Abstract
A distributed multi-missile cooperative guidance law based on the finite time theory is proposed to solve the terminal guidance problem of three-dimensional multi-missiles cooperative interception of large maneuvering target. According to the finite time consistency theory, an adaptive guidance law based on the integral sliding mode is designed to ensure that all missiles can reach the target at the same time in the terminal guidance process. The longitudinal and lateral acceleration of the line of sight are based on the guidance law of the fast terminal sliding mode surface. The terminal attack angle is constrained, so that the terminal attack Angle can reach the expected value in finite time. The simulation results show that the designed guidance law can achieve the cooperative attack on the maneuvering targets.
Highlights
多导弹协同制导。 如文献[ 16] 在传统比例导引的 基础上,提出了一种“ 领弹-从弹” 策略来实现多枚 导弹的协同攻击,将领弹的剩余距离和弹道偏角误 差作为参考状态变量。 文献[ 17] 则提出设置 1 枚 虚拟领弹,从而把时间约束转换为非线性化跟踪问 题。 文献[18] 设计了反馈线性化的协同制导律,使 每个从弹的攻击时间都能够在有限时间内收敛。
[5] 王建青, 李帆, 赵建辉, 等. 多导弹协同制导律综述[ J] . 飞行力学, 2011, 29(4) : 6⁃10 WANG Jianqing, LI Fan, ZHAO Jianhui, et al Summary of Guidance Law Based on Cooperative Attack of Multi⁃Missile Method [ J]
A distributed multi⁃missile cooperative guidance law based on the finite time theory is proposed to solve the terminal guidance problem of three⁃dimensional multi⁃missiles cooperative interception of large maneuvering tar⁃ get
Summary
多导弹协同制导。 如文献[ 16] 在传统比例导引的 基础上,提出了一种“ 领弹-从弹” 策略来实现多枚 导弹的协同攻击,将领弹的剩余距离和弹道偏角误 差作为参考状态变量。 文献[ 17] 则提出设置 1 枚 虚拟领弹,从而把时间约束转换为非线性化跟踪问 题。 文献[18] 设计了反馈线性化的协同制导律,使 每个从弹的攻击时间都能够在有限时间内收敛。 因此得到三维制导模型下弹-目相对运动方程: r rq 2β cos2 qε 2 β sinqε cosqε X26 sinqε cosqε ïïẋ5 = x6 ï îïïẋ6 2x4i x6i tanqεi aMβi x1i cosqεi aTβi x1i cosqεi ( ∑ ) ∑ unorm i sign n cij( tfj - tfi )
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