BLOCK II AJ10-137 APOLLO SERVICE MODULE ENGINE TESTING AT SIMULATED HIGH ALTITUDE (REPORT II, PHASE IV DEVELOPMENT)

Abstract

Developmental testing was conducted on the Aerojet-General Corporation AJ10-137, Block II, Apollo Service Module Propulsion engine. The Block II engine was designed to improve performance and structural durability and was operated at nominal conditions of 97-psia chamber pressure and 1.6 mixture ratio was nitrogen tetroxide and Aerozine-50 propellants. Primary objectives of these tests were to determine engine ballistic performance and to verify durability of a new combustion chamber design. Performance and durability of off-design chamber pressures and mixture ratios were also documented. The test results presented indicate the trend in performance as a function of chamber pressure, propellant temperature, and mixture ratio. Erosion and blistering occurred in the ablative lining of the first two chambers tested. Altered construction of the last four chambers produced excellent durability.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1967
Accession Number
AD0812441

Entities

People

  • A. L. Berg
  • J. F. Deford
  • M. W. Mcilveen

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Actuators
  • Air Force
  • Combustion
  • Combustion Chambers
  • Engines
  • Heat Of Combustion
  • Ignition
  • Liquid Propellants
  • Materials
  • Measurement
  • Propellants
  • Propulsion Systems
  • Rocket Engines
  • Service Modules
  • Spacecraft
  • Strain Gages
  • Test Facilities

Readers

  • Internal Combustion Engine (ICE) Technology.
  • Software Engineering
  • Surface Coatings Technology.