Trajectory optimization for satellite fast attitude maneuver based on collocation method

Aircraft trajectory optimization is the key to overall aircraft design, it plays an important role in modern aircraft design. In this paper, agile satellite attitude maneuver problem, is studied based on Time-Optimal and direct collocation method to get the agile satellite maneuvering trajectory optimization and simulation verification. The results is bang-bang mode, and the size of the deviation affect the accuracy of the result, the control torque change times will depends on the manuvering.