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- 저자 : Qianlei Jia (검색결과 2 건)
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Maneuverable Aircraft Flight Control Using Nonlinear Dynamic Inversion
Qianlei Jia,Weiguo Zhang,Jingping Shi,Jiayue Hu 제어로봇시스템학회 2018 제어로봇시스템학회 국제학술대회 논문집 Vol.2018 No.10
Feedback linearization is a mature and highly applied control method in aerospace and other industrial applications. The designed control inputs are used to cancel the nonlinear terms using negative feedback of these terms. This paper focuses on designing a fight simulation model for F-16 fighter jet in responding to diverse sharp maneuvers. F-16 model is expressed by fixed-mass rigid-body six-degree-of freedom (6-DOF) equations of motion, which include the detailed aerodynamic coefficients, the engine model and the actuator models that have lags and limits. The two-time scaled concept of dynamic inversion method divides the aircraft states into groups according to their rate of response. Dynamic Inversion (DI) control law is designed for the fast variables using the aerodynamic control surfaces as inputs. Next, DI 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 have proved the validity and rationality of the proposed technique .
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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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