固体运载火箭底部对流热环境数值模拟

Numerical Simulation of Convection Heating Flux in Solid Rocket Base

采用数值仿真方法,开展了固体运载火箭底部对流热环境计算研究。采用线性化热力学参数的单一介质简化处理方法,模拟了发动机喷流与高速主流的流场,得到了热流与温度参数,并与飞行试验结果进行了对比分析。结果表明固体运载火箭底部存在较为严酷的对流热环境,本文的数值计算结果与真实飞行试验结果吻合较好,该方法可为固体运载火箭的热环境与防热设计提供参考。

The numerical simulation method is used to study the convective thermal environment at the bottom of solid launch vehicle.The flow field of the engine jet and the high-speed mainstream is simulated by a simplified method,using a single medium of linear thermodynamic parameters.The heat flux and temperature are obtained and compared with flight test results.The results show that the thermal environment at the bottom is really critical.And the numerical simulation results are in good agreement with the results of the real flight test,which can provide a reference for the thermal environment and thermal protection design of solid launch vehicle.