Accession Number:

AD0817981

Title:

THRUST VARIATION OF A GASEOUS PROPELLANT ROCKET ENGINE

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1967-06-01

Pagination or Media Count:

80.0

Abstract:

The purpose of this thesis was to investigate the performance of a variable thrust rocket engine incorporating a variable area injector. The injector was designed, constructed, and assembled on an existing thrust chamber which was lengthened and provided with water cooling. Gaseous hydrogen and oxygen were used as propellants. The thrust was varied over a continuous range from 11 to 75 pounds, resulting in a throttling ratio of 6.821, while the specific impulse remained nearly constant. The transient response of the engine was fast, smooth, and accurate, and no indication of combustion instability was observed during the investigation.

Subject Categories:

  • Combustion and Ignition
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE