再入攻角对弹头锥身气动热环境及结构热响应影响研究

目的分析再入弹头锥身气动热环境及结构热响应,研究再入攻角振荡对其影响规律。方法建立基于工程法的气动热/结构热响应耦合计算方法,并采用该方法开展锥身典型位置气动热环境及结构热性计算分析。结果随着再入攻角的振荡衰减,各典型子午面冷壁热流密度曲线围绕90°子午面热流密度曲线振荡,其振幅呈现先振荡增大、后振荡衰减的变化规律。与90°子午面相比,各子午面总加热量均有所增大。再入攻角振荡引起的金属层外壁面温度最大振荡幅值为3K,但对最终时刻结构温度影响较小。结论计算弹道条件下,再入飞行攻角振荡对气动热环境及结构热响应影响较小,可通过增加余量的方式给予考虑。

Effect of the Attack Angle on the Reentry Warhead Aerodynamic Heating Environment and Structure Thermal Response

The paper aims to study the effect of the flying attack angle on the aerodynamic heating environment and structure thermal response of reentry warhead. A coupling calculation method based on engineering algorithm for the aerodynamic heating environment and structure thermal response was built, and the aerodynamic heating environment and structure thermal response of the reentry warhead were calculated and the effect of the attack angle was studied based on this method. With the oscillation attenuation of the reentry attack angle, the heat flux curve on every typical meridian plane oscillates around the curve in 90° meridian plane and the amplitude first increases and then decreases. The total reentry heat transfers in all typical planes increases compared with that in 90° meridian plane. The maximal amplitude of the temperature on the metal layer due to the oscillation attenuation of the attack angle is 3 K during reentry process, while it has little effect on the structure temperature at last time. In the computational ballistic condition,the oscillation attenuation of the attack angle has little effect on aerodynamic heating environment and structure thermal response ,which can be improved by increasing allowance.