Degradation due to contaminants throughout the test cycle
Inspection techniques for determining degradation due to contamination during fabrication of spacecraft components
Paul, F. W.↗
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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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The Surveyor thermal switch
Surveyor thermal switch for temperature control to assure spacecraft components performance during temperature extremes on lunar surface
Deal, T. E.↗
Spacecraft mechanism testing in the Molsink facility
Space molecular sink simulator facility /Molsink/ for extreme high vacuum outer space environment simulation, discussing Mariner Mars 1969 spacecraft components tests
Stephens, J. B.↗
Study-simulation of space station dynamics
Matrix algebra translator and executor /MATE/ takes equations describing structural control system environmental interaction problem for flexible spacecraft components and loads them into self programming computer.
Gaitens, M. J.↗
Instrument for measuring torsional creep and recovery Patent
Measuring shear-creep compliance of solid and liquid materials used in spacecraft components
Plazek, D. J.↗
Intermittent type silica gel adsorption refrigerator Patent
Intermittent type silica gel adsorption refrigerator for providing temperature control for spacecraft components
Romvary, E., Jr.↗
Omni-directional anisotropic molecular trap Patent
Omnidirectional anisotropic molecular trap, used with vacuum pump to simulate space environments for testing spacecraft components
Hardgrove, W. F.↗
MSC Apollo 13 Investigation Team. Panel 6 - Related Systems Evaluation. Volume 3 - Command and Service Module
Analysis of spacecraft components and systems with potential for failures similar to Apollo 13 flight emergency
Source record↗
Redundant actuating mechanism Patent
Design and development of release mechanism for spacecraft components, releasable despin weights, and extensible gravity booms
Madey, J. M.↗
Space simulator Patent
Space environment simulator for testing spacecraft components under aerospace conditions
Stephens, J. B.↗
Development of technology for installation of mechanical fasteners
Investigation of variables affecting joint preload properties of installed structural bolts and nuts used in fabrication and construction of spacecraft components
Brenner, H. S.↗
Peak acceleration limiter for vibrational tester Patent
Electronic detection system for peak acceleration limits in vibrational testing of spacecraft components
Chapman, C. P.↗
Solid state thermal control polymer coating Patent
Development of solid state polymer coating for obtaining thermal balance in spacecraft components
Pezdirtz, G. F.↗
Development of parametric data for the establishment of an ethylene oxide cycle for the decontamination of spacecraft
Decontamination of spacecraft components with ethylene oxide as function of parameters of gas concentration, time, temperature, and relative humidity
Daley, D. J.↗
Services provided in support of the planetary quarantine requirements
Microbiological contamination of Apollo spacecraft components
Favero, M. S.↗
High voltage transmission microscopy of Surveyor 3 camera shrouds
The internal structure of painted and unpainted aluminum alloy sheet samples from the TV camera shrouds were examined by high-voltage transmission electron microscopy. No clear-cut evidence of radiation damage effects was observed. Noticeable differences in microstructures between the upper visor and the sides and bottom of the lower shroud suggest different thermal histories, and the maximum temperatures due to solar heating are estimated to be between 164 and 319 C. Some correlation between microstructures and maximum estimated temperature is noted. It is felt that the apparent temperature rise due to solar heating will not affect the structural integrity of spacecraft components except possibly for very long periods of exposure. However, substantial thermal diffusion could affect interpretation of solar wind rare gas studies.
Fisher, R. M.↗
Dynamic analysis for shuttle design verification
Two approaches that are used for determining the modes and frequencies of space shuttle structures are discussed. The first method, direct numerical analysis, involves finite element mathematical modeling of the space shuttle structure in order to use computer programs for dynamic structural analysis. The second method utilizes modal-coupling techniques of experimental verification made by vibrating only spacecraft components and by deducing modes and frequencies of the complete vehicle from results obtained in the component tests.
Fralich, R. W.↗
Planetary quarantine
Developed methodologies and procedures for the reduction of microbial burden on an assembled spacecraft at the time of encapsulation or terminal sterilization are reported. This technology is required for reducing excessive microbial burden on spacecraft components for the purposes of either decreasing planetary contamination probabilities for an orbiter or minimizing the duration of a sterilization process for a lander.
Source record↗