THRUST VARIATION OF A GASEOUS PROPELLANT ROCKET ENGINE

Abstract

The purpose of this thesis was to investigate the performance of a variable thrust rocket engine incorporating a variable area injector. The injector was designed, constructed, and assembled on an existing thrust chamber which was lengthened and provided with water cooling. Gaseous hydrogen and oxygen were used as propellants. The thrust was varied over a continuous range from 11 to 75 pounds, resulting in a throttling ratio of 6.82:1, while the specific impulse remained nearly constant. The transient response of the engine was fast, smooth, and accurate, and no indication of combustion instability was observed during the investigation.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1967
Accession Number
AD0817981

Entities

People

  • Frederick J. De Groot

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Combustion
  • Combustion Chambers
  • Control Systems
  • Engineering
  • Flow Rate
  • Heat Transfer
  • Mass Flow
  • Mechanical Engineering
  • Mixtures
  • Plastic Explosives
  • Pressure Regulators
  • Rocket Engines
  • Spacecraft
  • Specific Impulse
  • Test Facilities
  • United States

Fields of Study

  • Physics

Readers

  • Aerospace Propulsion Engineering.
  • Computational Modeling and Simulation
  • Internal Combustion Engine (ICE) Technology.