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ELECTRIC PROPULSION AND POWER REQUIREMENTS FOR SPACE VEHICLES
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English
Abstract
Electric propulsion fundamentals are briefly covered along with several types of electric propulsion thrust devices and their characteristics. Several possible missions are listed which could be applicable for electric propulsion. Power requirements are presented in parametric form for the specific missions of a low-altitude sustainer and orbit transfers. Off-optimum operations are considered in the case of the 200–22,300 mile orbit transfer. Other missions such as changing the orbital plane are briefly covered.
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Citation
STULL, F. and SHIEL, V., "ELECTRIC PROPULSION AND POWER REQUIREMENTS FOR SPACE VEHICLES," SAE Technical Paper 600285, 1960, https://doi.org/10.4271/600285.Also In
References
- WADC Technical Note 59–156, “Ion Propulsion Mission Requirements and Their Effect on Ion Engine Design” Vincent W Shiel, Propulsion Laboratory March 1959
- WADC Technical Note 59–78, “An Ion Propulsion Test Facility” Ferguson Joseph M Shiel Vincent W. Robert E. Supp, Propulsion Laboratory January 1959
- WADC Technical Report 59–189, “A Preliminary Engineering Evaluation of Advanced Space Propulsion Systems” I & II Mosser Paul S Page Russell J. Stover Willis Plasmadyne Corporation March 1959
- Report R-1383–3, “Propulsion Requirements for Controllable Satellites” Edelbaum T. N. United Aircraft Corporation Research Department November 1959
- WADC Technical Report 59–365, “Advanced Space Propulsion Systems, Mission Analysis and Propulsion System Matching” New Devices Laboratories, Thompson Ramo-Wooldridge, Inc July 1959