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Coupled Attitude-orbit Dynamics and Control of Solar Sail by Moving the Center of Mass

Montazeri Hedesh, Hamidreza | 2020

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 53700 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Asadian, Nima
  7. Abstract:
  8. In this thesis, firstly we have developed a coupled dynamic for the orbit and attitude of a solar sail. Secondly, we found an optimal trajectory from the Earth to Mars and tried to control the system on the optimal trajectory by a control mechanis which moves the center of mass of the sail. The solar sail is considered to be rigid and Ideally reflective which means the sail reflects the full extent of the photons it receives. Adjusting the center of mass of the sail is done by changing the position of two sliding masses rode on two rails perpendicular to each other. Moving the center of mass of the sail brings about a change in the attitude of the sail which then causes a deflection in the force acting on the sail. This deflected force then defines the orbit of the sail. In this thesis, we have tried to control the attitude of the sail so that we can keep the solar sail on the designed optimal orbit. The results have shown that the designed controller could keep the satellite in an interplantary orbit between Earth and Mars with an error of 1% in position. Settling time of the designed controller is about several days and the control effort is at an acceptable margin. The innovation of our work lays in controlling a coupled orbit-attitude dynamic by moving the center of mass of the satellite and keeping it on an interplanetary optimal orbit
  9. Keywords:
  10. Optimal Trajectory ; Interplanetary Network ; Attitude Control ; Coupled Dynamics ; Mass Moving Center ; Solar Sail

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