A model of AP/HTPB composite propellant combustion in rocket-motor environments

Weidong Cai, Piyush Thakre, Vigor Yang

研究成果: Article同行評審

89 引文 斯高帕斯(Scopus)

摘要

A comprehensive theoretical/numerical model for treating AP/HTPB composite-propellant combustion in a rocket-motor environment is presented. The formulation takes into account the conservation equations in both the gas and condensed phases, and accommodates finite-rate chemical kinetics and variable thermophysical properties. The processes in the two phases are coupled at the surface to determine the propellant burning behavior. An asymptotic analysis based on a large activation-energy approximation for the condensed-phase decomposition is applied to help resolve the combustion wave structure in the interfacial layer. A simplified global reaction is employed to characterize the final diffusion flame between the decomposition products of AP and the pyrolysis products of HTPB. Only laminar flows are considered here, to avoid complications arising from turbulence. A detailed parametric study is conducted on the gas-phase flame structures of AP/HTPB composite propellants. The dependence of burning rate, flame stand-off distance, and heat-release distribution on AP particle size, chamber pressure, and gas-phase reaction rates is studied systematically. The phenomenon of erosive burning due to the strong crossflow in a rocket-motor environment is also examined.

原文English
頁(從 - 到)2143-2169
頁數27
期刊Combustion science and technology
180
發行號12
DOIs
出版狀態Published - 2008 十二月

All Science Journal Classification (ASJC) codes

  • Chemistry(all)
  • Chemical Engineering(all)
  • Fuel Technology
  • Energy Engineering and Power Technology
  • Physics and Astronomy(all)

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