Accession Number:

AD0861818

Title:

Stability Correlation Between the Pulse Motor Combustion Tool and a Full-Scale Engine.

Descriptive Note:

Technical rept. Nov 65-Sep 67,

Corporate Author:

AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Report Date:

1969-08-01

Pagination or Media Count:

105.0

Abstract:

A comparative stability evaluation was made between the Pulse Motor combustion tool and a full-scale engine. Sixty-two hot firings were conducted with the full-scale engine and 27 with the Pulse Motor, using four different injection patterns. The primary propellant combination was N2O450 N2H4-50 UDMH, although N2O4MMH and N2O4UDMH were also used. Testing was conducted at chamber pressures of 300 and 600 psia with a mixture ratio range of 1.8 to 2.2. The pulse gun stability-rating technique was used to artifically perturb the combustion process. Stability correlation between the Pulse Motor and full-scale engine was then evaluated by comparing the system response parameters, such as damping rate functions, pulse charge required for instability, resultant pressure perturbations, peak oscillation amplitudes, instability modes and frequencies, and combustion efficiency. Author

Subject Categories:

  • Combustion and Ignition
  • Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE