A bimodal spacecraft bus based on a cermet fueled heat pipe reactor

Conference · Sat Jul 01 04:00:00 UTC 1995

OSTI ID:100221

Polansky, G F ^[1]; Rochow, R F ^[2]; Gunther, N G ^[3]; Bixler, C H ^[4]

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1. Sandia National Labs., Albuquerque, NM (United States)
2. Novatech, Lynchburg, VA (United States)
3. Gunther Associates, San Jose, CA (United States)
4. Consultant, Mannford, OK (United States)

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.

• Research Organization: Sandia National Labs., Albuquerque, NM (United States)
• Sponsoring Organization: USDOE, Washington, DC (United States)
• DOE Contract Number: AC04-94AL85000
• OSTI ID: 100221
• Report Number(s): SAND--95-1510C; AIAA--95-2773; CONF-950720--8; ON: DE95015086
• Country of Publication: United States
• Language: English

Related Subjects

21 SPECIFIC NUCLEAR REACTORS AND ASSOCIATED PLANTS
CERMETS
COST
DESIGN
ENERGY CONVERSION
FUEL ELEMENTS
HEAT PIPES
NESDPS Office of Nuclear Energy Space and Defense Power Systems
REACTOR SAFETY
SPACE POWER REACTORS
SPACE PROPULSION REACTORS
SPACE VEHICLES