地外天体起飞时进入喷管内部激波对喷管的力、热效应

Force and heat effect of shock wave in nozzle interior on nozzle for celestial body outside earth taking off

为研究激波进入喷管内部对发动机喷管产生的力、热效应,对喷管与起飞平台基面之间的羽流场进行了大量的仿真计算,着重分析了不同导流型面、不同起飞偏角情况下,进入喷管内部激波对喷管产生的力、热综合效应,激波在喷管内部的分布形态,并给出了激波移出喷管的条件.结果表明:当激波进入喷管内部但不产生激波贴壁现象时,激波不会对喷管内壁产生附加的力、热冲击;当激波进入喷管内部且产生激波贴壁现象时,在激波贴壁区产生一定的附加力矩和附加热流.该结论对探测器结构布局的设计具有重要的指导作用.

In order to study the force and heat effects of the shock wave on nozzle, nu- merical simulation was carried out. The effects of force and heat on the nozzle, and the dis- tribute pattern of the shock wave inside the nozzle were mostly analyzed when the probe rose in different flow deflectors and rising angles. The condition for the shock wave to leave from the interior of nozzle was achieved. When the shock wave entered the interior of nozzle but did not cling to the wall of nozzle, the extra force and heat was not generated. But when the shock wave in the interior of nozzle clung to the wall of nozzle, the extra force and heat was generated in the wall-clinging area. The conclusion makes contribution to the structural lay-out design of the probe.