升力式飞行器最短返回时间离轨点设计方法  

A Minimum-Time Deorbit Point Design Method of Lifting Reentry Vehicle

作　　者：丁宁 李兆亭 张洪波[1] Ding Ning;Li Zhaoting;Zhang Hongho(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073

出　　处：《航天控制》2023年第1期31-38,共8页Aerospace Control

摘　　要：针对升力式飞行器升阻比较大、横向再入机动能力较强的特点,提出了一种综合考虑着陆场位置、返回时间和离轨燃耗约束的最短时间离轨点设计方法。首先,在飞行器运行轨道和着陆场位置给定的条件下,求解了着陆点与星下点轨迹的最小横向距离,并考虑位置及时间约束,根据再入可达域参数确定了再入航程角和再入时间范围。其次,考虑离轨燃耗约束,推导了再入角给定时离轨航程角和离轨时间的解析计算方法,采用牛顿迭代法求解二者取值范围。最后,依据离轨段及再入段航程角范围确定了离轨窗口,用非线性优化方法求解了返回时间最短的离轨点位置。数值仿真表明,所提方法能实现多约束下的飞行器最短返回时间离轨轨道计算,具有较好的适应性,可为航天器离轨方案设计提供参考。According to the large lift-drag ratio and strong lateral reentry maneuverability of lifting reentry vehicle, a design method for the minimum-time deorbit point is proposed, which involves the landing position, return time and deorbit burnup constraints for consideration. Firstly, the minimum lateral distance between the landing site and the ground track is solved under the given conditions of the vehicle′s orbit and landing position. By considering the position and time constraints, the reentry range angle and reentry time range are determined according to the parameters of reentry landing footprint. Secondly, under the fuel consumption constraint, the analytical calculation method of the deorbit range angle and time for given reentry angle is derived, and the value range of the two is solved by Newton’s iteration method. Finally, the deorbit window is determined according to the range angle in deorbit and reentry stage, and the minimum-time deorbit point is solved by nonlinear optimization method. Numerical simulation shows that the shortest deorbit time calculation can be achieved by using this method under multiple constraints, which has good adaptability and can serve as a reference for spacecraft deorbit design.

关 键 词：升力式飞行器 离轨制动 离轨点设计 再入角 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]