| 面向临近空间高机动目标的改进预测命中点规划方法 |
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| 引用本文： | 尹中杰,刘凯. 面向临近空间高机动目标的改进预测命中点规划方法[J]. 宇航总体技术, 2020, 4(2): 46-54 |
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| 作者姓名： | 尹中杰 刘凯 |
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| 作者单位： | 大连理工大学航空航天学院，大连 116024,大连理工大学航空航天学院，大连 116024 |
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| 摘 要： | 研究面向临近空间高超声速目标的预测命中点设计问题,考虑到高超声速目标机动能力强,拦截系统的目标预报弹道中存在多次出现斜距相同的情况,导致基于斜距的预测命中点设计方法不适用。通过引入目标弹道预划分手段,保证在每个预测命中点搜索区间的斜距具有单调性,以便可以快速有效搜索到预测命中点,解决当前方法的局限性。结合拦截弹的标准弹道族计算,提出了基于目标弹道预划分的改进预测命中点设计方法。在此基础上,考虑到延时发射,通过状态转换的方法,将三维平面进行降维处理,获得标准弹道族与目标弹道的所有位置重合点,并通过两者飞行时间时长对比筛选出可行拦截弹道方案,从而获得发射时间窗口。最后,通过开展仿真分析说明了提出方法的有效性。
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| 关 键 词： | 预测命中点；标准弹道族；发射时间窗口 |
Research on Improved Predicted Impact Point Planning for High Maneuvering Targets in Near Space |
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| YIN Zhongjie and LIU Kai. Research on Improved Predicted Impact Point Planning for High Maneuvering Targets in Near Space[J]. Astronautical Systems Engineering Technology, 2020, 4(2): 46-54 |
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| Authors: | YIN Zhongjie and LIU Kai |
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| Affiliation: | School of Aeronautics and Astronautics, Dalian University of Technology, Dalian 116024, China and School of Aeronautics and Astronautics, Dalian University of Technology, Dalian 116024, China |
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| Abstract: | In this paper, the design of predicted impact point for hypersonic target in near space is studied.Considering the strong maneuverability of hypersonic targets, the same skew range exists in the target prediction trajectory of interception system, which makes the design method of predicted impact point based on skew distance unsuitable.By introducing the method of pre-partition of targets trajectory, the oblique distance of each predicted impact point search interval is monotonous, so that the predicted impact point can be quickly and effectively searched, and the limitations of current methods can be solved.Combining with the calculation of standard trajectories of interceptor, an improved design method of predicted impact point based on pre-partition of target trajectory is proposed.On this basis, considering the delayed launch, the three planes are dimensionally reduced by the state transition method, and all the coincidence points between the standard trajectories and the target trajectory are obtained.Through the comparison of flight time, the feasible interception scheme is selected to obtain the launch time window.Finally, simulation analysis shows the effectiveness of the proposed method. |
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