Unsteady solid propellant pressure combustion response using a piston burner

B. Saarloos, M. Q. Brewster

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

A small-scale solid propellant laboratory burner has been designed to operate under piston-driven oscillating conditions from 40 to 400 Hz and 300 to 900 kPa mean pressure, with 10% amplitudes. The device was used to investigate the burning rate response of a widedistribution, bimodal AP (2:200 μm)-HTPB (IPDI) composite propellant (MURI TKC#5b). Results show that mean pressure and exit temperature decrease with increasing frequency due to increased heat transfer associated with oscillatory gas motion. Propellant burning rate is calculated numerically from pressure, volume, and frequency data using mass and energy balances. A linear analytic solution for pressure and temperature frequency response is also obtained for the case of constant mass injection to characterize general system behavior. The dynamic burning rate response appears to be nearly linear at low frequencies (< 150 Hz) and increasingly non-linear at higher frequencies due to an increasing combustion response magnitude with frequency and nearly constant relative pressure amplitude. In the range of frequencies determined to be most linear (40 to 150 Hz), the magnitude of the pressure-coupled frequency response ranges from 2 to 7 ± 1, with burning rate lagging pressure by 50 to 75°. The in-phase (real) component of the response ranges from 1 ± 1 to 4 ± 2. The results demonstrate the potential for the piston burner to measure pressure frequency response at low frequencies and also to measure non-linear dynamic burn rates over a range of frequencies at high spectral resolution within a single test. The results also demonstrate that nonlinear response can appear as spectral structure in the apparent linear response when the data are interpreted linearly.

Original languageEnglish (US)
Title of host publication41st Aerospace Sciences Meeting and Exhibit
StatePublished - Dec 1 2003
Event41st Aerospace Sciences Meeting and Exhibit 2003 - Reno, NV, United States
Duration: Jan 6 2003Jan 9 2003

Publication series

Name41st Aerospace Sciences Meeting and Exhibit

Other

Other41st Aerospace Sciences Meeting and Exhibit 2003
CountryUnited States
CityReno, NV
Period1/6/031/9/03

Fingerprint

solid propellants
Solid propellants
burners
pistons
Fuel burners
Pistons
combustion
burning rate
frequency response
Frequency response
HTPB propellants
composite propellants
Composite propellants
low frequencies
propellant
Spectral resolution
mass balance
propellants
Propellants
Energy balance

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Saarloos, B., & Brewster, M. Q. (2003). Unsteady solid propellant pressure combustion response using a piston burner. In 41st Aerospace Sciences Meeting and Exhibit (41st Aerospace Sciences Meeting and Exhibit).

Unsteady solid propellant pressure combustion response using a piston burner. / Saarloos, B.; Brewster, M. Q.

41st Aerospace Sciences Meeting and Exhibit. 2003. (41st Aerospace Sciences Meeting and Exhibit).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Saarloos, B & Brewster, MQ 2003, Unsteady solid propellant pressure combustion response using a piston burner. in 41st Aerospace Sciences Meeting and Exhibit. 41st Aerospace Sciences Meeting and Exhibit, 41st Aerospace Sciences Meeting and Exhibit 2003, Reno, NV, United States, 1/6/03.
Saarloos B, Brewster MQ. Unsteady solid propellant pressure combustion response using a piston burner. In 41st Aerospace Sciences Meeting and Exhibit. 2003. (41st Aerospace Sciences Meeting and Exhibit).
Saarloos, B. ; Brewster, M. Q. / Unsteady solid propellant pressure combustion response using a piston burner. 41st Aerospace Sciences Meeting and Exhibit. 2003. (41st Aerospace Sciences Meeting and Exhibit).
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