LIQUID INJECTION THRUST VECTOR CONTROL

Abstract

The technique of obtaining thrust vector control by the injection of a liquid into the supersonic region of a rocket nozzle was studied. Liquids studied were water, Freon-12, Perchloroethylene, nitrogen tetroxide and bromine. In addition, unsymmetrical dimethylhydrazine and inhibited red fuming nitric acid were injected simultaneously to explore the effect of energy release in the nozzle exit cone with bipropellant injection. Data on the relationships of side force to injectant flow rate, the effect of axial location of the injection port, the effect of injection pressure and the effects of injectant properties are presented and discussed. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jun 16, 1961
Accession Number
AD0268731

Entities

People

  • C.j. Green
  • F. Mccullough Jr

Organizations

  • Naval Air Weapons Station China Lake

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Combustion
  • Engineers
  • Flow Rate
  • Guided Missiles
  • Jet Propulsion
  • Liquid Propellants
  • Materials Laboratories
  • Measurement
  • Munitions
  • Plastic Explosives
  • Propellants
  • Propulsion Systems
  • Rocket Oxidizers
  • Secondary Flow
  • Test And Evaluation

Readers

  • Analytical Chemistry
  • Combustion and Flow Dynamics.
  • Rocket Propulsion.

Technology Areas

  • Hypersonics