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논문 기본 정보

자료유형
학술대회자료
저자정보
Ri Liu (Air Force Engineering University) Xiuxia Sun (Air Force Engineering University) Wenhan Dong (Air Force Engineering University) Guangzhi Xu (Air Force Engineering University)
저널정보
제어로봇시스템학회 제어로봇시스템학회 국제학술대회 논문집 ICCAS 2015
발행연도
2015.10
수록면
526 - 531 (6page)

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초록· 키워드

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This paper investigates the problem of designing a novel sliding mode controller of a transport aircraft for airdrop modes in the presence of bounded nonlinear uncertainty and actuator fault without the prior knowledge of the bounds. On the basis of feedback linearization of the aircraft-cargo dynamic model, an autopilot inner-loop which combines sliding mode control with adaptive function approximation is developed. The complex nonlinear uncertainty of the model is factorized into a known matrix and an uncertainty function. An adaptive approximation approach is used to estimate the function, and it overcomes the conservation drawback of the sliding mode control that relies on the bounds on the uncertainty/actuator fault. Notably, the adaptation law formed using the projection operator can bound the estimated function, and this avoids singularity of the control signal. Simulations verify the good performance of the control system, which can satisfy the airdrop mission performance indexes well, even in the presence of ±20% aerodynamic coefficients uncertainty and 20% actuator fault.

목차

Abstract
1. INTRODUCTION
2. AIRCRAFT-CARGO DYNAMIC MODEL
3. INPUT-OUTPUT FEEDBACK LINEARIZATION
4. CONTROL LAW DESIGN
5. SIMULATION ANALYSIS
6. CONCLUSION
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UCI(KEPA) : I410-ECN-0101-2016-569-001911507