A model of AP/HTPB composite propellant combustion

Weidong Cai, Vigor Yang

Research output: Contribution to conferencePaperpeer-review

11 Citations (Scopus)


A numerical/theoretical analysis has been performed to study combustion of AP/HTPB composite propellants in rocket-motor environments. The conservation equations accommodating flnite-rate chemical kinetics with variable thermophsyical properties in both condensed and gas phases are solved using finite- volume technique. The matching conditions at the interface follow the conservation laws of mass and energy. A parametric study on the gas-phase flame structure is carried out. Dependence of burning rate on pressure and AP particle size is also studied in depth. Good agreement between the experimental data and present computation is achieved. Under-prediction of influence of crossflow indicates erosive burning is a joint effect of flame bending and turbulence-enhanced mixing.

Original languageEnglish
Publication statusPublished - 2000
Event38th Aerospace Sciences Meeting and Exhibit 2000 - Reno, NV, United States
Duration: 2000 Jan 102000 Jan 13


Other38th Aerospace Sciences Meeting and Exhibit 2000
Country/TerritoryUnited States
CityReno, NV

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering


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