EXPERIMENTAL INVESTIGATION OF STAGED PUMPING TECHNIQUES FOR THE REMOVAL OF ROCKET EXHAUST GASES FROM SPACE SIMULATION CHAMBERS

Abstract

Results of an experimental investigation conducted to determine the feasibility of using titanium gettering to remove large flows of H2 gas and of combining gettering and cryopumping in a staged pumping system to remove simulated rocket exhaust gases are presented. The staged pumping system (about 8 in. in diameter and less than 30 in. long) consisted of a 77K cryopumping stage, a 20K cryopumping stage, and a titanium gettering stage with 77K surfaces. High temperature combustion exhaust gas mixtures, with flow rates up to about 0.3 gm/ sec, were pumped, and a pressure level of about 0.001 torr was maintained.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1966
Accession Number
AD0633471

Entities

People

  • B. A. Mccullough
  • W. G. Kirby

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Contracts
  • Cryopumping
  • Diameters
  • Elements
  • Exhaust Gases
  • Flow Rate
  • Gas Flow
  • Gases
  • Gettering
  • Heat Energy
  • High Temperature
  • Ionization Gages
  • Measurement
  • Pumping
  • Rocket Exhaust
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Human-Computer Interaction (HCI).

Technology Areas

  • Space
  • Space - Hall-Effect Thruster