Design considerations for the small scientific satellite
Small scientific satellite design guidelines and concepts, noting flexibility regarding accommodation of variety of missions for magnetosphere studies
Longanecker, G. W.↗
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Results for “Guidelines”
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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Conference scope and noise concepts
Guidelines and objectives of aircraft noise reduction conference
Hubbard, H. H.↗
Power distribution characteristics for overload protection.
Overload protection guidelines for power subsystems, discussing source and protective device characteristics emphasizing spacecraft requirements
Pellmann, R. R.↗
Design guides for irradiation experiments with fast spectrum reactor fuel elements in thermal test reactors
Design guidelines for irradiation experiments with fast spectrum reactor fuel elements in thermal test reactors
Anderson, J. L.↗
Solid Rocket Motor Metal Cases
Guidelines and practices for design of solid rocket motor cases
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Research on long term biological isolation of primates and mice. Volume 3 - Standing operating procedures for primate isolation study, appendix J Final report
Operating guidelines for experiments in biological isolation of primates
Bengson, M. H.↗
Thermionic Spacecraft Design Study
This report presents the results of a design study of nuclear-electric propelled unmanned spacecraft. The electric power source is in-core thermionic reactors based on either the internally (flashlight) or externally fueled diode concept. The study guidelines and approach are defined. The characteristics of the candidate launch vehicles, thrust subsystem, and communications subsystem are presented. The definition of two spacecraft/powerplant configurations are presented which deliver 240 kWe net to the thruster array. This definition, presented for both the flashlight and externally fueled reactors includes the key items of spacecraft arrangement and a detailed weight breakdown. Power conditioning, heat rejection subsystem, shielding, and spacecraft structure are detailed. The results show about a 30 percent weight advantage for the spacecraft based on the externally fueled reactor. This is primarily due to a 120 vdc power output from the externally fueled reactor, as compared to a 15 vdc power output from the flashlight reactor. Weight reduction by improved technology could further reduce the weight by 5 to 15 percent.
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Interplanetary space environment
Interplanetary space data for use as spacecraft development program design criteria guidelines
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Terrestrial space
Data on earth atmosphere above 90 km for use as spacecraft development program design criteria guidelines
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Cislunar space
Cislunar space data for use as spacecraft development program design criteria guidelines
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