防热环对空气舵舵轴流动及气动加热影响

空气舵缝隙内的舵轴是高速飞行器受热最严酷的部位之一。为减小舵轴的防热压力, 通过在舵轴周围设计防热环, 将舵轴的高热流区转移到防热环, 大幅减小舵轴的气动热载荷, 从而有效实现舵轴承力功能和防热环承热功能的分离。通过数值计算和试验研究分析了舵轴防热环的降热效果与机理, 获得以下结论: 通过有无防热环方案的仿真和试验对比, 表明了增加防热环能够明显降低舵轴热环境; 通过对舵缝隙内外流动的细致分析, 给出了舵轴防热环通过转移高热流区降低舵轴热流的降热机理; 通过不同舵偏和不同流态有无防热环方案数值计算的对比表明了防热环对舵轴热流的降低作用具有广泛适用性。 

Effect of Thermal-Protection Ring on Flow and Aeroheating of Rudder Shaft

The rudder shaft in the gap is one of the most severely heated parts of high speed aircrafts. In order to reduce the thermal-protection pressure of rudder shaft, the heat load of rudder shaft is greatly reduced by transferring the high heat flux zone from the rudder shaft to the thermal-protection ring. It effectively realizes the separation of the force load bearing function of rudder shaft and the thermal load bearing function of thermal-protection ring. In this paper, three research aspects were carried out. Firstly, the comparison of thermal environment of rudder shaft with or without thermal-protection ring between simulations and experiments was studied and the results show that the heat flux of rudder shaft can be obviously decreased by using the thermal-protection ring. Secondly, it shows that the way of reducing the thermal environment of rudder shaft is feasible by transferringrudder shaft's high heat flux zone to thermal-protection ring. Thirdly, the influence of rudder deflection on reducing thermal environment of the rudder shaft was studied by analyzing the law of the thermal environment with different rudder deflections.