We present in this article a MATLAB toolkit with a user-friendly graphical interface for composite nonlinear feedback control system design. The toolkit can be utilized to design a fast and smooth tracking controller ...We present in this article a MATLAB toolkit with a user-friendly graphical interface for composite nonlinear feedback control system design. The toolkit can be utilized to design a fast and smooth tracking controller for a class of linear systems and nonlinear systems with actuator and other nonlinearities as well as with external disturbances. The parameters of the controller can be tuned easily on the user panel or autotuned by the toolkit. The toolkit is capable of displaying both time-domain and frequency-domain responses on its main panel and generating three different types of con- trol laws, namely, the state feedback, the full-order measurement feedback and the reduced-order measurement feedback controllers. The usage and design procedure of the toolkit are illustrated by practical examples on a rotational/translational actuator （RTAC） system and a hard disk drive servo system. The toolkit can be utilized to design servo systems that deal with point-and-shoot fast targeting.展开更多
In this paper,a nonlinear°ight control law is designed for a hybrid unmanned aerial vehicle(UAV)to achieve the advanced°ight performances with the autonomous mission management(AMM).The hybrid UAV is capable...In this paper,a nonlinear°ight control law is designed for a hybrid unmanned aerial vehicle(UAV)to achieve the advanced°ight performances with the autonomous mission management(AMM).The hybrid UAV is capable of hovering like quadrotors and maneuvering as-xed-wing aircraft.The main idea is to design the°ight control laws in modules.Those modules are organized online by the autonomous mission management.Such online organization will improve the UAV autonomy.One of the challenges is to execute the transition°ight between the rotary-wing and-xed-wing modes.The resulting closed-loop system with the designed°ight control law is veri-ed in simulation and the simulation results demonstrate that the resulting closed-loop system can successfully complete the designated°ight missions including the transition°ight between the rotary-wing and-xed-wing modes.展开更多
基金supported by the Scientific Research Foundation for Returned Overseas Chinese Scholars,Ministry of Education of China(No.LXKQ0804)
文摘We present in this article a MATLAB toolkit with a user-friendly graphical interface for composite nonlinear feedback control system design. The toolkit can be utilized to design a fast and smooth tracking controller for a class of linear systems and nonlinear systems with actuator and other nonlinearities as well as with external disturbances. The parameters of the controller can be tuned easily on the user panel or autotuned by the toolkit. The toolkit is capable of displaying both time-domain and frequency-domain responses on its main panel and generating three different types of con- trol laws, namely, the state feedback, the full-order measurement feedback and the reduced-order measurement feedback controllers. The usage and design procedure of the toolkit are illustrated by practical examples on a rotational/translational actuator （RTAC） system and a hard disk drive servo system. The toolkit can be utilized to design servo systems that deal with point-and-shoot fast targeting.
文摘In this paper,a nonlinear°ight control law is designed for a hybrid unmanned aerial vehicle(UAV)to achieve the advanced°ight performances with the autonomous mission management(AMM).The hybrid UAV is capable of hovering like quadrotors and maneuvering as-xed-wing aircraft.The main idea is to design the°ight control laws in modules.Those modules are organized online by the autonomous mission management.Such online organization will improve the UAV autonomy.One of the challenges is to execute the transition°ight between the rotary-wing and-xed-wing modes.The resulting closed-loop system with the designed°ight control law is veri-ed in simulation and the simulation results demonstrate that the resulting closed-loop system can successfully complete the designated°ight missions including the transition°ight between the rotary-wing and-xed-wing modes.
