Heating Rates in a High Energy Propulsion System (HEPS) Orbital Transfer Vehicle (OTV).
Final rept. Jun-Aug 89,
ASTRONAUTICS LAB (AFSC) EDWARDS AFB CA
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Rocket propulsion systems which use nuclear energy sources present unique challenges to the design, safety, and reliability of the concept. Since the vehicle and its components must operate in high radiation fields, nuclear heating and radiation effects must be determined and factored into the system design. This report analyzed the nuclear heating in a High Energy Propulsion System HEPS Orbital Transfer Vehicle OTV nozzle. Using the FEMP2D Finite Element, Multigroup, Pn, 2-Dimensional code for an aluminum and carbon-carbon nozzle, it was determined that the heating contribution was found to be the significant source of heating for both materials. The overall heating rate in the aluminum nozzle approx. 12 Wcc was significantly higher than that found in the carbon-carbon nozzle approx. 8 Wcc. Keywords High energy propulsion system Orbital transfer vehicle Rocket nozzle analysis Nuclear heating Nuclear propulsion. jhd
- Nuclear Propulsion
- Unmanned Spacecraft
- Laminates and Composite Materials