考虑减速伞二次充气过程的星际飞船返回轨道研究  

Research on Starliner’s Return Trajectory Considering Parachutes’Re-inflation

作　　者：王征[1] 朱如意[1] 曹晓瑞[1] 刘敏华[1] Wang Zheng;Zhu Ru-yi;Cao Xiao-rui;Liu Min-hua(China Academy of Launch Vehicle Technology,Beijing,100076)

机构地区：[1]中国运载火箭技术研究院,北京100076

出　　处：《导弹与航天运载技术》2022年第3期82-86,共5页Missiles and Space Vehicles

摘　　要：为降低飞船返回过程中接地速度、提高着陆指标设计精度,飞船返回轨道设计成为保障宇航员能够安全着陆、船体能够再次重复使用的关键。以美国波音公司星际飞船为研究背景,综述了星际飞船首飞试验任务情况,简化飞船返回飞行程序;考虑两种主要摄动因素及减速伞二次充气过程,分别建立了飞船返回过程中离轨段与再入段飞行动力学模型;最后,通过数学仿真验证了飞船返回轨道设计方法的有效性。In order to reduce landing speed and to improve the accuracy of landing indicator,return trajectory design of spaceship is the key technology to determine whether astronauts can land safely,or the spaceship can be reused.Based on the Boeing’s CST-100 Starliner,the first Orbital Flight Test mission is summarized,and the spaceship’s return procedure is simplified.Considering two main perturbations and the re-inflation process of the parachutes,the diorite and reentry phases’flight dynamics model have been established respectively.Finally,the effectiveness of return trajectory designing method is verified by mathematical simulation.

关 键 词：星际飞船 二次充气 飞行动力学 返回轨道 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程] V417.7