An integral sliding mode guidance law(ISMGL)combined with the advantages of the integral sliding mode control(SMC)method is designed to address maneuvering target interception problems with impact angle constraints.Th...An integral sliding mode guidance law(ISMGL)combined with the advantages of the integral sliding mode control(SMC)method is designed to address maneuvering target interception problems with impact angle constraints.The relative motion equation of the missile and the target considering the impact angle constraint is established in the longitudinal plane,and an integral sliding mode surface is constructed.The proposed guidance law resolves the existence of a steady-state error problem in the traditional SMC.Such a guidance law ensures that the missile hits the target with an ideal impact angle in finite time and the missile is kept highly robust throughout the interception process.By adopting the dynamic surface control method,the ISMGL is designed considering the impact angle constraints and the autopilot dynamic characteristics.According to the Lyapunov stability theorem,all states of the closed-loop system are finally proven to be uniformly bounded.Simulation results are compared with the general sliding mode guidance law and the trajectory shaping guidance law,and the findings verify the effectiveness and superiority of the ISMGL.展开更多
电-热综合能源系统(integrated electricity and heat system,IEHS)可以有效促进可再生能源消纳。构建区域供热系统精细化模型与合理的可再生能源不确定性出力模型是调度IEHS的两个难点。该文首先提出计及可变流量调节模式的IEHS条件分...电-热综合能源系统(integrated electricity and heat system,IEHS)可以有效促进可再生能源消纳。构建区域供热系统精细化模型与合理的可再生能源不确定性出力模型是调度IEHS的两个难点。该文首先提出计及可变流量调节模式的IEHS条件分布鲁棒优化调度模型,主要有两点改进:通过构建基于修正模糊集的条件分布鲁棒模型建模可再生能源预测误差与其预测出力信息之间的内在依赖性,提升调度结果安全性与最优性;基于流体能量守恒方程与一阶隐式迎风格式建立可变流量调节模式下的IEHS调度模型,以期充分挖掘区域供热系统的灵活性,促进可再生能源消纳。所构建的IEHS调度模型为含有大量非线性约束的条件分布鲁棒模型,难以直接求解。对此,通过对偶理论与条件风险价值近似方法将条件分布鲁棒模型转化为含非线性约束的确定性模型,并提出自适应McCormick算法用以求解非线性约束。通过不同规模案例仿真表明,所提模型能够降低IEHS的调度成本,所提算法在保证可行性的条件下快速求出问题的近似最优解,最优间隙小于千分之一。展开更多
To solve the problem of attitude tracking of a rigid spacecraft with an either known or measurable desired attitude trajectory, three types of time-varying sliding mode controls are introduced under consideration of c...To solve the problem of attitude tracking of a rigid spacecraft with an either known or measurable desired attitude trajectory, three types of time-varying sliding mode controls are introduced under consideration of control input constraints. The sliding surfaces of the three types initially pass arbitrary initial values of the system, and then shift or rotate to reach predetermined ones. This way, the system trajectories are always on the sliding surfaces, and the system work is guaranteed to have robustness against parameter uncertainty and external disturbances all the time. The controller parameters are optimized by means of genetic algorithm to minimize the index consisting of the weighted index of squared error （ISE） of the system and the weighted penalty term of violation of control input constraint. The stability is verified with Lyapunov method. Compared with the conventional sliding mode control, simulation results show the proposed algorithm having better robustness against inertia matrix uncertainty and external disturbance torques.展开更多
基金supported by the Joint Equipment Fund of the Ministry of Education(6141A02022340)
文摘An integral sliding mode guidance law(ISMGL)combined with the advantages of the integral sliding mode control(SMC)method is designed to address maneuvering target interception problems with impact angle constraints.The relative motion equation of the missile and the target considering the impact angle constraint is established in the longitudinal plane,and an integral sliding mode surface is constructed.The proposed guidance law resolves the existence of a steady-state error problem in the traditional SMC.Such a guidance law ensures that the missile hits the target with an ideal impact angle in finite time and the missile is kept highly robust throughout the interception process.By adopting the dynamic surface control method,the ISMGL is designed considering the impact angle constraints and the autopilot dynamic characteristics.According to the Lyapunov stability theorem,all states of the closed-loop system are finally proven to be uniformly bounded.Simulation results are compared with the general sliding mode guidance law and the trajectory shaping guidance law,and the findings verify the effectiveness and superiority of the ISMGL.
文摘电-热综合能源系统(integrated electricity and heat system,IEHS)可以有效促进可再生能源消纳。构建区域供热系统精细化模型与合理的可再生能源不确定性出力模型是调度IEHS的两个难点。该文首先提出计及可变流量调节模式的IEHS条件分布鲁棒优化调度模型,主要有两点改进:通过构建基于修正模糊集的条件分布鲁棒模型建模可再生能源预测误差与其预测出力信息之间的内在依赖性,提升调度结果安全性与最优性;基于流体能量守恒方程与一阶隐式迎风格式建立可变流量调节模式下的IEHS调度模型,以期充分挖掘区域供热系统的灵活性,促进可再生能源消纳。所构建的IEHS调度模型为含有大量非线性约束的条件分布鲁棒模型,难以直接求解。对此,通过对偶理论与条件风险价值近似方法将条件分布鲁棒模型转化为含非线性约束的确定性模型,并提出自适应McCormick算法用以求解非线性约束。通过不同规模案例仿真表明,所提模型能够降低IEHS的调度成本,所提算法在保证可行性的条件下快速求出问题的近似最优解,最优间隙小于千分之一。
文摘To solve the problem of attitude tracking of a rigid spacecraft with an either known or measurable desired attitude trajectory, three types of time-varying sliding mode controls are introduced under consideration of control input constraints. The sliding surfaces of the three types initially pass arbitrary initial values of the system, and then shift or rotate to reach predetermined ones. This way, the system trajectories are always on the sliding surfaces, and the system work is guaranteed to have robustness against parameter uncertainty and external disturbances all the time. The controller parameters are optimized by means of genetic algorithm to minimize the index consisting of the weighted index of squared error （ISE） of the system and the weighted penalty term of violation of control input constraint. The stability is verified with Lyapunov method. Compared with the conventional sliding mode control, simulation results show the proposed algorithm having better robustness against inertia matrix uncertainty and external disturbance torques.
