This paper presents a robust orbit-attitude control method for spacecraft body-fixed hovering over a captured asteroid in the earth-moon system.First,relative orbit-attitude motion dynamics model of spacecraft with re...This paper presents a robust orbit-attitude control method for spacecraft body-fixed hovering over a captured asteroid in the earth-moon system.First,relative orbit-attitude motion dynamics model of spacecraft with respect to an asteroid is derived in the context of circular restricted three-body problem.As opposed to previous works focusing on point-mass translational models,this paper proposes a new feature point-based model which is established in a local frame originated in a selected spot attached to the asteroid surface.In such a case,the kinematic coupling effect is explicitly included,and the desired relative motion trajectories are thus to be time-invariant.Next,an adaptive sliding mode controller is devised for spacecraft robust hovering as well as sensor pointing in the presence of external disturbances and parameter uncertainties.Finally,a simulation scenario of spacecraft hovering over an asteroid which is assumed to be captured in a stable lunar distant retrograde orbit is illustrated.Results demonstrate that both orbital and attitude relative motion track the reference trajectories well under the proposed control law.展开更多
基金supported by the SAST-SJTU Joint Research Centre of Advanced Aerospace Technology,China(Grant No:USCAST2019-10).
文摘This paper presents a robust orbit-attitude control method for spacecraft body-fixed hovering over a captured asteroid in the earth-moon system.First,relative orbit-attitude motion dynamics model of spacecraft with respect to an asteroid is derived in the context of circular restricted three-body problem.As opposed to previous works focusing on point-mass translational models,this paper proposes a new feature point-based model which is established in a local frame originated in a selected spot attached to the asteroid surface.In such a case,the kinematic coupling effect is explicitly included,and the desired relative motion trajectories are thus to be time-invariant.Next,an adaptive sliding mode controller is devised for spacecraft robust hovering as well as sensor pointing in the presence of external disturbances and parameter uncertainties.Finally,a simulation scenario of spacecraft hovering over an asteroid which is assumed to be captured in a stable lunar distant retrograde orbit is illustrated.Results demonstrate that both orbital and attitude relative motion track the reference trajectories well under the proposed control law.
