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首页> 外文期刊>International journal of aerospace engineering >Fast Attitude Maneuver of a Flexible Spacecraft with Passive Vibration Control Using Shunted Piezoelectric Transducers
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Fast Attitude Maneuver of a Flexible Spacecraft with Passive Vibration Control Using Shunted Piezoelectric Transducers

机译：具有并联压电传感器被动振动控制的挠性航天器的快速姿态操纵

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This paper is concerned with designing a bang-bang control input to perform a quick rotational maneuver of a rigid spacecraft hub connected with flexible appendages. The control design is based on only the rigid body mode making it very simple to design and at the same time achieve the quickest maneuver possible. The induced vibrations are suppressed using piezoelectric transducers bonded to the appendages and connected to an electric circuit with the objective of converting the vibrational energy to electrical energy and then dissipating it using passive electric elements, such as a resistance and an inductor. The proposed control design method is applied to a spacecraft containing a rigid hub and flexible appendages. The attitude control torque is produced using either the reaction wheels contained inside the rigid hub or jet thrusters mounted outside it. The control design process starts with deriving the nonlinear partial differential equations of motion for the spacecraft using Hamilton's principle which accounts for the electromechanical coupling and the presence of resistive or resistive-inductive circuits. To simplify the analysis, the nonlinear ordinary differential equations of motion are then obtained using the assumed mode method. The effectiveness of the control design method is numerically tested on a spacecraft that is required to perform a quick attitude maneuver and, simultaneously, suppress the induced vibrations. The simulations show a quick and accurate maneuver has been achieved combined with very low levels of vibrations resulting from the reduced coupling between flexible and rigid motions as well as the damping added as a result of the passive shunt circuit. Furthermore, the resistance-inductance shunt circuit is shown to be more effective in damping the vibrations than the resistance shunt circuit.
机译：本文涉及设计爆炸控制输入，以执行与柔性附件连接的刚性航天器轮毂的快速旋转操纵。控制设计仅基于刚体模式，因此设计非常简单，同时实现了最快的机动性。使用压电换能器抑制感应的振动，压电换能器连接到附件并连接到电路，目的是将振动能转换为电能，然后使用无源电子元件（例如电阻和电感器）将其消散。所提出的控制设计方法被应用于包含刚性轮毂和柔性附件的航天器。姿态控制扭矩是通过刚性轮毂内部包含的反作用轮或安装在其外部的喷气推进器产生的。控制设计过程开始于使用汉密尔顿原理推导航天器的非线性偏微分运动方程，该方程解释了机电耦合以及电阻性或电阻性电感电路的存在。为了简化分析，然后使用假定模式方法获得非线性的常微分运动方程。该控制设计方法的有效性在航天器上进行了数值测试，该航天器需要执行快速姿态操纵并同时抑制感应振动。仿真显示，由于柔性运动和刚性运动之间的耦合减少以及被动分流电路增加的阻尼而导致的振动水平非常低，因此实现了快速准确的操纵。此外，示出了电阻-电感分路电路在阻尼振动方面比电阻分路电路更有效。

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