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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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Prototype lunar gravity simulator for studies of reduced gravity effects on human self locomotive capability, using magnetic air bearings and body support system
Prototype cloud physics laser nephelometer design and performance, determining droplet concentration and size from scattered light pulse count and amplitudes
Prototype electrolyzer for generating oxygen from water vapor under various atmospheric conditions, noting spacecraft cabin application
Space compatible flight prototype ion engine power conditioning system design for Hg thrustor using oxide cathode
Flight prototype electrostatic ballistic pendulum momentum transducer
Design and test evaluation of prototype one-third octave band spectrum analyzer for measurement and analysis of acoustic and vibration data onboard space vehicles
Development and tests of flight prototype power conditioner for 20 cm mercury bombardment electric thruster system
Development of prototype waste collection system /modified Hydro John/ designed for use in either zero or one gravity environment
Prototype device for monitoring sleep during manned space flight including performance tests
Thermal and hydraulic performance of prototype SNAP-8 mercury boiler - design, fabrication, and preliminary evaluation
Design and development of prototype static cryogenic heat transfer system utilizing heat pipe with wetting arterial wick and nitrogen as working fluid
Design and fabrication of flight-concept prototype electrochemical water recovery subsystem
Space station prototype environmental thermal control and life support systems, considering maintainability, reliability, weight penalties and fault detection and isolation
The thermal protection system for the flight configuration of the SERT 2 satellite was designed using an analytical thermal network to represent the satellite and its environment. A large part of this digital analytical network was adjusted and calibrated by comparing predicted temperatures with experimental measurements made with the prototype SERT 2 satellite in an extended thermal vacuum test. The procedures used in adjusting and calibrating the analytical network are outlined.
The prototype slide staining system capable of performing both one-component Wright's staining of blood smears and eight-step Gram staining of heat fixed slides of microorganisms is described. Attention was given to liquid containment, waste handling, absence of contamination from previous staining, and stability of the staining reagents. The unit is self-contained, capable of independent operation under one- or zero-g conditions, and compatible with Skylab A.
Three transport system concepts were experimentally evaluated for transferring human and nonhuman wastes from a collection site to an incineration unit onboard spacecraft. The operating parameters, merits, and shortcomings of a porous-pneumatic, nozzle-pneumatic, and a mechanical screw-feed system were determined. An analysis of the test data was made and a preliminary design of two prototype systems was prepared.
Two near optimum full-scale Viking aeroshell prototypes (140 deg ring-stiffened conical shells), differing only in base ring size, were designed and tested under uniform pressure to buckling failure. Part I describes the computerized design procedure which iterates between a design program based on approximate equations to determine skin and ring gages and ring spacings, and a sophisticated system of shell of revolution programs for more accurate analysis as a basis for redesign. Part II discusses fabrication techniques, test procedures, and test results. Both buckling and prebuckling data are compared with the theoretical predictions of Part I. Appropriate buckling knockdown factors for this type of construction are identified. Measured strains in skin and rings agreed well with theoretical predictions and the buckling pressure was in close agreement with the design ultimate pressure.
A functional description of the flash evaporator that is being developed as a candidate for the Space Shuttle Environmental Control System thermal control is presented. A single evaporator configuration uses water as an evaporant to accommodate on-orbit peak heat loads and Freon 22 for terrestrial flight phases below 120,000 ft altitude. Development history, test plans, and operational characteristics are described. Detailed information is included to show: design features, fabrication techniques used for a prototype unit, redundancy considerations, and the control arrangement.