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- Type of Document: M.Sc. Thesis
- Language: Farsi
- Document No: 46643 (45)
- University: Sharif University of Technology
- Department: Aerospace Engineering
- Advisor(s): Asadian, Nima
- Abstract:
- In this thesis a novel non-rotating space tethered configuration is introduced which its relative positions are controlled using electromagnetic forces. The attitude dynamics is controlled by three reaction wheels in the body axes. The nonlinear coupled orbital dynamics of a dumbbell tethered satellite formation flight are derived through a constrained Lagrangian approach. These equations are presented in the leader satellite orbital frame. The advantage of using equations in the Cartesian coordinate system over presenting the equations of satellite formation plane angles is the appearance of gravity gradient and Earth’s magnetic field effects. The tether is assumed to be mass-less and straight, and the J2 perturbation is included to the analysis. The forces and the moments of the electromagnetic coils are modeled based on the far-filed model of the magnetic dipoles. A guidance scheme for generating the desired positions as a function of time in Cartesian system is presented. The satellite tethered formation with variable length is controlled utilizing a linear controller. This approach is applied to different scenarios and the results show that the linear controller can control the nonlinear system. Furthermore, the performance of proposed guidance scheme and linear controller is evaluated in compared with optimal control method results
- Keywords:
- Linear Control ; Optimal Control ; Formation Flight ; Magnetic Dipole ; Electromagnetic Formation Flight ; Space Tether
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