ADIABATIC COMPRESSOR PROPULSION SYSTEM,

Abstract

A method to improve the performance of solid-core nuclear rocket engines is examined. The device proposed employs an adiabatic compressor to raise the fuel specific impulse of hydrogen which has already been directly heated by a nuclear reactor. A preliminary design of the compressor is presented, and the over-all system described. A mission analysis is discussed. It appears that this device has a performance capability for certain missions intermediate between the direct heating nuclear rocket and the electrical propulsion schemes. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 13, 1960
Accession Number
AD0606016

Entities

People

  • K. D. Favro
  • R. B. Reddy

Organizations

  • TRW Inc.

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Compressors
  • Engineering
  • Engines
  • Hydrogen
  • Mechanical Engineering
  • Nuclear Reactors
  • Propulsion System Components
  • Propulsion Systems
  • Rocket Engines
  • Rockets
  • Specific Impulse
  • Thrusters

Fields of Study

  • Physics

Readers

  • Internal Combustion Engine (ICE) Technology.
  • Quantum spin resonance or Electron Paramagnetic Resonance spectroscopy.
  • Theoretical Analysis.