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RISS 인기검색어
- 검색키워드
- 저자 : Yongxi Lyu (검색결과 5 건)
- 무료
- 기관 내 무료
- 유료
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An Improved Method of Control Law Design at High Angle of Attack Based on Wind Tunnel Test Data
Yongxi Lyu,Yuyan Cao,Weiguo Zhang,Jingping Shi,Xiaobo Qu 제어로봇시스템학회 2018 제어로봇시스템학회 국제학술대회 논문집 Vol.2018 No.10
This paper presents an improved dynamic inversion (DI) based method, which is further successfully applied to the high angle of attack flight control of the aircraft under the influence of unsteady aerodynamics. On the basis of large oscillation wind tunnel test data, the accurate unsteady aerodynamic model is established by the sequential minimal optimization - support vector regression (SMO-SVR) method. The nonlinear longitudinal aircraft model is created by considering engine model, atmospheric model, actuator model, and so on. In order to solve the problem of large control error and control delay caused by the unsteady aerodynamics, the improved DI method is proposed. The integral is added in the pitch angle rate control, and the control law of angle of attack is designed combining lag correction. The daisy chain allocation method is utilized to obtain the deflections of the control surfaces and the engine vector nozzle. Numerical simulation of Cobra maneuver is employed to demonstrate the advantages and potential practical application of the proposed improved control law design method.
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Finite-time Observer Based Predefined-time Aircraft Attitude Tracking Control
Yunhao Fu,Jingping Shi,Yongxi Lyu 제어·로봇·시스템학회 2023 International Journal of Control, Automation, and Vol.21 No.11
This paper investigates the attitude tracking issue of the fixed-wing unmanned aerial vehicle (UAV) with model uncertainty and external disturbance using contemporary predefined-time stability theory and disturbance observer. Firstly, by using a time-varying tuning function with the expected settling time, composite state tracking errors are introduced to the design process of dynamic surface control, which is named dynamic surface based predefined time control (DSPTC). Then, the lumped disturbances are estimated by finite time extended states observer (FTESO). It is proved that all of signals in the aircraft attitude system are globally uniformly ultimately bounded. Finally, a set of simulations is implemented to validate the availability of the proposed controller.
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Adaptive Back-stepping Neural Control for an Embedded and Tiltable Vtail Morphing Aircraft
Fuxiang Qiao,Jingping Shi,Xiaobo Qu,Yongxi Lyu 제어·로봇·시스템학회 2022 International Journal of Control, Automation, and Vol.20 No.2
This paper presents an adaptive back-stepping neural control (ABNC) method for the coupled nonlinear model of a novel type of embedded surface morphing aircraft. Based on a large number of aerodynamic data for different V-tail configurations, the longitudinal and lateral aerodynamic characteristics of the aircraft are analyzed, and a nonlinear model with six degrees-of-freedom is established. To avoid the problem of “differential explosion,” the controller is designed using the traditional back-stepping control (TBC) method with a first-order filter. Radial basis function neural networks are introduced to estimate the uncertainty and external disturbance of the model, and a controller based on the ABNC method is designed. The stability of the proposed ABNC controller is proved using Lyapunov theory, and it is shown that the tracking error of the closed-loop system converges uniformly within specified bounds. Simulation results show that the ABNC controller works well, with better tracking performance and robustness than the TBC controller.
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Ehab Safwat,Weiguo Zhang,Mei Wu,Yongxi Lyu,Qianlei Jia 제어로봇시스템학회 2018 제어로봇시스템학회 국제학술대회 논문집 Vol.2018 No.10
This paper focuses on autonomous path-following flight under uncertainty and external disturbances. Integrated UAV waypoints guidance scheme based on carrot chasing guidance law is presented. In order to follow a desired path a Virtual Track Point (VTP) is introduced on the path and make the UAV chase it. The UAV updates its heading direction toward the VTP. As time progresses, the UAV will move toward the path and asymptotically follow the path. Nonlinear Dynamic Inversion (NDI) awards the flight control system researchers a straight forward method of deriving control laws for nonlinear systems. The control inputs are used to cancel unwanted terms in the equations of motion using negative feedback of these terms. The two-timescale assumption that separates the fast dynamics which are the three angular rates of the aircraft from the slow dynamics which include the angle of attack, side-slip angle, and bank angle is adopted. NDI control law is designed for the fast variables using the deflection of aerodynamic control surfaces as inputs. Next, NDI is applied to the control of the slow states using the outputs of the fast loop as inputs. Simulation results for the nonlinear flight control system are given to illustrate the effectiveness of the technique. The validation of the designed flight system controller is demonstrated through real flight test.
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Reconfigurable Flight Control System Design for Blended Wing Body UAV Based on Control Allocation
Xiaobo Qu,Jingping Shi,Haijun Zhou,Ling Zuo,Yongxi Lyu 제어로봇시스템학회 2018 제어로봇시스템학회 국제학술대회 논문집 Vol.2018 No.10
The aircraft control surface fault reconfigurable scheme based on control allocation is an active approach to achieve fault-tolerant in flight control. It has obvious advantages such as the structure and parameters of the control law does not need to be redesigned as deflector failures occurs. The attainable moment subset and allocation efficiency with typical control allocation algorithms are evaluated. A modular scheme reconfigurable flight control system (FCS) of a miniature tailless Blended Wing Body UAV is studied by utilizing weighted pseudo-inverse, direct control, and fixed-point control allocation methods. The performance of the reconfigurable FCS is tested and verified with the simulation including typical failure modes such as deflector floating, loss-of-effectiveness and lock-in-place. Results validate that the reconfigurable FCS based on control allocation has preferable ability to handle deflector failures, improve the safety and reliability of aircraft. And the modular scheme proposed in the article demonstrates a good application prospect in the field of aviation and aerospace engineering.
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