Rigid-flexible Coupling Dynamics and Control of the Spacecraft with Axisymmetric Appendages Based on Input Shaping
Year: 2025
Type: conference-paper
Abstract: Modern spacecrafts are often equipped with large axisymmetric flexible appendages. The coupling effect between the vibration of flexible appendages and the motion of the spacecraft’s main platform has a significant impact on the dynamics and control of the spacecraft. The displacement of flexible appendages of spacecraft, including solar panels, antennas, and space manipulators, are mainly characterized by bending deformation. The theory of Euler-Bernoulli beam is the accurate and effective modelling method, which could describe dynamic behaviours of the flexible appendages. The governing equations of the rigid-flexible coupled dynamic equations of the spacecraft were obtained by using the Lagrange’s equations in terms of general quasi-coordinates. The control strategy of the rigid-flexible coupled spacecraft system was designed to realize the attitude control of the rigid platform and suppress the residual vibration of the flexible appendages. The input shaping technique was used to suppress the displacement response of vibration in flexible appendages. Effective algorithms were designed to simulate spacecraft dynamics and control, and the accuracy of the model and control law were verified through numerical simulation. PD controller based on the input shaping technique could significantly reduce the residual vibration of the flexible appendages, which has reference significance for the overall design and controller design of the complex spacecraft system.
Authors: Simeng Huang, Yulong Yan, Baozeng Yue, Tao Ke, Feng Yuan
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: diamond
OpenAlex ID: W4415617410