固体发动机燃气射流对发射平台冲击效应研究

Study on the impact effect of solid rocket motor exhaust plume to the launching platform

为研究燃气射流对发射平台的热冲击和动力冲击效应,采用有限速率化学反应模型和H2/CO反应体系模拟了燃气射流中的复燃现象,得到了射流流场结构及发射平台上的温度和压力分布情况,计算结果与试验数据吻合较好。研究表明,在射流近场内考虑复燃效应时,计算结果更为准确。发射平台中心处为高温区,应采用抗高温耐烧蚀的材料。发射平台距发动机喷口为1.4、1.7、2 m时,平台上压力分布变化不大;发射平台离发动机喷口越远,平台上的温度变化越小。

To study the thermo-impact and the dynamical impact of the exhaust plume to the launching platform,the finite rate chemistry model and H2/CO chemistry system were used to simulate the afterburning phenomenon of plume.The temperature and pressure on the launching platform and the exhaust plume contours were obtained.The simulated results were in accordance with that of experiment.The results show that it is reasonable to calculate the close range exhaust plume in considering the afterburning.The launching platform centre region is the high temperature zone and should be defended by the high temperature resistant material.In the range of 1.4 m,1.7 m and 2 m apart of the motor nozzle,the pressure is less influenced by the distance and the temperature decreases with the distance increase.