导弹发射产生的高温燃气会对发射装置造成严重的烧蚀作用。为了研究发射装置的热防护问题,提出一种在导流器内布设竖直向上的喷水管道方案,利用液态水的汽化吸热原理和冲击作用实现对发射装置的热防护。基于Mixture多相流模型,耦合液态水的汽化方程与组分运输模型,分析该方案的降温机理及效果;对不同喷水速度工况下的燃气流场进行了数值模拟,得出不同喷水速度与降温效果之间的变化规律。结果表明,经过导流器内布设的管道喷水后,导流器表面和发射车壁面会形成水膜,对高温燃气起到隔离作用,发射装置温度明显下降。随着喷水速度增大,导流器表面和发射车壁面形成的水膜厚度变厚,对燃气的隔离作用更明显;当喷水速度增加到55 m/s时,燃气射流直接冲击区域的液态水汽化速率最大,相同时间内吸热量最多,该区域温度达到最低,故喷水速度55 m/s对流场的降温效果最佳。该结论可为导弹发射装置的热防护设计提供理论参考。

When the vehicle missile launches, the high-temperature gas can cause severe ablation to the launch devices. In order to research the thermal protection of the launch devices, a scheme of water pipes which are mounted in the deflector is proposed. The realization of thermal protection of the devices is based on the endothermic gasification principle and the impact of liquid water. Based on the Mixture multiphase flow model and coupled with the vaporization equation of liquid water and species transport model, the flow field under different injection speed conditions are numerically simulated. Finally, the relationship between injection speed and cooling effect is obtained. The results show that after injecting water through water pipes mounted in the deflector, the water film can be formed on the devices which can isolate the high-temperature gas and the temperature of the devices reduced greatly. The higher injecting speed, the thicker the water film on the launcher surface, and the more obvious isolation effect on gas. When the injecting speed reaches 55 m/s, the vaporization rate and the heat absorption in the area which the gas jet can directly impact reaches the maximum, and temperature of this area is the lowest, so this condition is the best condition with the best cooling effect. The result of the research can be regarded as a reference for the thermal protection design of the launch devices.