Abstract
To intercept a higher-speed target in the terminal guidance phase, this paper proposes a generalized relative biased proportional navigation (BPN) law. In order to enlarge the capture domain of the classical proportional navigation (PN) law and make full use of the maneuverability of a missile, the paper designs time-varying navigation coefficients; thus the modified PN guidance law integrates the advantages of the PN guidance law with those of the retro-PN guidance law. In order to intercept high-speed targets with impact angle constraints, the relative BPN law is introduced, and the impact angle is achieved by controlling the relative flight-path angle. In order to improve the performance of the guidance law for intercepting higher-speed maneuvering targets, some compensation measures are designed for guidance commands. Extensive simulations are conducted to verify the design features of the proportional navigation law.
Highlights
To intercept a higher⁃speed target in the terminal guidance phase, this paper proposes a generalized rela⁃ tive biased proportional navigation ( BPN) law
Journal of Guidance, Control, and Dynamics, 2018, 41(3) : 779⁃787 [7] 刁兆师,单家元
Summary
针对以上问题,本文提出了一种拦截高速运动 目标的广义相对偏置比例制导律。 为解决经典常系 数比例导引法捕获域较小的问题,本文将目标视为 一个虚拟静止目标,通过相对关系,推导出一种可使 导引系数自适应调节的制导律基本形式,以使所提 制导方案可综合顺轨和逆轨 2 种拦截模式,并具有 更大的捕获域及过载利用能力。 在此基础上,为解 决含碰撞角约束打击高速运动目标的问题,借助相 对偏置比例的思想以及小角度假设的方法,通过控 制相对飞行轨迹角以间接地实现对碰撞角的约束。 此外,为解决目标机动对制导性能的影响,对制导指 令进行了目标机动补偿,使所提制导方案在拦截高 速机动目标及对其进行碰撞角约束时也具有较好的 制导性能。 下几个区间: CPN = { γM ∶ γM,1 < γM < γM,2 } üïï CRPN = { γM ∶ γM,2 < γM < γM,3 } ý C = { γM ∶ γM,1 < γM < γM,3 } þïï 通过分析,可得 {Ne > 0, ∀γM ∈ CPN; Ne < 0, ∀γM ∈ CRPN
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