Fuel-optimal orbit-attitude motion planning for spacecraft close-range rendezvous and synchronization requires solving a two-point boundary value problem with continuous input actuation.This paper presents a geometric...Fuel-optimal orbit-attitude motion planning for spacecraft close-range rendezvous and synchronization requires solving a two-point boundary value problem with continuous input actuation.This paper presents a geometric approach to the problem,which not only encompasses both translational and rotational dynamics,but also incorporates a novel adaptive multiplier method to enforce actuation constraints during the optimization process.Further,in the case of underactuation,such as small single-thruster spacecraft,the paper proposes a guided technique for the geometric approach to direct the attitude using the optimal translational trajectory.The geometric approach is verified through several case studies,where it is compared against a direct method optimization and a concurrent controller,to demonstrate the computational efficiency as well as resulting optimal trajectories of the approach.展开更多
文摘Fuel-optimal orbit-attitude motion planning for spacecraft close-range rendezvous and synchronization requires solving a two-point boundary value problem with continuous input actuation.This paper presents a geometric approach to the problem,which not only encompasses both translational and rotational dynamics,but also incorporates a novel adaptive multiplier method to enforce actuation constraints during the optimization process.Further,in the case of underactuation,such as small single-thruster spacecraft,the paper proposes a guided technique for the geometric approach to direct the attitude using the optimal translational trajectory.The geometric approach is verified through several case studies,where it is compared against a direct method optimization and a concurrent controller,to demonstrate the computational efficiency as well as resulting optimal trajectories of the approach.
