高速再入飞行试验再入条件优化设计

飞行器返回再入时将经历极高的气动热环境，因此深空探测返回飞行器，尤其是载人飞船需要通过实际飞行试验验证相关性能，为降低成本和研制风险，通常采用大再入角和相对第二宇宙速度较低的再入速度进行飞行试验。为获得能实现高热流密度验证的最小能量再入任务方案，采用优化设计手段对飞行试验的再入角和速度以及倾侧角控制进行设计，经仿真分析表明，优化结果可达到飞行试验要求的热流密度，并可将再入速度需求降低约2．1 km／s。

Initial EntryC ondition Optimization of High-Speed Entry Flight Test for Deep Space Exp loration Vehicles

When performing earth reentry ,deep space exploration vehicles suffer high heat load .In order to validate relevant system performance ,entry flight tests are often carried out for deep space exploration vehicles,especially for crew vehicles.For the sake of retrenching funds and reducing mission risk ,deep space exploration vehicle flight tests often perform earth entry in large flight path angle and relatively high speed ,instead of entry in second cosmic velocity .In this study ,we propose an optimization method for ini-tial entry condition of high-speed entry flight test .We validate the proposed method by an entry flight test mission,and simulation show that the exact heat load is acquired with reducing 2.1 km/s velocity demand .