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首页> 外文期刊>Journal of guidance, control, and dynamics >Constrained Numerical Predictor-Corrector Guidance for Mars Precision Landing
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Constrained Numerical Predictor-Corrector Guidance for Mars Precision Landing

机译：火星精确着陆的受约束的数值预测器-校正制导

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摘要

In this Note, a novel constrained numerical predictor-corrector (CNPC) algorithm has been developed for the design of Mars entry guidance with an inequality constraint on the aerodynamic acceleration. The novel CNPC algorithm has roots in the so-called exact-penalty method. The development of the algorithm is based on one single parameter iteration and is modeled as a constrained-minimization problem. In the current work, the inequality constraint on the aerodynamic acceleration is equivalently converted into an equality constraint. By the exact-penalty method, the original CNPC guidance problem is transformed into an equivalently unconstrained numerical predictor-corrector (UNPC) guidance problem, in which the exact-penalty term is considered to be the €, norm of the equality-constraint violation. A smoothing technology is applied to the approximation of the nonsmooth function in the exact-penalty term, such that several gradient-based iteration methods are applicable to the search for the single guidance parameter. Numerical results demonstrate the strong robustness of the CNPC algorithm to uncertainties in the flight dynamics. It is shown that all the cases in the 1000-run Monte Carlo simulation strictly satisfy the constraint. With this novel CNPC algorithm, the aerodynamic-acceleration constraint can be satisfied strictly without adversely decreasing the targeting accuracy. Compared with the UNPC algorithm, the novel CNPC algorithm does not increase the complexity of the algorithm.
机译：在本说明中，已经开发了一种新颖的约束数值预测器-校正器（CNPC）算法，以设计对空气动力学加速度具有不等式约束的火星进入制导系统。新颖的CNPC算法起源于所谓的精确罚分法。该算法的开发基于一个单参数迭代，并被建模为约束最小化问题。在当前的工作中，将对空气动力学加速度的不等式约束等效地转换为等式约束。通过精确罚分方法，将原始的CNPC指导问题转换为等效无约束的数值预测器-校正器（UNPC）指导问题，其中，精确罚分项被视为等同约束违规的€范数。在精确惩罚项中将平滑技术应用于非平滑函数的逼近，以便几种基于梯度的迭代方法可用于搜索单个指导参数。数值结果表明，CNPC算法对飞行动力学不确定性具有很强的鲁棒性。结果表明，在1000次运行的蒙特卡洛模拟中，所有情况都严格满足约束条件。使用这种新颖的CNPC算法，可以严格满足空气动力学加速约束，而不会不利地降低瞄准精度。与UNPC算法相比，新颖的CNPC算法不会增加算法的复杂度。

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  • 来源
    《Journal of guidance, control, and dynamics》 |2017年第1期|177-185|共9页
  • 作者

    Yiyu Zheng; Hutao Cui; Yuanhang Ai;

  • 作者单位

    Harbin Institute of Technology, 150080 Harbin,Heilongjiang, People's Republic of China;

    Harbin Institute of Technology, 150080 Harbin,Heilongjiang, People's Republic of China;

    Harbin Institute of Technology, 150080 Harbin,Heilongjiang, People's Republic of China;

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