Dynamic modeling and control of rigid-flexible-thermo-electrically coupled piezoelectric integrated smart spacecraft

• Published in: Applied mathematical modelling Vol. 140; p. 115896
• Main Authors: Zhang, Shun-Qi, Lai, Wang-Jie, Huang, Chang-Yang, Cai, Chen-Sheng, Lin, Cheng-Hui, Zhu, Qing-Hua
• Format: Journal Article
• Language: English
• Published: Elsevier Inc 01.04.2025
• Subjects: Assumed mode method; Piezoelectric structures; Rigid-flexible-thermo-electrical coupling; Spacecraft modeling; Vibration control; Piezoelectric structures; Vibration control; Spacecraft modeling; Rigid-flexible-thermo-electrical coupling; Assumed mode method
• ISSN: 0307-904X
• DOI: 10.1016/j.apm.2024.115896

With the significant growth in the structure dimensions of flexible components, vibrations become critical to spacecraft during maneuvers control. Introducing piezoelectric materials as sensors or actuators can effectively suppress vibrations. However, smart spacecraft coupled with multi-field results in big challenge in modeling and control simulations. The paper develops a two-dimensional rigid-flexible-thermo-electrically coupled dynamic model using the Lagrange's principle for simulation and control of smart spacecraft. Based on the piezoelectric constitutive equation, a piezoelectric composite solar wing dynamic model is obtained. Furthermore, the discrete dynamic model is established with assumed mode method. According to the finite difference method, the variation of temperature and the responses of smart spacecraft under the solar radiation is obtained. As a validation, three numerical examples of rigid-flexible coupling models are provided in the frequency domain, and one is selected to demonstrate the feasibility and accuracy of the proposed model in time domain analysis. Subsequently, the temperature variations of flexible components under solar radiation are verified and analyzed, and the resulting flexible vibrations are calculated. Finally, a PID control algorithm is employed to study the active vibration suppression of flexible components, thereby achieving high-precision attitude control of the spacecraft in the space radiation environment. •Dynamic model of solar arrays with surface-applied piezoelectric structures subject.•The frequency and dynamic response of spacecraft model is verified by Comsol software.•Effect of thermal moment on solar array vibration under varying angles of incidence.•Vibration controller is designed and the effect performance of controller is analyzed.