高超声速飞行器主动冷却系统优化设计

以碳氢燃料为冷却剂的主动冷却系统是进行高超声速飞行器热防护最有效的方法之一。在满足工作要求的情况下，应尽量减小主动冷却系统的质量，实现飞行器的轻质化目标。利用MATLAB@2007软件对高超声速飞行器燃烧室的主动冷却系统进行了优化设计，计算了冷却通道在满足各项热负荷条件下，系统的最小质量以及此时所对应的冷却通道各项尺寸。选择了Inconel X-750、Inconel 625和Hastelloy X 这3种不同的镍基合金分别当做冷却通道固壁材料，并且在主动冷却系统的近燃烧侧引入热障涂层，以分析不同材料和有无热障涂层对系统轻质化的影响，为高超声速飞行器主动冷却系统的材料选择和优化设计提供了理论依据。

Optimal Design for Active Cooling System of Hypersonic Vehicle

Active cooling with hydrocarbon-fuel is one of the most effective ways for hypersonic vehicle thermal protection. In order to enture the lightweight of a flight vehicle it is very necessary to minimize the weight of the active cooling system under working conditions. This paper provides an optimization method for the purpose by developing a code based on MATLAB@2007. The code is applied to calculate the minimum weight and the structure dimensions of the active cooling system under various loading conditions. Three Ni-based alloys including Inconel X-750, Inconel 625 and Hastelloy X are selected as the solid materials of the active cooling system, respectively. A thermal barrier coating is applied on the actively cooled panel side near the combustion chamber to discuss the thermal barrier coating's effect on minimizing the weight. This work is helpful in testing the optimal result of different materials and provides a good theoretical foundation for the material selection and optimal design of the active cooling system.