An Experimental Evaluation of 100-lb-Thrust Ablatively Cooled Rocket Engines

Abstract

Five 100-lb-thrust ablatively cooled chambers, designed and fabricated by industrial companies, were subjected to test firings in a partial assessment of the state of the art of this type of chamber design. The severity of the test conditions (nitrogen tetroxide and hydrazine burned at a nominal pressure of 150 psia) caused all but two of the chambers to fail or erode excessively before 500 sec of firing time had elapsed. Both of the more resistant chambers had hard throat inserts of silicon carbide or molybdenum.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1966
Accession Number
ADB209443

Entities

People

  • R. N. Porter
  • W. H. Tyler

Organizations

  • California Institute of Technology

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Assembly
  • Body Weight
  • Ceramic Materials
  • Combustion
  • Combustion Chambers
  • Construction
  • Fibers
  • Films
  • Hot Spots
  • Jet Propulsion
  • Materials Laboratories
  • Materials Processing
  • Rocket Engines
  • Silicon Carbide
  • Test And Evaluation
  • Test Equipment
  • Test Facilities

Readers

  • Aerospace Test and Evaluation
  • Rocket Propulsion.
  • Surface Engineering/Surface Coating Technology.