THRUST OPTIMIZATION OF A NUCLEAR ROCKET OF VARIABLE SPECIFIC IMPULSE,

Abstract

A simple relation is derived between the specific impulse and the flow rate of a gas under the reactor operating conditions allowing molecular dissociation of the gas. Utilizing this relation, an optimum variable thrust program to maximize velocity is obtained for a vertically ascending vehicle under the assumptions of constant gravity and zero aerodynamic drag. The advantage of this program is demonstrated by comparison with the usual constant thrust program. (Author)

Document Details

Document Type
Technical Report
Publication Date
May 29, 1958
Accession Number
AD0606336

Entities

People

  • C. J. Wang
  • G. W. Anthony
  • H. R. Lawrence

Organizations

  • TRW Inc.

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Drag
  • Dissociation
  • Drag
  • Flow Rate
  • Optimization
  • Physical Properties
  • Specific Impulse
  • Thrust

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Propulsion Engineering.
  • Fluid Dynamics.