This paper investigates the finite-time attitude tracking problem for rigid spacecraft. Two backstepping finite-time slid- ing mode control laws are proposed to solve this problem in the presence of inertia uncertaint...This paper investigates the finite-time attitude tracking problem for rigid spacecraft. Two backstepping finite-time slid- ing mode control laws are proposed to solve this problem in the presence of inertia uncertainties and external disturbances. The first control scheme is developed by combining sliding mode con- trol with a backstepping technique to achieve fast and accurate tracking responses. To obtain higher tracking precision and relax the requirement of the upper bounds on the uncertainties, a se- cond control law is also designed by combining the second or- der sliding mode control and an adaptive backstepping technique. This control law provides complete compensation of uncertainty and disturbances. Although it assumes that the uncertainty and disturbances are bounded, the proposed control law does not require information about the bounds on the uncertainties and disturbances. Finite-time convergence of attitude tracking errors and the stability of the closed-loop system are ensured by the Lya- punov approach. Numerical simulations on attitude tracking control of spacecraft are provided to demonstrate the performance of the proposed controllers.展开更多
Shock wave/boundary layer interaction(SWBLI)is still one of the unresolved bottlenecks that restrict the development of more advanced flight vehicles.Supersonic forward-facing step(FFS),an extreme case of compression ...Shock wave/boundary layer interaction(SWBLI)is still one of the unresolved bottlenecks that restrict the development of more advanced flight vehicles.Supersonic forward-facing step(FFS),an extreme case of compression ramp,often occurs severe SWBLIs with a large separation bubble.In this paper,experimental investigations on vortical structures and density fluctuations characteristics of supersonic FFS controlled by self-sustaining dual synthetic jets(SDSJ)are carried out in a Mach number 2.95 wind tunnel.High spatial–temporal resolution flowfield images of FFS without/with active flow control are captured by adopting nano-particle-based planar laser scattering technique.The control effects of the distance between the actuator and the step are mainly compared.The paper finds that the SDSJ can effectively change the feature of flowfield,eliminate the separation shock and the reattachment shock,compel the original shock induced by the step leading edge to distort and reduce its intensity finally.Density fluctuations analysis demonstrates that the whole flows seem to move upstream with the increase of distance(dS-J).Discrete Fourier transformation spectrums results reveal that the fluctuations are mainly located in the low-frequency region at first.High-frequency components and frequency bandwidth increase slightly after the SDSJ are applied.展开更多
变流器有限控制集模型预测控制(finite control setmodel predictive control,FCS-MPC)算法是一种变流器优化控制算法。该算法具有动态响应快、处理系统约束灵活且无需PWM调制器和相关参数设计等优点,但仅可确保所选开关函数组合在一个...变流器有限控制集模型预测控制(finite control setmodel predictive control,FCS-MPC)算法是一种变流器优化控制算法。该算法具有动态响应快、处理系统约束灵活且无需PWM调制器和相关参数设计等优点,但仅可确保所选开关函数组合在一个控制周期内的最优,这样将使得系统控制趋于保守,而影响系统控制性能。分析传统变流器FCS-MPC算法的保守性,提出一种在一个控制周期内同时考虑最优开关函数组合及次优开关函数组合,并确保在两个控制周期内所选开关函数组合最优的多步预测的FCS-MPC算法(finitecontrol set model predictive control with multi-step prediction,FCS-MPCMSP);进行采用该算法的两电平三相电压型逆变器在空载、带阻感性负载、带非线性负载及负载投入等工况下的仿真和实验。仿真及实验结果表明:采用该算法的三相电压型逆变器输出电压与给定电压的差值明显小于采用传统FCS-MPC算法的情况,改善了逆变器输出电压质量,从而验证了该算法的有效性及可行性。展开更多
