that the BQM-34E drone is indeed suitable as a NASA research vehicle.
Various technological processes to achieve lightweight reliable joining systems for structural elements of aircraft and spacecraft are considered. Joining methods, combinations of them, and nondestructive evaluation and quality assurance are emphasized.
Consideration of stability under structural perturbations of free dynamic systems described by the differential equation dx/dt = A(t,x)x, where the matrix A(t,x) has time-varying nonlinear elements. The concept of 'connective stability' is introduced to study the structural properties of competitive-cooperative nonlinear matrix systems. It is shown that stability reliability in such systems is high and that they remain stable despite time-varying (including 'on-off') interaction among individual agents present in the system. The results obtained can be used to study stability aspects of mathematical models arising in as diverse fields as economics, biology, arms races, and transistor circuits.
Simple and reliable test system gives go/no-go indication of output level of headset microphones. Portable system has its own internal battery power supply and can be used in field or in laboratory with wide variety of headset types.
Mathematical analysis of power spectrum of outputs from high-reliability communication system is used to determine system bandwidth. Analysis provides mathematical relationships of signal power spectrum at output of hard limiter for any type of baseband pulse input subjected only to output parameter constraints.
A multi-slit shadow direction sensor of jalousie type (JDS) was developed to provide a simple, highly reliable tracking system to guide a rotating mirror toward the sun so that the reflected light would illuminate the input slit of a photoelectric spectrometer. The operating principle and stability are considered as well as determination of initial signal level at the output of each photosensor. A procedure is recommended for calculation of a JDS. Both one- and two-coordinate sun direction sensors are described and considered for use in the tracking system of a photoelectric spectrometer.
Results from an intensive FBW advanced development effort indicate significant improvements in overall flight control system performance, reliability, safety and maintainability. Additionally, the strong and credible FBW technology base developed as a result paved the way for further exploitation through the application of advanced concepts such as control configured vehicles and multi-mode controls.
Power spectra for binary phase-shift keyed (PSK) and frequency-shift keyed (FSK) signals with combined sinusoidal amplitude modulation by the bit rate clock are presented. Such signal formats have application in 'burst' communication systems wherein reliable bit synchronization is provided with relative receiver simplicity. Effects of the clock amplitude modulation index and phase are considered, and corresponding power spectra are illustrated. Further, effects of the clock parameters on the rate of spectral rolloff are given and compared with those of conventional PSK and FSK spectra.
Dual-function integrated circuits use one shift register array instead of two to feed video data to seven tape channels thereby making system more reliable and less expensive than predecessor. Basic principle of reformatter is also applicable to multiplexing and frequency conversion circuits.