复合推进剂固体火箭发动机喷流流场数值模拟

Numerical simulation of composite solid propellant rocket motor exhaust plume

采用CEA(Chemical Equilibrium with Applications)计算复合推进剂化学平衡组分及喷管入口参数,随后通过FLUENT对固体火箭发动机喷管-尾喷焰流场进行了一体化数值仿真。采用时间推进法及AUSM空间离散格式数值求解二维轴对称Navier-Stokes方程组,采用k-ε湍流模型模拟喷流与环境大气的掺混,并考虑了H2、CO、HCl在喷流流场中的二次燃烧,运用拉格朗日方法模拟Al2O3颗粒与喷流的相互作用。计算在不同高度和马赫数下展开,给出了不同情况下的流场分布。结果表明,H2、CO、HCl的二次燃烧对喷流流场影响显著;随着高度的增加,喷流流场影响域扩大;随着来流马赫数增加,喷流流场波节数降低。

Tbe CEA（ Chemical Equilibrium with Applications）was used to calculate the equilibrium composition of composite propellant and inlet parameter of the nozzle.Then numerical simulations of solid rocket motor nozzle and exhaust plume flow-field were carried using FLUENT software. The 2D axisymmetric Navier-Stokes equations were solved by time-marching method and AUSM spatial discretization scheme.The k-8 turbulence model, chemical kinetics and Lagrange method were taken to describe turbu- lence, H2, CO, HC1 afterburning and gas-particle（ A1203 ）interaction in the exhaust plume.The calculation was made at different altitude and Mach number.The flow-fields under different conditions were described.The results show that： the afterburning of H2, CO and HC1 has significantly influence on the plume flow-field, the flow-field expands along with the increasing of altitude, and the wave number is reduced with the increasing of Mach number.