Modeling combustion of laminate propellants with fine ammonium perchlorate

P. Genevieve, M. Q. Brewster

Research output: Contribution to conferencePaper

Abstract

The combustion of AP/HTPB laminate propellants is investigated theoretically. Numerical computations are based on finite-rate chemistry with simplified kinetics and a free surface. Both pure and oxygenated binders (loaded with fine AP) are considered. The model shows the ability to qualitatively predict relative protrusion and recession of AP and binder as well as diffusion flame shape. The results show that fine-AP loading has a pronounced effect on the surface and flame structure. The addition of fine AP shows the predominance of a premixed flame over the diffusion flame, which persists over a range of laminate thickness from 100 to 600 μm. The surface profile is also modified toward a recession of the binder with respect to AP as the width increases. The binder surface remains relatively flat (unlike the case of pure binder, which protrudes noticeably), and burns ahead of the AP, which lags behind at the pressures simulated (10 to 30 atm).

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

    Fingerprint

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Genevieve, P., & Brewster, M. Q. (2002). Modeling combustion of laminate propellants with fine ammonium perchlorate. Paper presented at 40th AIAA Aerospace Sciences Meeting and Exhibit 2002, Reno, NV, United States.