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首页> 外文期刊>Aerospace and Electronic Systems, IEEE Transactions on >Polynomial Guidance Laws Considering Terminal Impact Angle and Acceleration Constraints
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Polynomial Guidance Laws Considering Terminal Impact Angle and Acceleration Constraints

机译：考虑终端冲击角和加速度约束的多项式制导律

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摘要

The work presented here investigates proposed impact angle control guidance laws with terminal acceleration constraints for a stationary or slowly moving target. These laws, called time-to-go polynomial guidance (TPG), assume the guidance command as a polynomial function of time-to-go and determine the coefficients of the guidance command to satisfy the specified terminal constraints. The closed-form trajectory solutions of the guidance command and the target look angle for lag-free systems are derived and their characteristics are investigated. Based on the results we propose a systematic method to find the guidance gains that satisfy practical limits, such as the actuator's command limit and the seeker's field-of-view (FOV) limit. A time-to-go estimation method is also discussed for implementing TPG. Nonlinear and adjoint simulations are performed to investigate the performance of TPG.
机译：本文介绍的工作研究了针对固定或缓慢移动目标的具有最终加速度约束的拟议的冲击角控制制导律。这些定律称为通行时间多项式制导（TPG），将通行命令视为通行时间的多项式函数，并确定通行命令的系数以满足指定的终端约束。推导了无滞后系统的制导指令和目标视角的闭式轨迹解，并研究了它们的特性。根据结果​​，我们提出了一种系统的方法来找到满足实际限制的制导增益，例如执行器的命令限制和导引头的视场（FOV）限制。还讨论了实现TPG的时间估计方法。进行非线性和伴随模拟以研究TPG的性能。

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