Open Access
 Issue JNWPU Volume 39, Number 1, February 2021 141 - 147 https://doi.org/10.1051/jnwpu/20213910141 09 April 2021

This is an Open Access article distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

1 分阶段制导方案

 图1分阶段制导示意图

1.1 虚拟目标

 图2虚拟目标位置示意图

1.2 带落角约束的快速非奇异终端滑模制导律

 图3弹目相对运动关系

1.3 分段制导律设计

1) 滑翔段

2) 落角约束段

3) 截获调整段

4) 末制导阶段

 图4过载指令选择示意图

μ|ψFOV|＜qE＜|ψFOV|时, 根据qE的运动方向来确定aM的表达式。当qEμ|ψFOV|向|ψFOV|方向运动时, ; 反之, 当qE由|ψFOV|向μ|ψFOV|方向运动时,

5) 盲区段

RRcmin时, 制导系统停控, 该阶段制导指令为进入盲区时刻的制导指令, 直至命中目标。

2 全捷联导引头视线角速度估计

 图5全捷联导引头视线角速度估计方案结构图

2.2 视线角速度提取

r, α决定了跟踪的快速性；β影响噪声抑制效果。通过调整r, α, β 3个参数, 结合(22)式就可估计视线角速度。本文选取r=50, α=0.7, δ=5h, β=1.7, h为积分步长。

3 弹道仿真验证

GPS测量误差/m: Δx~(0, 100), Δy~(0, 152); 导引头测角误差/(°): ΔqB~(0, (0.286 5)2); 姿态角测角误差/(°): Δ~(0, 0.52)。

 图6弹目运动轨迹

 图7弹道倾角

 图8指令过载与实际过载

 图9视线角偏差qE

 图10估计值与真实值

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All Figures

 图1分阶段制导示意图 In the text
 图2虚拟目标位置示意图 In the text
 图3弹目相对运动关系 In the text
 图4过载指令选择示意图 In the text
 图5全捷联导引头视线角速度估计方案结构图 In the text
 图6弹目运动轨迹 In the text
 图7弹道倾角 In the text
 图8指令过载与实际过载 In the text
 图9视线角偏差qE In the text
 图10估计值与真实值 In the text

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