Satellite solar panels are subjected to the dual effects of thermal cycling environments and random disturbances when running in orbit, and their vibration control is a key engineering issue for ensuring the stable operation of spacecraft. This study simplifies joint structures such as satellite solar panels into a combined system of composite laminate matrix and bolted lap joints. On the premise of retaining the key characteristics of thermal-random disturbance coupling, this study conducts dynamic modeling and vibration control research on composite-joint-plates (CJPs). In the aspect of dynamic modeling, a hyperbolic secant attenuation surface spring model is introduced to simulate the non-uniform distribution of bolt contact pressure, with further consideration of thermal stress and the temperature dependency of material parameters. Meanwhile, electromechanical coupling characteristics are introduced based on the direct and inverse piezoelectric effects of piezoelectric materials, thus establishing a thermo-electromechanical coupling dynamic model within the framework of the Hamilton principle. The accuracy of the model in characterizing dynamic characteristics is fully verified by constructing an experimental test system. In the design of control methods, a differential tracking-dynamic frequency-domain decomposition coordinated composite control method (DT-DFD-CCC) is proposed. This method utilizes the Prony algorithm to extract the main frequency components in real-time from random vibration responses, adaptively adjusts the control parameters of positive position feedback (PPF), and combines the compensation capability of velocity feedback control (VFC) to achieve broadband suppression. Both simulation and experimental results demonstrate that the proposed method exhibits strong adaptability and robustness, enabling effective control of the multi-modal vibration of structures under random excitation. Additionally, the frequency veering behavior induced by changes in fiber angles is investigated, revealing that both the modal shapes and main resonance peaks exchange before and after veering. The DT-DFD-CCC method successfully suppresses the multi-modal vibration responses in the veering region under random excitation. Ultimately, this study provides theoretical support and an adaptive control solution for vibration control of composite joint structures under complex working conditions. • A surface spring model with a hyperbolic secant attenuation stiffness distribution is proposed. • The temperature dependence and thermal strain are incorporated into the dynamic model. • A DT-DFD-CCC method with strong adaptive capability is proposed. • The effectiveness of the DT-DFD-CCC method is verified through experimental tests. • The modal coupling vibration law within the veering region is revealed.
Zhang et al. (Sun,) studied this question.