Heating Rates in a High Energy Propulsion System (HEPS) Orbital Transfer Vehicle (OTV).

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)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1989
Accession Number
ADA214354

Entities

People

  • Rodney L. Miller

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Carbon Carbon Composites
  • Energy
  • Gas Turbine Nozzles
  • High Energy
  • Materials
  • Nozzles
  • Nuclear Energy
  • Nuclear Propulsion
  • Propulsion Systems
  • Radiation
  • Radiation Effects
  • Rocket Nozzles
  • Rocket Propulsion
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Missile Defense Systems.
  • Pulsed Power and Plasma Physics.
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster