极低频超大型航天器姿态机动与物理试验验证

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针对具有0.01 Hz极低频主模态的超大型航天器的姿态机动问题,给出利用经典的Bang-Bang轨迹规划方法、滤波轨迹规划方法和传统的相平面控制方法进行姿态机动的方案,构建了极低频超大型航天器姿态机动地面物理试验系统,对不同的姿态机动控制方法进行了试验验证.针对不同的姿态机动轨迹规划方法,采用喷气发动机或控制力矩陀螺作为执行机构,构建了5种超大型航天器姿态机动控制方案,即:姿态跟踪控制+Bang-Bang轨迹规划+喷气发动机,姿态跟踪控制+滤波轨迹规划+喷气发动机,姿态跟踪控制+Bang-Bang轨迹规划+控制力矩陀螺,姿态跟踪控制+滤波轨迹规划+控制力矩陀螺,相平面控制+角速度偏置规划+喷气发动机.利用构建的超大型物理试验系统对上述5种方案进行了试验比较,试验结果表明:机动轨迹对挠性变形的影响超过执行机构的影响,姿态跟踪控制+滤波轨迹规划+控制力矩陀螺方案最优,其变形量相对相平面控制方案能减少约81.8%.
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