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Multivariable control of flexible spacecraft.

机译：挠性航天器的多变量控制。

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This thesis addresses H-infinity mixed sensitivity and LQR (Linear Quadratric Regulator) control system design for a large flexible spacecraft. The spacecraft consists of a rigid central body with two flexible roll-out solar arrays. In this paper, we look at how changes in spacecraft parameters such as mass, width and length of the solar arrays influence the feasibility of obtaining an acceptable control design. In the following case studies. H-infinity mixed sensitivity and LQR controllers are designed and an analysis is presented.; For the nominal case, a control system is created for the spacecraft given its nominal weight along with its nominal length and width. However, the results show that for the nominal case, arriving at an acceptable control design that attenuates worst-case disturbance torques is not achievable.; Then, in Case 1, an analysis is presented where the spacecraft's mass is increased. As a consequence, the arrays become stiffer. This extra stiffness allows for the design of an acceptable control system capable of attenuating the given disturbances.; In Case 2, the width of the array is increased and its length decreased. The final mass for Case 2 is very close to the nominal case. Similar to Case 1, an acceptable control design is found. However, the torque used for this case is lower than in Case 1.; The final results for both cases show that in Case 2, driving the initial states to zero uses less torque than in Case 1. Also, since adding extra weight to the spacecraft is undesirable, Case 2 seems to be the most appropriate solution to the control problem.
机译：本文研究了大型柔性航天器的H无限混合灵敏度和LQR（线性二次调节器）控制系统设计。该航天器由一个刚性的中央主体和两个柔性的可展开太阳能电池阵列组成。在本文中，我们研究了航天器参数（例如太阳能电池阵列的质量，宽度和长度）的变化如何影响获得可接受的控制设计的可行性。在以下案例研究中。设计了H无限混合灵敏度和LQR控制器，并进行了分析。对于名义情况，给航天器创建一个控制系统，给定其名义重量以及名义长度和宽度。但是，结果表明，在正常情况下，无法获得能够减弱最坏情况下的干扰转矩的可接受的控制设计。然后，在案例1中，分析了航天器质量增加的情况。结果，阵列变得更硬。这种额外的刚度允许设计一种能够衰减给定干扰的可接受的控制系统。在情况2中，阵列的宽度增加而长度减小。情况2的最终质量非常接近标称情况。与情况1相似，找到了可接受的控制设计。但是，这种情况下使用的扭矩低于情况1。两种情况的最终结果表明，在情况2中，将初始状态驱动为零比在情况1中使用更少的扭矩。而且，由于不希望增加航天器的重量，因此情况2似乎是控制的最合适解决方案问题。

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