基于多拦截器协同攻击优化公式的轨迹整形制导

Hyeong-Geun Kim, Jongho Shin
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引用次数: 0

摘要

在本研究中,我们提出了一种最佳制导结构,可实现多枚导弹齐射攻击时的撞击角和时间限制。作为推导制导法则的第一步,我们使用相对射程的多项式函数定义了满足撞击角和时间约束的理想视角轮廓。制导指令根据最优化公式进行配置,以实现所需的视角轮廓,同时最大限度地减少法向加速度的使用。根据所提出的法则,所产生的轨迹以多项式形式表示,其指数可以选择,以满足各种曲率的撞击路线所需的约束条件。此外,由于实施时不需要曲率半径较小的轨迹难以估算的到达时间,因此所提出的法则可以实现广泛的终点约束。数值模拟结果表明,在各种终端条件下,所提出的法则都能实现精确拦截,从而验证了所提出的法则。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Trajectory-shaping guidance based on optimality formulation for cooperative attack of multiple interceptors
In this study, we present an optimal guidance structure that achieves impact angle and time constraints for the salvo attack of multiple missiles. As the first step in deriving a guidance law, we define a desired profile of the look angle that satisfies the impact angle and time constraints using a polynomial function of the relative range. The guidance command is configured based on the optimality formulation that achieves the desired profile of the look angle while minimizing the usage of the normal acceleration. The resulting trajectory under the proposed law is expressed as a polynomial form whose exponents can be selected to satisfy the desired constraints with the impact courses of various curvatures. In addition, the proposed law can achieve a wide range of terminal constraints since the time-to-go, which is difficult to estimate for a trajectory with a small radius of curvature, is not required for implementation. The numerical simulation results show that the proposed law achieves precise interception under various terminal conditions, validating the proposed law.
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