O2/H2 Advanced Maneuvering Propulsion Technology Program. Water-Cooled Segment Testing

Abstract

This report describes the analysis, design, fabrication, and test of water-cooled segments to define the most suitable injector configurations and combustion chamber geometries for 25,000-pound-thrust, O2/H2, lightweight, aerospike thrust chambers. Two-hundred and seventy-one hot-fire tests with numerous injector and chamber configurations were conducted at chamber pressures between 140 and 988 psi. The injector development was supplemented with cold- flow tests of single injection elements. High measured performance was demonstrated in low-volume combustion chambers (3.0-inch length from injector face to the throat).

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Apr 14, 1972
Accession Number
AD0893612

Entities

People

  • Dingbin Huang
  • H. G. Diem

Tags

Communities of Interest

  • Human Systems
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Combustion
  • Creep
  • Fabrication
  • Gaseous Fuels
  • Geometry
  • Heat Transfer
  • Hydrodynamics
  • Ignition
  • Ignition Systems
  • Measurement
  • Mechanical Properties
  • Pressure Measurement
  • Rocket Engines
  • Test And Evaluation
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Rocket Propulsion.
  • Software Engineering