지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학술대회자료
- 저자정보
- 발행연도
- 2015.10
- 수록면
- 1,463 - 1,468 (6page)
이용수
초록· 키워드
오류제보하기
A sliding mode control method is presented in this paper, which is proven to achieve asymptotic limit cycle oscillation (LCO) suppression in unmanned aerial vehicle wings equipped with synthetic jet actuators (SJA). With a focus on applications involving small unmanned aerial vehicles (SUAV) with limited onboard computing resources, the proposed control law is designed to be inexpensively implemented, requiring no adaptive laws, function approximators, or pitching and plunging velocity measurements. Challenges in the control design include input-multiplicative uncertainty due to the parametric uncertainty and nonlinearity that are inherent in the SJA dynamic model. To achieve the result, a sliding mode control strategy is amalgamated with a velocity estimator, which is designed using a bank of dynamic filters. This is the first output feedback control result that achieves asymptotic LCO regulation in the presence of an uncertain, nonlinear SJA dynamic model, without the use of adaptive laws or neural networks. A detailed model of the SUAV dynamics is utilized along with a rigorous Lyapunov-based stability analysis to prove asymptotic regulation of the pitching and plunging displacements, and numerical simulation results are provided to demonstrate the performance of the proposed control design.
목차
Abstract
1. INTRODUCTION
2. DYNAMICAL MODEL
3. CONTROL DEVELOPMENT
4. SIMULATION RESULTS
5. CONCLUSIONS
REFERENCES
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UCI(KEPA) : I410-ECN-0101-2016-569-001919285