Accession Number:

AD0893612

Title:

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

Descriptive Note:

Final rept. 1 Dec 1970-3 Dec 1971

Corporate Author:

ROCKETDYNE CANOGA PARK CA

Personal Author(s):

Report Date:

1972-04-14

Pagination or Media Count:

409.0

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, O2H2, 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.

Subject Categories:

  • Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE