Research On Containment Control Method For Relative Position Of Super Large-scale Chip Satellite Cluster

In recent years,with the development of large-scale integrated circuit and micro electro-mechanical technology,the USA and Europe have proposed and began to develop highly integrated,miniaturized chip satellites.Constrained by mass,volume and power,the chip satellites are simple in function and usually need to work together in a large-scale group.It is not necessary and impossible to perform accurate formation,and only needs to be kept within a certain range,that is,exist situations,where have multiple pilots.Therefore,this thesis is based on the group of large-scale chip satellites with multi-pilotfollow structure,and targets the information sharing limitation,such as the limit of sensor field and communication link.In-depth studied relative position containment control of very large-scale chip satellite groups using tools like algebraic graph theory.The results of the paper are as follows:Aiming at the group of large-scale chip satellites under the condition of undirected fixed topology,an exponential convergence relative position containment control algorithm is proposed by using algebraic graph theory.The convergence and maximum convergence speed are given to control gain coefficient and communication topology.This enables the follower to converge to the convex hull surrounded by the multiple pilots at an exponential speed and then remain in the convex hull to realize the orbital containment control of the large-scale chip satellite.Combined with the large-scale chip satellite group mission background,the orbital containment control algorithm for exponential convergence is verified by mathematical simulation,and the influence of control gain coefficient selection and topology design of system information on systematisms and convergence speed are analyzed.Aiming at large-scale chip satellites tasks with convergence time and maneuvering speed requirements,under the undirected fixed topology and the joint connected topology,the finite-time convergence orbital containment control algorithm of the chip satellite group is designed based on the homogeneous theory,so that the followers can enter the fixed convex hull enclosed by the pilot within a limited time.The numerical simulation in the chip satellite group mission background is used to verify the effectiveness of the proposed algorithm in the undirected fixed topology and the joint connected topology.Considering the influence of external disturbance on satellite orbital motion,a nonsingular terminal sliding mode controller and a fast terminal sliding mode controller are designed for large-scale chip satellite group under the directed strong connected topology,so that the followers can enter the fixed convex hull enclosed by the pilot within a limited time under external disturbance.The numerical simulation in the chip satellite group mission background is used to verify the effectiveness of the proposed algorithm and the robustness to external disturbance.