| 带落速落角约束的高超声速飞行器俯冲轨迹规划方法 |
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| 引用本文： | 梁子璇,黄美伊,冉宇寰,朱圣英.带落速落角约束的高超声速飞行器俯冲轨迹规划方法[J].宇航学报,2022,43(8):1052-1060. |
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| 作者姓名： | 梁子璇 黄美伊 冉宇寰 朱圣英 |
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| 作者单位： | 1. 北京理工大学深空探测技术研究所,北京 100081；2. 深空自主导航与控制工信部重点实验室,北京 100081 |
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| 基金项目： | 国家自然科学基金（61803008，62073034）；中国科协青年人才托举工程（2019QNRC001） |
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| 摘 要： | 针对高超声速飞行器俯冲段精确打击任务需求,提出了一种能够同时满足落速与落角约束的轨迹规划方法。建立了两段式轨迹规划策略,第一段采用参数化控制剖面调节飞行速度,第二段采用传统偏置比例导引律实现落角控制。将控制剖面的参数设计分解为多参数优化与单参数搜索两个问题：通过离线求解可行初始位置范围最大的多参数优化问题,提高控制剖面对初始偏差的适应性；通过在线求解带罚函数的单参数搜索问题,得到落速偏差最小的俯冲轨迹。结合高超声速飞行器模型,对所提出的俯冲轨迹规划方法进行了仿真。结果表明,该方法能够得到满足落速与落角约束的俯冲轨迹,具有较好的求解效率,且对初始状态偏差具有较强的鲁棒性。
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| 关 键 词： | 高超声速飞行器 俯冲段 落速约束 落角约束 轨迹规划 |
| 收稿时间： | 2022-02-27 |
Diving Trajectory Planning Method for Hypersonic Vehicles with Terminal Velocity and Impact Angle Constraints |
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| LIANG Zixuan,HUANG Meiyi,RAN Yuhuan,ZHU Shengying.Diving Trajectory Planning Method for Hypersonic Vehicles with Terminal Velocity and Impact Angle Constraints[J].Journal of Astronautics,2022,43(8):1052-1060. |
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| Authors: | LIANG Zixuan HUANG Meiyi RAN Yuhuan ZHU Shengying |
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| Affiliation: | 1. Institute of Deep Space Exploration, Beijing Institute of Technology, Beijing 100081, China;2. Key Laboratory of Autonomous Navigation and Control for Deep Space Exploration, Ministry of Industry and Information Technology, Beijing 100081, China |
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| Abstract: | To meet the requirements of precision strike of hypersonic vehicles in the diving phase, a trajectory planning method with terminal velocity and impact angle constraints is proposed. A two stage trajectory planning strategy is established. In the first stage, a parameterized control profile is used to adjust the flight velocity, and in the second stage, a bias proportional navigation guidance law is used for the impact angle constraint. The control profile parameters are determined by solving a multi parameter optimization problem and a single parameter searching problem. The multi parameter optimization is solved offline to maximize the feasible zone of the initial position, which improves the adaptability to initial errors. The single parameter searching with a penalty function is conducted onboard, which yields a constrained diving trajectory. The proposed trajectory planning method is verified by simulations using a hypersonic vehicle model. The results indicate that the method satisfies both the terminal velocity and impact angle constraints, has good computational performance, and is robust to the initial dispersions. |
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| Keywords: | Hypersonic vehicles Diving phase Terminal velocity constraint Impact angle constraint Trajectory planning |
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