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定向能载荷约束下面对称飞行器定向定姿制导技术研究

白璐1,林德福1,郑多2,尉明军3   

  1. 1. 北京理工大学
    2. 北京理工大学宇航学院
    3. 中国航天科工三院三部复杂系统控制与智能协同技术重点实验室
  • 收稿日期:2024-01-19 修回日期:2024-05-20 出版日期:2024-05-22 发布日期:2024-05-22
  • 通讯作者: 郑多
  • 基金资助:
    国家自然科学基金青年基金项目;教育部产学研创新项目;民用飞行器研究;北京理工大学青年教师学术启动计划

Research on guidance technology of specified direction and attitude for plane symmetrical aircraft with directed energy load constraint

1, 2,Duo Zheng 1   

  • Received:2024-01-19 Revised:2024-05-20 Online:2024-05-22 Published:2024-05-22
  • Contact: Duo Zheng
  • Supported by:
    National Natural Science Foundation of China;Civilian Aircraft Research;Beijing Institute of Technology Research Fund Program for Young Scholars

摘要: 机载定向能武器是未来攻防对抗中获得非对称优势的决定性因素之一。针对定向能载荷对目标有效毁伤要求下的面对称飞行器位置、航向、倾斜姿态等多约束问题,提出一种侧向加速度补偿的定向定姿多约束机动制导策略。描述了机载定向能对地面目标实施打击的任务场景,揭示了定向能载荷约束下面对称飞行器的机动规律及其对位置、航向、倾斜姿态等的约束条件;基于面对称飞行器运动学模型及其位置、定向、定姿等多约束条件,设计了“虚拟导引-定姿攻击”的机动制导策略,协调各约束施加的时间和条件,避免了过约束可能导致的指令解算困难问题。分析了各约束条件之间的耦合关联特性,提出了虚拟导引定向制导机制,引导飞行器沿指定航向飞向目标;在此基础上,提出了基于侧向加速度补偿的定向定姿机动策略,主动产生侧向加速度以实现飞行器动态平衡,保证面对称飞行器能够同时满足并维持定向能载荷正常工作所需要的航向和倾斜角约束,确保定向能载荷拥有充足的照射时间。仿真结果表明,研究提出的基于侧向加速度补偿的机动制导策略,能够满足定向能载荷约束下面对称飞行器的定向定姿制导任务要求,对支撑机载定向能武器的实际运用具有一定的参考价值。

关键词: 机载定向能, 面对称飞行器, 侧向加速度补偿, 倾斜角约束, 航向角约束

Abstract: Airborne directed energy weapons are one of the decisive factors to gain asymmetric advantages in future offensive and defensive confrontations. Aiming at the multiple constraint problem about the position, flight direction and bank attitude of the plane symmetrical aircraft under the requirement of effective damage to the target caused by directed energy load, a multiple constraint maneuvering guidance strategy with specified direction and attitude based on lateral acceleration compensation is proposed. The mission scenario of airborne directed energy loads attacking ground tar-gets is described, and the maneuvering laws as well as constraints of position, flight direction and bank attitude of the plane symmetrical aircraft restricted by directed energy load are revealed. Based on the kinematic model and multiple constraint such as position, specified direction and attitude of plane symmetrical aircrafts, the maneuvering guidance strategy of “virtual guidance - specified attitude attack” is designed to coordinate the imposed time and conditions of each constraint, which helps avoid the problem of command solution difficulty caused by excessive constraints. The coupling correlation characteristics existed in all constraints are analyzed, and a specified direction virtual guidance mechanism is proposed to guide the aircraft to the target on the specified course. On this basis, a specified direction and attitude maneuvering strategy with lateral acceleration compensation is proposed to actively generate the lateral acceleration for realizing dynamic balance of the aircraft, which could ensure that the plane symmetrical aircraft could simultaneously satisfy and maintain the heading angle as well as the bank angle constraints required for the normal operation of the directed energy load, and guarantee the directed energy load has sufficient irradiation time. The simu-lation results indicate that the proposed maneuvering guidance strategy based on lateral acceleration compensation can meet requirements of the guidance mission with specified direction and attitude of the plane symmetrical aircraft restricted by directed energy load, and has certain reference value for supporting the practical application of airborne directed energy weapons.

Key words: airborne directed energy, plane symmetrical aircraft, lateral acceleration compensation, bank angle constraint, heading angle constraint

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