Research On Guidance And Control Strategy Of Close-Range Relative Motion Against Space Tumbling Target

The development of space activities has led to a continuous increase in the number of space debris,and the complex tumbling state of space debris has brought greater challenges to on-orbit service technology.The close-range relative motion of chaser is the basis for tracking and capturing space tumbling target.In this paper,the guidance and control strategy during the fly-around and approaching phase between chaser and target are studied.The close-range relative motion model between chaser and target is constructed.Based on the classical differential geometry principle,the three-dimensional relative motion equation is derived,which is decomposed into the motion in the instantaneous plane and the rotation of this plane.The coupling term of the traditional motion equation is eliminated.A finite time convergent guidance control strategy for approaching and flyaround phase is proposed.In approaching phase,a finite time convergent sliding model control is used to control the relative distance along the line of sight,while a true proportional navigation method is used to control the line-of-sight rate perpendicular to the line of sight.In fly-around phase,a finite time convergent sliding model control is used in both directions to realize forced fly around through changing the terminal constraints.The synchronous fly-around and approaching strategy considering the attitude motion of tumbling target is studied.The analytical solution of the tumbling target attitude motion without external torque is derived.The control strategy is designed for the target with regular precession and Euler-Poinsot motion in typical scenarios in order to realize the synchronous fly around.By changing the terminal constraint conditions,the synchronous approximation guidance control strategy is further discussed.A relative attitude control strategy based on error quaternion is explored.The error quaternion attitude dynamics equation of the chaser and target is established.Based on the sliding model variable structure control theory,the attitude control methods of the adaptive sliding model control and the control based on the exponential approach law are compared.Finally,a six degree simulation is performed in the synchronous fly-around and approximation phase to verify the feasibility of the control strategy.This paper studies the guidance and control strategy of close-range relative motion against space tumbling target based on the differential geometry principle.The research work is a useful exploration for the reconnaissance and capture of the tumbling target,and it can be used as reference for close-range position and attitude tracking control of the space tumbling target.