This paper investigates the cooperative tracking control problem of Electromagnetic Formation Spacecraft(EMFS)on elliptical orbit.The actuator saturation and topology switching problems exist in formation cooperative ...This paper investigates the cooperative tracking control problem of Electromagnetic Formation Spacecraft(EMFS)on elliptical orbit.The actuator saturation and topology switching problems exist in formation cooperative tracking control.The proposed novel adaptive consensus protocol addresses this problem by utilizing both synchronous and asynchronous topology switching.Firstly,to enhance the robustness of the system and minimize the impact of time-varying parameters on the control algorithm,the controller gain is determined through solving the Adaptive Riccati Differential Equation(ARDE).Secondly,a three-layer network communication structure with mirror nodes is constructed,in which different control input saturation levels are designed according to the correlation with the leader.Then,the Average Dwell Time(ADT)switching technique is utilized to generate the control switching signal,ensuring that the topology maintains a directed spanning tree when the switching signal condition is satisfied.Finally,simulation results validate the theoretical findings and provide a comparison with other methods,demonstrating the superiority of the proposed approach.展开更多
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
In this paper,we address a cross-layer resilient control issue for a kind of multi-spacecraft system(MSS)under attack.Attackers with bad intentions use the false data injection(FDI)attack to prevent the MSS from reach...In this paper,we address a cross-layer resilient control issue for a kind of multi-spacecraft system(MSS)under attack.Attackers with bad intentions use the false data injection(FDI)attack to prevent the MSS from reaching the goal of consensus.In order to ensure the effectiveness of the control,the embedded defender in MSS preliminarily allocates the defense resources among spacecrafts.Then,the attacker selects its target spacecrafts to mount FDI attack to achieve the maximum damage.In physical layer,a Nash equilibrium(NE)control strategy is proposed for MSS to quantify system performance under the effect of attacks by solving a game problem.In cyber layer,a fuzzy Stackelberg game framework is used to examine the rivalry process between the attacker and defender.The strategies of both attacker and defender are given based on the analysis of physical layer and cyber layer.Finally,a simulation example is used to test the viability of the proposed cross layer fuzzy game algorithm.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 , perturbation and the time window constraint...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 , 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 J~ 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funded by the National Natural Science Foundation of China(No.6200326)。
文摘This paper investigates the cooperative tracking control problem of Electromagnetic Formation Spacecraft(EMFS)on elliptical orbit.The actuator saturation and topology switching problems exist in formation cooperative tracking control.The proposed novel adaptive consensus protocol addresses this problem by utilizing both synchronous and asynchronous topology switching.Firstly,to enhance the robustness of the system and minimize the impact of time-varying parameters on the control algorithm,the controller gain is determined through solving the Adaptive Riccati Differential Equation(ARDE).Secondly,a three-layer network communication structure with mirror nodes is constructed,in which different control input saturation levels are designed according to the correlation with the leader.Then,the Average Dwell Time(ADT)switching technique is utilized to generate the control switching signal,ensuring that the topology maintains a directed spanning tree when the switching signal condition is satisfied.Finally,simulation results validate the theoretical findings and provide a comparison with other methods,demonstrating the superiority of the proposed approach.
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 Natural Science Foundation of China(62073268,62122063,62203360)the Young Star of Science and Technology in Shaanxi Province(2020KJXX-078).
文摘In this paper,we address a cross-layer resilient control issue for a kind of multi-spacecraft system(MSS)under attack.Attackers with bad intentions use the false data injection(FDI)attack to prevent the MSS from reaching the goal of consensus.In order to ensure the effectiveness of the control,the embedded defender in MSS preliminarily allocates the defense resources among spacecrafts.Then,the attacker selects its target spacecrafts to mount FDI attack to achieve the maximum damage.In physical layer,a Nash equilibrium(NE)control strategy is proposed for MSS to quantify system performance under the effect of attacks by solving a game problem.In cyber layer,a fuzzy Stackelberg game framework is used to examine the rivalry process between the attacker and defender.The strategies of both attacker and defender are given based on the analysis of physical layer and cyber layer.Finally,a simulation example is used to test the viability of the proposed cross layer fuzzy game algorithm.
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 , 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 J~ 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.
