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Boundary Control of Vibration in Satellite Flexible Solar Panels

Kaviani Rad, Hossein | 2017

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 49991 (08)
  4. University: Sharif University of Technology
  5. Department: Mechanical Engineering
  6. Advisor(s): Alasty, Aria; Salarieh, Hassan; Vatankhah, Ramin
  7. Abstract:
  8. Many spacecrafts and satellites have long flexible components, the most common ones are the satellites with flexible solar panels, which are used to provide the satellite energy. The governing equations of the satellite rigid motion along with the solar panels vibrations are the combination of the coupled partial and ordinary differential equations. Various reasons, such as the satellite maneuvers and the external disturbances, cause the vibration of panels. Due to the dependence between the governing equations of the satellite rigid motion and the flexible components vibrations, these vibrations affect the satellite rigid dynamics and the control aims; therefore, in addition to the satellite angle and location control, the vibrations of the panels should be controlled, in such a way that at the end of the satellite maneuver, in addition, to track the desired angle or position, the vibrations are suppressed. In this research, primly, the partial and ordinary differential equations governing the rotation, translation, and vibration of the flexible satellite, in a circular orbit around the Earth, are obtained by considering the orbital motion and orbital disturbances such as the gravity gradient torque. Then, the partial differential equations without reducing to the ordinary differential equations, are controlled by the boundary control; the proof of the asymptotic and exponential stability of the system is based on the Lyapunov stability. The advantage of this control method is to avoid the spillover instability and the in-domain measurement and actuation. The sensors are used only at the base of the panels; furthermore, only the common satellite actuators such as the thruster and the reaction wheel are used. Also, the boundary control and the disturbance observer are designed for the system by considering the disturbance torque and distributed force
  9. Keywords:
  10. Flexible Satellites ; Boundary Control ; Partial Differential Equations ; Asymptotic Stabilization ; Exponential Stability ; Vibration Control ; Hybrid System

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