Ignition of composite solid propellants: Model development, experiments, and validation

J. W. Weber, K. C. Tang, M Quinn Brewster

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

Abstract

In this work, ignition of the aluminized composite solid propellant used in the space shuttle by a radiant source is experimentally and numerically investigated. A critical ignition temperature model (Tign=600 K) for an inertly heated solid with in-depth absorption is demonstrated to provide reasonable estimates of ignition times over a range of fluxes from 20-200 W/cm2. Experimental data for comparison includes selfsustained deflagration (go/no-go) and first-light times. It was found that for 10.6-μm radiation the firstlight and go/no-go boundary times were quite similar at low fluxes, with a time vs. flux slope near -1.8 on a log-log plot. A slight slope break near 80 W/cm2 was observed in the go/no-go boundary results, leading to a slope of -1.45 between 100 and 200 W/cm2. The model matches the slope over the range of fluxes reasonably well, including the slope break. The first visible light emission was generally observed at or near the surface of the propellant, rather than in the gas phase. The effects of a slight room temperature convective crossflow (hc ~ 140 W/m2K) on ignition times were also investigated.

Original languageEnglish (US)
Title of host publication39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
StatePublished - Dec 1 2003
Event39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2003 - Huntsville, AL, United States
Duration: Jul 20 2003Jul 23 2003

Publication series

Name39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Other

Other39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2003
CountryUnited States
CityHuntsville, AL
Period7/20/037/23/03

Fingerprint

Solid propellants
Ignition
Fluxes
Composite materials
Experiments
Space shuttles
Light emission
Propellants
Radiation
Temperature
Gases

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

Cite this

Weber, J. W., Tang, K. C., & Brewster, M. Q. (2003). Ignition of composite solid propellants: Model development, experiments, and validation. In 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit (39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).

Ignition of composite solid propellants : Model development, experiments, and validation. / Weber, J. W.; Tang, K. C.; Brewster, M Quinn.

39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2003. (39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).

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

Weber, JW, Tang, KC & Brewster, MQ 2003, Ignition of composite solid propellants: Model development, experiments, and validation. in 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2003, Huntsville, AL, United States, 7/20/03.
Weber JW, Tang KC, Brewster MQ. Ignition of composite solid propellants: Model development, experiments, and validation. In 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2003. (39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).
Weber, J. W. ; Tang, K. C. ; Brewster, M Quinn. / Ignition of composite solid propellants : Model development, experiments, and validation. 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2003. (39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).
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