Injector/Chamber Scaling Evaluation-TRW Injector Development

Abstract

This report describes the results of TRW injector development tests. This project, a task under the overall Minimum Cost Design Space Launch Vehicle (MCD/SLV) Program, has as a goal the development of low-cost injectors capable of performing at 90% theoretical Isp (shifting), 250,000-lb thrust using N2O4/UDMH propellants, and will evaluate their scalability up to the multimillion-lb- thrust class. A total of seven injector and three chamber configurations were tested. Maximum performance obtained was approximately 88% of test site theoretical shifting Isp (90% vacuum Isp). Dynamic combustion characteristics of this concept were evaluated by artificially inducing chamber pressure overpressures of 100% or greater. In all tests, chamber pressure recovered to within 10% of the original value within 30 to 40 milliseconds, and the engine is considered dynamically stable.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1969
Accession Number
AD0507734

Entities

People

  • Bernard R. Bornhorst
  • Donald A. Grimes
  • Michael F. Powell
  • Mitchell J. Fleiszar Jr.
  • Patrick W. Powell

Organizations

  • Air Force Research Laboratory

Tags

DTIC Thesaurus Topics

  • Air Force
  • Combustion
  • Combustion Chambers
  • Engineering
  • Engineers
  • Fabrication
  • Flow Rate
  • Government Procurement
  • Launch Vehicles
  • Mechanical Engineering
  • Plastic Explosives
  • Propellants
  • Propulsion Systems
  • Recording Systems
  • Rocket Propulsion
  • Test And Evaluation
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Aerospace Propulsion Engineering.
  • Internal Combustion Engine (ICE) Technology.
  • Software Engineering

Technology Areas

  • Space
  • Space - Hall-Effect Thruster