In this paper,for Multi-Spacecraft System(MSS)with a directed communication topology link and a static virtual leader,a controller is proposed to realize attitude consensus and attitude stabilization with stochastic l...In this paper,for Multi-Spacecraft System(MSS)with a directed communication topology link and a static virtual leader,a controller is proposed to realize attitude consensus and attitude stabilization with stochastic links failure and actuator saturation.First,an MSS attitude error model suitable for a directed topology link and with a static virtual leader based on SO(3)is derived,which considers that the attitude error on SO(3)cannot be defined based on algebraic subtraction.Then,we design a controller to realize the MSS on SO(3)with attitude consensus and attitude stabilization under stochastic links failure and actuator saturation.Finally,the simulation results of a multi-spacecraft system with stochastic links failure and a static virtual leader spacecraft are demonstrated to illustrate the efficiency of the attitude controller.展开更多
For the low-earth-orbit(LEO) long-duration multi-spacecraft rendezvous mission,a mixed integer nonlinear programming(MINLP) model is built with consideration of the J2 perturbation and the time window constraints base...For the low-earth-orbit(LEO) long-duration multi-spacecraft rendezvous mission,a mixed integer nonlinear programming(MINLP) model is built with consideration of the J2 perturbation and the time window constraints based on lighting condition.A two-level hybrid optimization approach is proposed.The up-level problem uses the visiting sequence,the orbital transfer duration and the service time after each rendezvous as design variables,and employs the mix-coded genetic algorithm to search the optimal solution;the low-level problem uses the maneuver time and impulses in each rendezvous as design vari-ables,and employs the downhill simplex method to search the optimal solution.To improve the solving efficiency of the low-level problem,a linear dynamic model with J2 perturbation is derived,and the approximate strategy of the low-level prob-lem is then proposed.The proposed method has been applied to several numerical problems.The results lead to three major conclusions:(1) The MINLP model for LEO long-duration multi-spacecraft rendezvous mission is effective,and the proposed hybrid optimization strategy can obtain good solutions that satisfy time window constraints;(2) The derived linear dynamic equations are good first-order approximation to the long-duration rendezvous trajectory under J2 perturbation;(3) Under J2 perturbation,the long-duration rendezvous problem has multiple local minimums either in the duration of multiple orbits or in a single orbit,and it agrees with the problem's characteristic to use the mix-coded genetic algorithm.展开更多
基金supported in part by the National Natural Science Foundation of China(Nos.U20B2054,U20B2056 and 62103275)the Natural Science Foundation of Shanghai,China(No.23ZR1432400)。
文摘In this paper,for Multi-Spacecraft System(MSS)with a directed communication topology link and a static virtual leader,a controller is proposed to realize attitude consensus and attitude stabilization with stochastic links failure and actuator saturation.First,an MSS attitude error model suitable for a directed topology link and with a static virtual leader based on SO(3)is derived,which considers that the attitude error on SO(3)cannot be defined based on algebraic subtraction.Then,we design a controller to realize the MSS on SO(3)with attitude consensus and attitude stabilization under stochastic links failure and actuator saturation.Finally,the simulation results of a multi-spacecraft system with stochastic links failure and a static virtual leader spacecraft are demonstrated to illustrate the efficiency of the attitude controller.
基金supported by the National Natural Science Foundation of China (Grant No. 10902121)the Foundation of State Key Laboratory of Astronautic Dynamics (Grant No. 2011ADL-DW0203)the Science Project of National University and Defense Technology (Grant No. JC09-01-01)
文摘For the low-earth-orbit(LEO) long-duration multi-spacecraft rendezvous mission,a mixed integer nonlinear programming(MINLP) model is built with consideration of the J2 perturbation and the time window constraints based on lighting condition.A two-level hybrid optimization approach is proposed.The up-level problem uses the visiting sequence,the orbital transfer duration and the service time after each rendezvous as design variables,and employs the mix-coded genetic algorithm to search the optimal solution;the low-level problem uses the maneuver time and impulses in each rendezvous as design vari-ables,and employs the downhill simplex method to search the optimal solution.To improve the solving efficiency of the low-level problem,a linear dynamic model with J2 perturbation is derived,and the approximate strategy of the low-level prob-lem is then proposed.The proposed method has been applied to several numerical problems.The results lead to three major conclusions:(1) The MINLP model for LEO long-duration multi-spacecraft rendezvous mission is effective,and the proposed hybrid optimization strategy can obtain good solutions that satisfy time window constraints;(2) The derived linear dynamic equations are good first-order approximation to the long-duration rendezvous trajectory under J2 perturbation;(3) Under J2 perturbation,the long-duration rendezvous problem has multiple local minimums either in the duration of multiple orbits or in a single orbit,and it agrees with the problem's characteristic to use the mix-coded genetic algorithm.
