Advanced Maneuvering Propulsion Technology Program

Abstract

The engine design and analysis task was continued with a (1) detailed parametric analysis of thrust chamber temperature and pressure drop characteristics, (2) revision of the engine balance, and (3) continued main oxidizer and turbine control valve design activity. The engine critical component task effort was primarily directed toward the completion of fabrication of the prototype channel-wall thrust chamber segment. Design of the main thrust chamber nozzle has been completed and design of the base closure and secondary engine nozzle simulator is nearing completion.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1969
Accession Number
AD0504212

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Combustion Chambers
  • Composite Materials
  • Computer Programs
  • Control Systems
  • Engine Components
  • Fabrication
  • Fluid Flow
  • Heat Transfer
  • Heat Transfer Coefficients
  • Manufacturing
  • Materials
  • Mechanical Properties
  • Parametric Analysis
  • Performance Tests
  • Test And Evaluation
  • Thrust Chambers

Fields of Study

  • Physics

Readers

  • Internal Combustion Engine (ICE) Technology.
  • Rocket Propulsion.
  • Systems Analysis and Design