一种空间站太阳翼非线性振动主动控制方法和系统
By establishing a full-modal nonlinear mathematical model and a non-singular fast terminal sliding mode active vibration controller that couples the space station's solar panels and attitude control, the problem that linear models in the existing technology cannot effectively suppress the nonlinear vibration of the space station is solved, thus improving control accuracy and performance.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHANGHAI AEROSPACE SYST ENG INST
- Filing Date
- 2023-03-01
- Publication Date
- 2026-07-17
AI Technical Summary
Existing space station vibration control methods are based on linear finite-dimensional models, which fail to effectively suppress nonlinear vibrations, resulting in poor control performance. Furthermore, neglecting the influence of higher-order modes leads to control overflow problems.
A full-modal nonlinear mathematical model of the coupling between the space station's solar array and attitude control is established. A piezoelectric ceramic actuator is used as the actuator to construct a non-singular fast terminal sliding mode active vibration controller. The nonlinear vibration characteristics of the solar array are considered and the model is simplified to solve the control overflow problem.
It achieved more accurate vibration suppression, improved the attitude control accuracy of the space station and the active vibration control performance of the flexible structure, and provided a basis and reference for control under different parameters and structural characteristics.
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Figure CN116414032B_ABST