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首页> 外文期刊>IEEE Transactions on Aerospace and Electronic Systems >Quaternion Based Three-Dimensional Impact Angle Control Guidance Law
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Quaternion Based Three-Dimensional Impact Angle Control Guidance Law

机译：基于四维冲击角控制指导法

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摘要

This article deals with a guidance law for impact angle control (IAC) in the 3-D space. Extended from the 2-D IAC law, the proposed guidance law is derived using a quaternion. The general form of the IAC law comprises a biased proportional navigation guidance (PNG) law, wherein a component to control the impact angle is added to the PNG law. Since the biased term consists of a rotation angle and Euler axis obtained by a quaternion coordinate transformation between the missile's velocity vector and the desired impact angle, the magnitude of the guidance command depends on the rotation angle multiplied by the biased term. Therefore, from attempting to minimize the control energy, the optimal impact roll angle causing the rotation angle to be zero is mathematically derived. The Euler axis that satisfies this optimal impact roll angle is composed of two velocity vectors; the angle between the two velocity vectors is the minimum rotation angle. Numerical simulations are performed for stationary and moving targets according to the desired impact angle.
机译：本文涉及三维空间中的冲击角控制（IAC）的指导法。从2-D IAC法延伸，所提出的指导法使用四元素来得出。 IAC法的一般形式包括偏置比例导航引导（PNG）定义，其中将用于控制冲击角的组分添加到PNG法中。由于偏置术语由导弹速度矢量与所需冲击角之间的四元轴坐标变换而获得的旋转角度和欧拉轴，因此引导命令的幅度取决于旋转角乘以偏置术语。因此，从尝试最小化控制能量，数学导出了使旋转角度为零的最佳冲击辊角。满足该最佳冲击辊角的欧拉轴由两个速度矢量组成;两个速度矢量之间的角度是最小旋转角度。根据所需的冲击角对静止和移动目标进行数值模拟。

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