Accession Number : ADA214354
Title : Heating Rates in a High Energy Propulsion System (HEPS) Orbital Transfer Vehicle (OTV).
Descriptive Note : Final rept. Jun-Aug 89,
Corporate Author : ASTRONAUTICS LAB (AFSC) EDWARDS AFB CA
Personal Author(s) : Miller, Rodney L.
Report Date : OCT 1989
Pagination or Media Count : 27
Abstract : 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 W/cc) was significantly higher than that found in the carbon-carbon nozzle (approx. 8 W/cc). Keywords: High energy propulsion system; Orbital transfer vehicle; Rocket nozzle analysis; Nuclear heating; Nuclear propulsion. (jhd)
Descriptors : *NUCLEAR PROPULSION, *SPACE TUGS, HIGH ENERGY, RELIABILITY, TRANSFER TRAJECTORIES, HEATING, RADIATION HARDENING, ROCKET NOZZLES, CARBON CARBON COMPOSITES.
Subject Categories : Nuclear Propulsion
Laminates and Composite Materials
Distribution Statement : APPROVED FOR PUBLIC RELEASE