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논문 기본 정보

자료유형
학술저널
저자정보
Byung-Yoon Lee (Korea Advanced Institute of Science and Technology) Dong-Wan Yoo (Korea Advanced Institute of Science and Technology) Min-Jea Tahk (Korea Advanced Institute of Science and Technology)
저널정보
한국항공우주학회 International Journal of Aeronautical and Space Sciences International Journal of Aeronautical and Space Sciences Volume.14 Number.1
발행연도
2013.3
수록면
58 - 66 (9page)

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초록· 키워드

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This paper addresses the performance of three different types of attitude control systems for the Quad-rotor UAV to perform the flip maneuver. For this purpose, Quad-rotor UAV’s 6-DOF dynamic model is derived, and it was used for designing an attitude controller of the Quad-rotor UAV. Attitude controllers are designed by three different methods. One is the open-loop control system design, another is the PD control system design, and the last method is the sliding mode control system design. Performances of all controllers are tested by 6-DOF simulation. In case of the open-loop control system, control inputs are calculated by the quad-rotor dynamic model and thrust system model that are identified by the thrust test. The 6-DOF realtime simulation environment was constructed in order to verify the performances of attitude controllers.

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Abstract
1. Introduction
2. Dynamic Modeling of the Quad-Rotor
3. Control System Design
4. Simulation
5. Conclusion
Acknowledgement
References

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UCI(KEPA) : I410-ECN-0101-2014-550-003079109