THE DESIGN AND MANUFACTURE OF A 6 INCH DIAMETER ABLATIVE COMBUSTION CHAMBER.

Abstract

A 6 in. diameter ablative combustion chamber has been designed for use in evaluation tests on rocket engine components. This combustion chamber was designed for operation at 1000 psia chamber pressure with the propellant combination N2O4 and 50% N2H4 - 50% UDMH at a mixture ratio of 2.1/1. This report presents the design and fabrication of two complete combustion chamber assemblies and two spare combustion chamber liners. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1965
Accession Number
AD0819226

Entities

People

  • W. Q. Walker

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Assembly
  • Chambers
  • Combustion
  • Combustion Chamber Liners
  • Combustion Chambers
  • Diameters
  • Engine Components
  • Engines
  • Fabrication
  • Rocket Engines

Fields of Study

  • Physics

Readers

  • Rocket Propulsion.
  • Software Engineering