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논문 기본 정보

자료유형
학술대회자료
저자정보
Qianlei Jia (Northwestern Polytechnical University) Weiguo Zhang (Northwestern Polytechnical University) Jingping Shi (Northwestern Polytechnical University) Jiayue Hu (Northwestern Polytechnical University)
저널정보
제어로봇시스템학회 제어로봇시스템학회 국제학술대회 논문집 ICCAS 2018
발행연도
2018.10
수록면
1,513 - 1,518 (6page)

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초록· 키워드

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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 .

목차

Abstract
1. INTRODUCTION
2. AIRPLANE MATHEMATICAL MODELING
3. DYNAMIC INVERSION CONTROL LAW
4. SIMULATION RESULTS
5. CONCLUSION
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UCI(KEPA) : I410-ECN-0101-2018-003-003540221