宇航学报 ›› 2022, Vol. 43 ›› Issue (4): 403-412.doi: 10.3873/j.issn.1000-1328.2022.04.002

• 飞行器设计与力学 • 上一篇    下一篇

基于上升轨迹可达范围的目标拦截发射窗口计算

贾飞达,韩宏伟,温昶煊   

  1. 1.北京理工大学宇航学院,北京 100081; 2. 深空探测自主导航与控制工信部重点实验室,北京 100081
  • 收稿日期:2021-06-08 修回日期:2021-09-13 出版日期:2022-04-15 发布日期:2022-04-15

Calculation of Launch Window for Target Interception Based on Reachable Domain of Ascending Trajectory

JIA Fei da, HAN Hong wei, WEN Chang xuan   

  1. 1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;2. Key Laboratory of Autonomous Navigation and Control for Deep Space Exploration, Beijing 100081, China
  • Received:2021-06-08 Revised:2021-09-13 Online:2022-04-15 Published:2022-04-15

摘要: 针对低轨目标拦截任务,提出一种利用上升轨迹可达范围分析的发射窗口计算方法。首先,建立以上升时长和航程为性能指标的上升轨迹和优化模型,确定拦截器上升轨迹可达范围。然后,根据目标星下点与上升轨迹可达范围外包络的穿越关系以及拦截器的上升时长范围,对发射窗口进行初筛,得到准发射窗口。最后,针对每一段筛选出的准发射窗口,通过精确判定目标星下点与每一上升时长可达范围子环的位置关系,得到每段准窗口中能够实现目标拦截的发射窗口,将其取并集得到针对目标拦截的精确发射窗口。仿真表明本文提出的计算方法能够快速准确得到目标拦截的发射窗口。

关键词: 目标拦截, 可达范围, 发射窗口

Abstract: For low Earth orbit target interception, a launch window calculation method is proposed based on the analysis of reachable domain of ascending trajectory. Firstly, an ascending trajectory and optimization model is developed with the flight duration and range as performance functions, which is then adopted to solve the reachable domain of the interceptor’s ascending trajectory. Secondly, a conservative launch window for a given target is initially screened out based on the traversal relationship between the target sub satellite point and the outer envelope of the solved reachable domain. Finally, an accurate launch window for target interception can be obtained by accurately determining the positional relationship between the sub satellite points of the target and each reachable domain for every flight duration. Simulation results show that the proposed calculation strategy can obtain the launch window with high efficiency and accuracy.

Key words: Target interception, Reachable domain, Launch window

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