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首页> 外文会议>4th ESA International Conference on Spacecraft Guidance, Navigation and Control Systems, 4th, Oct 18-21, 1999, ESTEC, Noordwijk, The Netherlands >Multiobjective LMI based Attitude Control Design for a Telecommunication Satellite
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Multiobjective LMI based Attitude Control Design for a Telecommunication Satellite

机译：基于多目标LMI的电信卫星姿态控制设计

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摘要

The applicability of modern control techniques based on the Linear Matrix Inequality (hereafter denoted LMI) framework is investigated in this paper. Once the problem has been formulated in terms of LMI, it can be solved efficiently using interior point, polynomial-time algorithms. The main interest of these methods lies in the fact they allow to turn the multi-objective control problem into a convex optimisation one, in which the criterion is composed of various different specifications. The objectives addressed in this paper include stability, time constraints expressed in terms of peak output amplitude and command input peak bound, as well as frequency constraints such as H_2 and/or H_∞ performance and gain and phase margins. The main application of the control methods considered in this study is the attitude control of a telecommunication satellite from the Spacebus family, during a station keeping manoeuvre (SKM). In this work, various LMI optimisation criteria are compared in terms of performance and robustness of the derived control laws : it is especially shown that H_2 and/or H_∞ frequency constraints are necessary to obtain satisfactory results.
机译：本文研究了基于线性矩阵不等式（以下简称LMI）框架的现代控制技术的适用性。一旦根据LMI提出了问题，就可以使用内部点多项式时间算法有效地解决问题。这些方法的主要目的在于，它们可以将多目标控制问题转化为凸优化问题，其中准则由各种不同的规格组成。本文解决的目标包括稳定性，以峰值输出幅度和命令输入峰值范围表示的时间限制，以及频率限制，例如H_2和/或H_∞性能以及增益和相位裕度。本研究中考虑的控制方法的主要应用是在保持站机动（SKM）期间对来自太空客车家族的电信卫星的姿态控制。在这项工作中，在性能和导出控制律的鲁棒性方面对各种LMI优化标准进行了比较：特别表明，H_2和/或H_∞频率约束对于获得令人满意的结果是必要的。

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