A bimodal spacecraft bus based on a cermet fueled heat pipe reactor [electronic resource].
- Washington, D.C. : United States. Dept. of Energy, 1995. and Oak Ridge, Tenn. : Distributed by the Office of Scientific and Technical Information, U.S. Dept. of Energy.
- Physical Description:
- 9 pages : digital, PDF file
- Additional Creators:
- Sandia National Laboratories, United States. Department of Energy, and United States. Department of Energy. Office of Scientific and Technical Information
- Restrictions on Access:
- Free-to-read Unrestricted online access
- Bimodal space reactor systems provide both thermal propulsion for the spacecraft orbital transfer and electrical power to the spacecraft bus once it is on station. These systems have the potential to increase both the available payload in high energy orbits and the available power to that payload. These increased mass and power capabilities can be used to either reduce mission cost by permitting the use of smaller launch vehicles or to provide increased mission performance from the current launch vehicle. A major barrier to the deployment of these bimodal systems has been the cost associated with their development. This paper describes a bimodal spacecraft bus with performance potential to permit more than 70% of the instrumented payload of the Titan IV/Centaur to be launched from the Atlas IIAS. The development cost is minimized by basing the design on existing component technologies.
- Published through SciTech Connect., 07/01/1995., "sand--95-1510c", " aiaa--95-2773", "conf-950720--8", "DE95015086", AIAA/SAE/ASME joint propulsion conference and exhibit, San Diego, CA (United States), 10-12 Jul 1995., and Rochow, R.F.; Polansky, G.F.; Bixler, C.H.; Gunther, N.G.
- Funding Information:
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