Time-Optimal Reorientation of a Spacecraft Using an Inverse Dynamics Optimization Method

摘要

This paper proposes a rapid attitude trajectory generationmethod for satellite reorientation, which is suitable forrnboth rest-to-rest and track-to-trackmaneuvers. The problemis first formulated and solved using academic softwarernreadily used for generating optimal guidance trajectories offline. Then, the problem is reformulated using a Bezierrnpolynomial parametrization of the quaternion trajectory, which naturally satisfies the unit quaternion normrnconstraint. The parameters of the quaternion trajectory polynomial and of the speed profile are varied to arrive at arnquasi-optimal solution that is both feasible and exactlymatches the endpoint conditions specified in the problem. Thernreduction in the number of varied parameters due to the predetermined structure of the trajectory leads to a fastrncomputational speed as well as a solution that satisfies the end constraints at each iteration. The paper includesrnnumerical simulation results obtained for several cases.