Abstract
This paper studies on the complex dynamics coupling phenomena between orbital motion of space vehicle and elastic vibration of solar panel. For solar panel is a typical large flexible structure and generate continuous vibration inevitably under various loads in space environment, the vibration control is necessary. To provide appropriate dynamic parameters for the design of controller, high accuracy mechanics model of flexible space vehicle must be established. The conventional method did not consider the impact of static deformation on the vibration of solar panel, and hold that solar panel vibrates under the base of zero equilibrium position, which actually not accord with the fact that static equilibrium position is varying along the time under the influence of space vehicle orbital motion. In this paper, a novel method of describing the solar panel deformation is proposed, which think the vibration is a vector superposition of static deformation and dynamic deformation. To illustrate the influence of orbital motion on the dynamic traits of solar panel, a simplified curved beam model of solar panel is adopted to simulate the vibration behavior of solar panel undergoing large overall orbital motion.
Published Version
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