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首页> 外文期刊>Journal of guidance, control, and dynamics >Adaptive impact time control via look-angle shaping under varying velocity
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Adaptive impact time control via look-angle shaping under varying velocity

机译：在变化的速度下通过视角整形进行自适应冲击时间控制

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摘要

This work presents a feasible framework for impact time control under varying velocity. The main idea (i.e., shaping of the look angle in polynomial form) leads to a mathematically tractable formulation in the linear domain. After solving the linearized problem, whereby a suboptimal control law is also derived as a byproduct, the solution is extended to the nonlinear domain by means of an adaptive guidance scheme based on the idea of gain update. The adaptive scheme, which is also useful in providing robustness against unmodeled disturbances such as autopilot lag, is further extended to cope with the varying velocity profile of the missile. This is enabled by considering the future mean velocity, which is iteratively predicted based on the analytical solutions borrowed from the linearized system, in the guidance algorithm. The performance of this predictive-adaptive guidance scheme, the implementation of which is straightforward, is shown with realistic engagement simulations that include drag, gravity, and autopilot lag to be comparable to numerical optimal solutions. The results of additional simulations involving drag uncertainty further demonstrate the robustness properties of the method.
机译：这项工作提出了一个可行的框架，用于在变化的速度下控制冲击时间。主要思想（即，以多项式形式对视角进行整形）导致在线性域中数学上易于处理的公式。在解决了线性化问题后，还得出了次优控制律作为副产品的情况，该解决方案通过基于增益更新思想的自适应制导方案，扩展到非线性域。自适应方案，也可用于提供针对非模型性干扰（如自动驾驶仪滞后）的鲁棒性，进一步扩展以应对导弹的速度分布变化。这可以通过考虑未来平均速度来实现，该平均速度是在导航算法中基于从线性化系统借用的解析解进行迭代预测的。该预测-自适应制导方案的性能很容易实现，并通过实际的交战模拟（包括阻力，重力和自动驾驶滞后）与数值最优解进行了比较，从而表明了该方案的性能。涉及阻力不确定性的其他模拟结果进一步证明了该方法的鲁棒性。

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  • 来源
    《Journal of guidance, control, and dynamics》 |2017年第12期|3247-3255|共9页
  • 作者

    Tekin Raziye; Erer Koray S.; Holzapfel Florian;

  • 作者单位

    Aselsan Inc., MGEO Navigation and Guidance Systems Design Department, Ankara, Turkey;

    Roketsan Missiles Inc., TMS Guidance Systems Design Department, Ankara, Turkey;

    Technische Universität München, Institute of Flight System Dynamics, Munich, Germany;

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