航天器挠性板系统的模态分析和模型降阶

大型航天器上的太阳帆板这种悬臂外伸薄板结构挠性附件,由于存在模型不确定性及外部扰动条件下所引起的振动控制问题,为了易于低维控制器的设计以及降低控制“溢出”,需要建立板系统的低阶模型。对挠性悬臂板系统动力学模型分析采用模态展开技术,并利用模态截断方法、基于平衡实现的截断方法和平衡奇异摄动截断方法对挠性悬臂板进行了模型降阶,得到板系统的低阶模型,然后分析了降阶模型幅值误差。这为基于智能结构控制悬臂板控制器的设计提供了参考,数字仿真结果验证了方法的可行性。

Modal Analysis and Model Reduction for Flexible Cantilever Plate System of Spacecraft

Some flexible appendages of spacecraft are cantilever plate structures,active vibration control method is applied to suppress the vibration due to the uncertainties and environmental disturbances.A low-order model of the plate system must be obtained to design the controller and reduce the control "spillover".Modal expansion is adopted to analyze the dynamics model,and the modal truncation method,balanced truncation method and singular perturbation approximation method are used for model reduction,then we can get the low-order model,and the model error by truncation is obtained to provide the reference for the controller design,and the simulation results demonstrate the effectiveness of the method.