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Analysis and Performance Evaluation of the ZEM/ZEV Guidance and its Sliding Robustification for Autonomous Rendezvous in Relative Motion

机译：ZEm / ZEV制导分析与性能评估及其相对运动自主交会的滑动理论

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Devising closed-loop guidance algorithms for autonomous relative motion is an important problem within the field of orbital dynamics. In this paper, we study the guided relative motion of two spacecraft for which one of them is executing an autonomous rendezvous via the ZEM/ZEV feedback guidance and its robustified Optimal Sliding Guidance (OSG) counterpart. Starting from the classical Clohessy-Wiltshire (CW) model, we systematically analyze the ability of the ZEM/ZEV feedback guidance to generate closed loop trajectories that drive the deputy spacecraft to the chief satellite and evaluate its performance in terms of target accuracy and propellant consumption. It is shown that the guidance gains and the time of flight predicted by the theoretical solution generates a class of feedback trajectories that are accurate but suboptimal with respect to the open-loop fuel-optimal solution. Indeed, a parametric study shows that a different set of gains may generate relative guided trajectories that yields fuel consumption closer to the ideal optimal. The guidance algorithms are also demonstrated to be accurate in guiding the relative motion of the deputy toward a chief spacecraft in highly elliptical orbit where the Linearized Equations of Relative Motions (LERM) are employed to compute the Zero-Effort-Miss (ZEM) and Zero-Effort-Velocity (ZEV) necessary to compute the acceleration command as prescribed by the theory.
机译：设计用于自主相对运动的闭环引导算法是轨道动力学领域中的重要问题。在本文中，我们研究了两个航天器的制导相对运动，其中一个正在通过ZEM / ZEV反馈制导及其稳固的最佳滑行制导（OSG）对应物执行自主会合。从经典的Clohessy-Wiltshire（CW）模型开始，我们系统地分析ZEM / ZEV反馈制导的能力，以产生将副航天器驱动到主卫星的闭环轨迹，并根据目标精度和推进剂消耗评估其性能。结果表明，理论解所预测的制导增益和飞行时间会产生一类反馈轨迹，这些反馈轨迹相对于开环燃料最优解是准确的，但次优。实际上，一项参数研究表明，一组不同的增益可能会产生相对的引导轨迹，从而使燃油消耗接近理想的最佳水平。还证明了该引导算法可以准确地将副手的相对运动引向高椭圆轨道上的主要航天器，在这种情况下，采用相对运动的线性化方程（LERM）计算零努力小姐（ZEM）和零计算理论所要求的加速命令所必需的-Effort-Velocity（ZEV）。

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