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首页> 外文会议>Cranfield Conference on Dynamica and Control of Systems and Structures in Space; 2004; Liguria; IT >Taking into account Flexibility in Attitude Control
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Taking into account Flexibility in Attitude Control

机译：考虑到姿态控制的灵活性

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摘要

Large structures in space do deform in a non negligible manner. The effect that deformations have on the dynamic of a spacecraft might be captured by complex non linear mathematical models. In a recent work the authors developed a non coupled set of ordinary differential equations describing the full non linear dynamic of a flexible spacecraft equipped with a system of next generation fly-wheels. These equations are here exploited to test the robustness of a "Velocity Based" steering law to flexible dynamic. As the "Velocity Based" steering law for a VSCMG device is designed under the hypothesis of rigid dynamic, "spill-over" effects are visible. Even though vibrations are suppressed quite rapidly, the "spill-over" introduces a tracking error that has to be accounted for. As a result, a minimum attitude acquisition time is found for a selected satellite configuration, faster manoeuvres are not possible as flexible modes would be excited in such a way as to make the spacecraft lose the required pointing accuracy.
机译：空间中的大型结构确实会以不可忽略的方式变形。变形对航天器动力的影响可以通过复杂的非线性数学模型来捕捉。在最近的工作中，作者开发了一组非耦合的常微分方程，这些方程描述了装备有下一代飞轮系统的挠性航天器的全部非线性动力学特性。在这里利用这些方程式来测试“基于速度”转向定律对灵活动力的鲁棒性。由于VSCMG设备的“基于速度”的转向定律是在刚性动态的假设下设计的，因此可以看到“溢出”效果。即使非常迅速地抑制了振动，“溢出”也会引入跟踪误差，必须加以考虑。结果，找到了针对所选卫星配置的最小姿态获取时间，不可能进行更快的操纵，因为将以使航天器失去所需的指向精度的方式来激发灵活模式。

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