固体火箭尾流场对舱体冲击效应研究

Study on the Impacts of Solid Rocket Plume Flow Field on Payload Fairings

火箭燃气射流对搭载平台的冲击效应是搭载平台表面防护和结构设计的重要依据。为研究不同射角下高速射流对舱体的冲击效果,基于有限体积法,采用SST k-ω湍流模型,建立固体火箭发射过程的三维仿真物理模型。分别在70°射角和56°射角工况下,对固体火箭发动机喷出的燃气射流进行数值模拟,得到了不同时刻射流的特性以及两射角下舱体上表面受射流影响情况,分析射流对舱体表面的冲击效应。分析结果表明,射流冲出喷管后在空气中膨胀,形成曲面激波。抵达舱体表面后压缩,产生高温高压区,随后温度和压力沿舱体表面流动逐渐降低。舱体表面温度和压力变化趋势相一致,56°射角时舱体表面温度较低,受到的冲击效应更大。

The impact of the rocket missile’s gas jet on the carrying platform is a crucial consideration for surface protection and structural design.In order to investigate the impact effects of high-speed jets on the fuselage at different angles,a three-dimensional simulation physical model of the solid rocket launch process is established using the finite volume method and the SST k-ωturbulence model.Numerical simulation is conducted for the gas jet ejected from the solid rocket engine at both 70°and 56°angles,obtaining the characteristics of the jet at different time points and analyzing the impact of the jet on the surface of the fuselage at the two angles.The results indicate that,after the jet exits the nozzle,it expands in the air,forming a curved shock wave.Upon reaching the surface of the fuselage,it compresses,creating a high-temperature and high-pressure zone.Subsequently,the temperature and pressure gradually decrease along the surface of the fuselage.The trends in temperature and pressure changes on the fuselage surface are consistent,with the fuselage surface temperature being lower at a 56°angle,resulting in a greater impact effect.