Functional and physical design of a flight prototype ion engine power conditioner
Space compatible flight prototype ion engine power conditioning system design for Hg thrustor using oxide cathode
Benson, G. C.↗
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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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Flight prototype electrostatic ballastic pendulum Final report
Flight prototype electrostatic ballistic pendulum momentum transducer
Powell, J. G.↗
Prototype airborne one-third octave band spectrum analyzer for acoustic and vibration data
Design and test evaluation of prototype one-third octave band spectrum analyzer for measurement and analysis of acoustic and vibration data onboard space vehicles
Source record↗
Development and test of a flight prototype power conditioner for 20 cm mercury bombardment electric thruster system
Development and tests of flight prototype power conditioner for 20 cm mercury bombardment electric thruster system
Source record↗
Development of a prototype waste collection system /the modified Hydro John/
Development of prototype waste collection system /modified Hydro John/ designed for use in either zero or one gravity environment
Mangialardi, J. K.↗
Development and testing of a prototype operational system for automatic monitoring of sleep during manned space flight Final report
Prototype device for monitoring sleep during manned space flight including performance tests
Frost, J. D.↗
Design, fabrication, and preliminary evaluation of thermal and hydraulic performance of a prototype SNAP-8 mercury boiler
Thermal and hydraulic performance of prototype SNAP-8 mercury boiler - design, fabrication, and preliminary evaluation
Furman, E. R.↗
Design and development of a prototype static cryogenic heat transfer system
Design and development of prototype static cryogenic heat transfer system utilizing heat pipe with wetting arterial wick and nitrogen as working fluid
Source record↗
Design and fabrication of a flight-concept prototype electrochemical water recovery subsystem
Design and fabrication of flight-concept prototype electrochemical water recovery subsystem
Putnam, D. F.↗
System features of a space station prototype environmental thermal control and life support system
Space station prototype environmental thermal control and life support systems, considering maintainability, reliability, weight penalties and fault detection and isolation
Flugel, C.↗
Validation of SERT 2 thermal analytical techniques by thermal vacuum testing of the prototype satellite
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.
Smolak, G. R.↗
Prototype Slide Stainer
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.
Source record↗
Design and fabrication of a prototype for an automatic transport system for transferring human and other wastes to an incinerator unit onboard spacecraft, phase 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.
Labak, L. J.↗
Design, analysis, and tests of a structural prototype Viking aeroshell. I - Aeroshell design and analysis. II - Test procedure and test results.
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.
Heard, W. L., Jr.↗
Development of a laboratory prototype spraying flash evaporator.
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.
Gaddis, J. L.↗
Atmosphere revitalization in the space station prototype.
The atmosphere revitalization group (ARG) for the space station prototype (SSP) environmental/thermal control and life support system (ETC/LSS) has been designed to meet a comprehensive set of requirements and constraints for a flight type mission. Design definition is for a modular vehicle temperature and humidity control subsystem, contaminant control equipment, a hydrogen depolarized cell CO2 concentrator, a water electrolysis oxygen generation subsystem, CO2 reduction equipment, and a pressure and composition control subsystem. Performance requirements are for support of a crew of six. Realistic leakage rates and metabolic activity cycles, cabin temperature selectability, and controlled cabin relative humidities are specified for the design. Operational aspects of the subsystem are discussed with emphasis given to the influence of a 180-day, maintainable requirement on system design. Consideration of flight vehicle type packaging, in flight maintenance, data management systems interface and fault detection capability, and electrical supply constraints is covered.
Trusch, R. B.↗
Establishment, test, and evaluation of a prototype volcano surveillance system
Prototype volcano surveillance system located in Alaska, Hawaii, California, Washington, Iceland, Central and South America
Ward, P. L.↗
Prototype ultrasonic instrument for quantitative testing
A prototype ultrasonic instrument has been designed and developed for quantitative testing. The complete delivered instrument consists of a pulser/receiver which plugs into a standard oscilloscope, an rf power amplifier, a standard decade oscillator, and a set of broadband transducers for typical use at 1, 2, 5 and 10 MHz. The system provides for its own calibration, and on the oscilloscope, presents a quantitative (digital) indication of time base and sensitivity scale factors and some measurement data.
Lynnworth, L. C.↗