INVESTIGATION OF SCAVENGING SYSTEMS FOR REMOVAL OF ROCKET EXHAUST GASES FROM SPACE SIMULATION CHAMBERS

Abstract

Tests were conducted on a rocket exhaust scavenging system as part of a program to develop new techniques for testing at simulated space conditions. Detailed plume characteristics were computed, and a model scavenging system was tested for both cold and hot gas rockets. Results indicate that for the firing of a typical small control rocket it will be possible to maintain 0.0001 torr pressure in a space chamber.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1966
Accession Number
AD0637702

Entities

People

  • D. E. Anderson
  • J. A. Morris

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Back Pressure
  • Computer Programs
  • Exhaust Gases
  • Gases
  • Hot Gases
  • Mass Spectrometers
  • Measurement
  • Motion Picture Cameras
  • Partial Pressure
  • Pressure Gages
  • Rocket Exhaust
  • Secondary Flow
  • Simulators
  • Space Simulation Chambers
  • Test Facilities
  • Vacuum Chambers

Fields of Study

  • Physics

Readers

  • Parallel and Distributed Computing.
  • Plasma Physics.
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster