高速再入飞行试验再入条件优化设计  

Initial Entry Condition Optimization of High-Speed Entry Flight Test for Deep Space Exploration Vehicles

作　　者：吴文瑞[1] 黄震[1] 侯砚泽[1] 

机构地区：[1]中国空间技术研究院载人航天总体部,北京100094

出　　处：《航空计算技术》2016年第5期1-3,8,共4页Aeronautical Computing Technique

基　　金：国家自然科学基金项目资助(61403028)

摘　　要：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。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.

关 键 词：深空探测飞行器 第二宇宙速度 飞行试验 再入弹道 优化设计 

分 类 号：V41[航空宇航科学与技术—航空宇航推进理论与工程] O242[理学—计算数学]