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首页> 外文期刊>IEEE Transactions on Aerospace and Electronic Systems >Range-to-go weighted optimal guidance with impact angle constraint and seeker's look angle limits
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Range-to-go weighted optimal guidance with impact angle constraint and seeker's look angle limits

机译：具有冲击角约束和导引头视线范围限制的按距离加权最优制导

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摘要

In this paper, an impact angle control guidance law, which considers simultaneously the impact angle and seeker's look angle constraints, is proposed for a constant speed missile against a stationary target. An optimal control theory with state variable inequality constraint is used to design the guidance law, for which a control energy performance index with the weighting function of the range-to-go is minimized. Various forms of guidance and trajectory shaping are possible by selecting a proper gain of the weighting function. To handle the seeker's look angle limits when the missile trajectory is highly curved by controlling the impact angle, the proposed guidance law generates three types of acceleration commands as the guidance phases: the first acceleration command for an initial guidance phase makes an initial seeker's look angle reach the maximum look angle; the second one for a midguidance phase maintains the maximum look angle; the final one for a terminal guidance phase intercepts the target with the desired impact angle. The performance of the proposed guidance law was investigated with nonlinear simulations for various engagement conditions.
机译：提出了同时考虑冲击角和导引头的视场角约束的冲击角控制制导律。使用具有状态变量不等式约束的最优控制理论来设计制导律，在该制导律中，具有随行范围的加权函数的控制能量性能指标被最小化。通过选择适当的加权函数增益，可以进行各种形式的引导和轨迹整形。为了通过控制冲击角来控制导弹轨迹高度弯曲时的搜寻者的视线角限制，建议的制导律生成三种类型的加速命令作为制导阶段：初始制导阶段的第一加速度命令使初始搜寻器的视线角达到最大视角；中导阶段的第二个保持最大视角；最终制导阶段的最后一个以所需的冲击角拦截目标。针对不同的交战条件，通过非线性仿真研究了拟议制导律的性能。

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