本文建立高超声速气动热和结构传热的松耦合计算方法,以探路者号火星探测器为研究对象,开展了探测器高超声速气动热和结构传热的耦合计算研究,分析了探测器进入条件下某轨道点上气动加热和结构传热机理.耦合计算表明,随着时间的推进,表面结构温度逐渐升高,壁面热流相对降低,表面趋向辐射平衡温度.因热防护系统结构传热时间尺度长于飞行器进入过程总时间,探测器进入的真实过程滞后于辐射平衡过程.耦合研究表明,使用耦合计算方法能较好地再现真实的气动加热和结构传热过程.
Loosely coupled method of aeroheating and heat transfer computation was established in this paper,based on which coupled analysis for Mars Pathfinder entry vehicle was performed to illustrate the mechanism between hypersonic flowfield aeroheating and structural heat transfer during its entry.Coupled computation results show that the surface temperature increases and the heatflux decreases dnring the coupled process and the thermal state on the surface ultimately tends to radiative-equilibrium.The actual entry process is considered to lag behind that on the surface radiative-equilibrium hypothesis due to longer scale time of heat transfer in the thermal protection system than the total entry time.Consequently,the coupled method is suggested to better simulate aeroheating and heat transfer problems.
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