Active vibration control of flexible spacecraft using modified input shaping and adaptive positive position feedback

使用修正输入整形和自适应正位置反馈的柔性航天器主动振动控制

• 批准号: 341905-2007
• 负责人: Shan, Jinjun
• 金额: $ 1.35万
• 依托单位: York University
• 依托单位国家: 加拿大
• 项目类别: Discovery Grants Program - Individual
• 财政年份: 2010
• 资助国家: 加拿大
• 起止时间: 2010-01-01 至 2011-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=458647
• 关键词: Active; vibration; control; flexible; spacecraft

Active vibration control is a crucial issue for modern flexible spacecraft because the flexible dynamics may interact with the attitude/orbit dynamics, which makes high-precision attitude/orbit control more difficult. To address this issue, a strategy that combines modified input shaping technique and adaptive positive position feedback is proposed to control vibration of flexible spacecraft. Modified input shaping will be integrated with spacecraft actuators, momentum wheels and jet thrusters, to suppress several low-order vibration modes, while adaptive positive position feedback will be applied to piezoelectric smart actuators to control the dominant high-order vibration modes. The research work will be conducted as follows. Firstly, the basic principles of modified input shaping will be investigated and an adaptive algorithm will be developed for automatic tuning of parameters of the positive position feedback filters. Secondly, a detailed 3-axis dynamic model for flexible spacecraft will be developed based on flexible multi-body dynamics. The actuator configuration problem will be studied and the optimal configuration will be determined. Thirdly, the hybrid vibration controller that combines modified input shaping and adaptive positive position feedback will be developed. Method will also be developed to minimize the interaction of these two vibration controllers. The stability of the hybrid vibration controller will be proved through stability theory. Different spacecraft on-orbit operation modes will be considered as well. Then, numerical simulation will be conducted using MATLAB/Simulink to validate the theoretical analysis. Finally, hardware experiments will be conducted to verify the effectiveness of the proposed vibration control strategy. By using the proposed strategy, it is expected that the flexible vibration of spacecraft can be suppressed to an allowable level quickly so that high-precision attitude/pointing control can be achieved.

由于挠性航天器的挠性动力学与姿态/轨道动力学之间存在相互影响，使得高精度的姿态/轨道控制变得更加困难，因此振动主动控制是现代挠性航天器的关键问题。针对这一问题，提出了一种结合修正输入成形技术和自适应位置正反馈的挠性航天器振动控制策略。改进的输入整形将与航天器致动器、动量轮和喷气推进器结合起来，以抑制几种低阶振动模式，而自适应正位置反馈将应用于压电智能致动器，以控制占主导地位的高阶振动模式。研究工作将按以下方式进行。首先，研究了修正输入成形的基本原理，并提出了一种自适应算法来自动调整正位置反馈滤波器的参数。其次，基于柔性多体动力学理论，建立了柔性航天器的三轴动力学模型。将研究的执行器配置问题，并确定最佳配置。第三，将修正输入成形与自适应位置正反馈相结合的混合振动控制器。方法也将被开发，以尽量减少这两个振动控制器的相互作用。通过稳定性理论证明了混合振动控制器的稳定性。还将考虑不同的航天器在轨运行模式。然后，利用MATLAB/Simulink进行数值仿真，验证理论分析的正确性。最后，将进行硬件实验，以验证所提出的振动控制策略的有效性。通过使用所提出的策略，可以期望的柔性振动的航天器可以抑制到允许的水平，从而可以实现高精度的姿态/指向控制。