Large Attitude Maneuvers of a Spacecraft with Flexible Solar Panels

This paper faces with the problem maneuver control of a spacecraf solar panels, actuated by thrusters wheels. A functional separatio performed: thrusters are used maneuvers with a feed forward ap reaction wheels are used in closed the maneuver. Thrusters allocatio to increase the resulting torque reduce the fuel consumption for th Since the attitude dynamics is infl vibrations due to the flexibility panels, this effect is taken into attitude dynamics equations are de Lagrangian approach to include of the arrays. An optimal cont implemented in order to consumption while maneuvering Numerical simulations have b evaluate the AOCS performance large attitude maneuvers, and accuracy. Results are presented.