脉冲推力轨道拦截可达性描述及求解方法  

Description and Solutin of Orbit Interception Accessibility with Impulse Thrust

作　　者：李彬 郑伟[1] 张洪波[1] LI Bin;ZHENG Wei;ZHANG Hongbo(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073)

机构地区：[1]国防科技大学空天科学学院

出　　处：《飞控与探测》2019年第4期26-36,共11页Flight Control & Detection

摘　　要：针对航天器单脉冲轨道拦截可达性分析问题,基于共面变轨、逆轨拦截假设,考虑能量、时间和交会角约束,提出了拦截航天器可拦截区和可发射区的概念。在航天器单脉冲空间可达范围的基础上,进一步考虑了目标轨道的约束,建立了目标轨道命中区的计算策略,对异面轨道交叉点为燃料最省点做出了解释。把拦截可达性相关的问题归纳为8个基本拦截问题,通过这8个问题的组合,描述了考虑能量、时间和交会角约束下拦截问题的可拦截区和可发射区的计算方法。采用圆轨道共面变轨、逆轨拦截场景进行了仿真验证,结果表明该方法能够快速有效地计算出约束条件下航天器的拦截可达范围,能够用于分析特定任务情况下的拦截可达性。Aiming at the accessibility analysis for spacecraft orbit interception problem,the concepts of intercepting region and launching region for the interception spacecraft are proposed,based on the assumption of coplanar maneuver and head-on interception.Three constraints of energy,time and intersection angle are considered in the analysis.On the basis of the space reachable domain for spacecraft with single impulse,the calculating strategy of the hit region on the target orbit is established with taking the target orbit constraint into account.It is explained that the cross-over point of two non-coplanar orbits is the fuel-optimal point in the interception mission.The problems related to interception accessibility are summarized into eight basic interception problems.Through the combination of them,the calculation method of the intercepting region and launching region under the constraint of energy,time and intersection angle is described.The simulation analysis is carried out in the scene of coplanar transfer and head-on interception between two circular orbits.Simulation results show that this method can calculate the interception reachable domain for spacecraft under three constraints quickly and effectively,and can be used to analyze the interception accessibility for spacecraft in specific mission scenario.

关 键 词：航天器 脉冲推力 轨道拦截 可达范围 任务规划 

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]