Unsteady pressure combustion response of AP composite propellants

B. Saarloos, M. Q. Brewster

Research output: Contribution to conferencePaper

Abstract

A small-scale laboratory burner has been set-up to operate under driven pressure oscillating conditions. Pressure oscillations are created by oscillating the volume of the combustion chamber using a piston assembly. The oscillation amplitude to mean ratios of the volume and pressure range from 7 to 10 percent. Pressure, volume, and temperature are measured during a test. Speed (frequency) versus time is also tracked for the duration of the test. Preliminary results show some interesting phenomena, including a mean pressure that decreases with increasing frequency. The rate of change of speed also has an effect on mean pressure. The decrease in mean pressure is enhanced during periods of increasing frequency, and depreciated during periods of decreasing frequency. This suggests non-linear combustion behavior.

Original languageEnglish (US)
StatePublished - Dec 1 2002
Event40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States
Duration: Jan 14 2002Jan 17 2002

Other

Other40th AIAA Aerospace Sciences Meeting and Exhibit 2002
CountryUnited States
CityReno, NV
Period1/14/021/17/02

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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    Saarloos, B., & Brewster, M. Q. (2002). Unsteady pressure combustion response of AP composite propellants. Paper presented at 40th AIAA Aerospace Sciences Meeting and Exhibit 2002, Reno, NV, United States.