本文研究了无刷直流电机(brushless direct current motor,BLDCM)混沌系统的全局有限时间同步问题.利用混沌吸引子的有界性,提出了两步控制策略.首先不施加控制,让主–从混沌系统各自的轨迹收敛到各自的吸引子中,并估计了吸引子的界和...本文研究了无刷直流电机(brushless direct current motor,BLDCM)混沌系统的全局有限时间同步问题.利用混沌吸引子的有界性,提出了两步控制策略.首先不施加控制,让主–从混沌系统各自的轨迹收敛到各自的吸引子中,并估计了吸引子的界和收敛时间;再对收敛到吸引子的从系统施加状态误差反馈控制,根据有限时间稳定性理论,得出该控制器在满足一定条件时,两个相同的混沌系统可以快速达到有限时间同步.这种方法在主从系统的初始值相差很大的情况下可以大大减少控制成本,并且可以并估计同步时间.文章最后用仿真结果验证了所得判据的可行性和有效性.展开更多
文摘This paper investigates the finite-time attitude tracking problem for rigid spacecraft. Two backstepping finite-time slid- ing mode control laws are proposed to solve this problem in the presence of inertia uncertainties and external disturbances. The first control scheme is developed by combining sliding mode con- trol with a backstepping technique to achieve fast and accurate tracking responses. To obtain higher tracking precision and relax the requirement of the upper bounds on the uncertainties, a se- cond control law is also designed by combining the second or- der sliding mode control and an adaptive backstepping technique. This control law provides complete compensation of uncertainty and disturbances. Although it assumes that the uncertainty and disturbances are bounded, the proposed control law does not require information about the bounds on the uncertainties and disturbances. Finite-time convergence of attitude tracking errors and the stability of the closed-loop system are ensured by the Lya- punov approach. Numerical simulations on attitude tracking control of spacecraft are provided to demonstrate the performance of the proposed controllers.
基金The present research was supported by the National Natural Science Foundation of China(Grants 11972369,51809271,11872374 and 11602299).
文摘Shock wave/boundary layer interaction(SWBLI)is still one of the unresolved bottlenecks that restrict the development of more advanced flight vehicles.Supersonic forward-facing step(FFS),an extreme case of compression ramp,often occurs severe SWBLIs with a large separation bubble.In this paper,experimental investigations on vortical structures and density fluctuations characteristics of supersonic FFS controlled by self-sustaining dual synthetic jets(SDSJ)are carried out in a Mach number 2.95 wind tunnel.High spatial–temporal resolution flowfield images of FFS without/with active flow control are captured by adopting nano-particle-based planar laser scattering technique.The control effects of the distance between the actuator and the step are mainly compared.The paper finds that the SDSJ can effectively change the feature of flowfield,eliminate the separation shock and the reattachment shock,compel the original shock induced by the step leading edge to distort and reduce its intensity finally.Density fluctuations analysis demonstrates that the whole flows seem to move upstream with the increase of distance(dS-J).Discrete Fourier transformation spectrums results reveal that the fluctuations are mainly located in the low-frequency region at first.High-frequency components and frequency bandwidth increase slightly after the SDSJ are applied.
文摘变流器有限控制集模型预测控制(finite control setmodel predictive control,FCS-MPC)算法是一种变流器优化控制算法。该算法具有动态响应快、处理系统约束灵活且无需PWM调制器和相关参数设计等优点,但仅可确保所选开关函数组合在一个控制周期内的最优,这样将使得系统控制趋于保守,而影响系统控制性能。分析传统变流器FCS-MPC算法的保守性,提出一种在一个控制周期内同时考虑最优开关函数组合及次优开关函数组合,并确保在两个控制周期内所选开关函数组合最优的多步预测的FCS-MPC算法(finitecontrol set model predictive control with multi-step prediction,FCS-MPCMSP);进行采用该算法的两电平三相电压型逆变器在空载、带阻感性负载、带非线性负载及负载投入等工况下的仿真和实验。仿真及实验结果表明:采用该算法的三相电压型逆变器输出电压与给定电压的差值明显小于采用传统FCS-MPC算法的情况,改善了逆变器输出电压质量,从而验证了该算法的有效性及可行性。
文摘本文研究了无刷直流电机(brushless direct current motor,BLDCM)混沌系统的全局有限时间同步问题.利用混沌吸引子的有界性,提出了两步控制策略.首先不施加控制,让主–从混沌系统各自的轨迹收敛到各自的吸引子中,并估计了吸引子的界和收敛时间;再对收敛到吸引子的从系统施加状态误差反馈控制,根据有限时间稳定性理论,得出该控制器在满足一定条件时,两个相同的混沌系统可以快速达到有限时间同步.这种方法在主从系统的初始值相差很大的情况下可以大大减少控制成本,并且可以并估计同步时间.文章最后用仿真结果验证了所得判据的可行性和有效性.
