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 language | English (US) |
|---|---|
| Title of host publication | 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit |
| State | Published - Dec 1 2003 |
| Event | 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2003 - Huntsville, AL, United States Duration: Jul 20 2003 → Jul 23 2003 |
Publication series
| Name | 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit |
|---|
Other
| Other | 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2003 |
|---|---|
| Country | United States |
| City | Huntsville, AL |
| Period | 7/20/03 → 7/23/03 |
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ASJC Scopus subject areas
- Aerospace Engineering
- Control and Systems Engineering
- Electrical and Electronic Engineering
Cite this
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 proceeding › Conference contribution
}
TY - GEN
T1 - Ignition of composite solid propellants
T2 - Model development, experiments, and validation
AU - Weber, J. W.
AU - Tang, K. C.
AU - Brewster, M Quinn
PY - 2003/12/1
Y1 - 2003/12/1
N2 - 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.
AB - 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.
UR - http://www.scopus.com/inward/record.url?scp=84897818213&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84897818213&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84897818213
SN - 9781624100987
T3 - 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
BT - 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
ER -