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
- 학위논문
- 저자정보
- 지도교수
- 강범수
- 발행연도
- 2016
- 저작권
- 부산대학교 논문은 저작권에 의해 보호받습니다.
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이 논문의 연구 히스토리 (3)
2016
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This study deals with numerical prediction and experimental verification on dynamic characteristics and modal analyses for a small-scale quad-rotor drone. The rotor-arm, which has a slender body with a propeller and motor at its tip, is vulnerable to resonance in specific frequency bend due to its unbalanced mass. We used vibrational analysis and modal tests to investigate and address the resonance problem. Using these methods, The fifth eigen-mode was confirmed to be the closest to the operational range of the propeller.
Using the Rayleigh’s method, Young’s modulus was calculated for each circular and octagonal type of commercial CFRP tube. Then, we compared the analytically formulated natural frequencies of the tubes with experimental and numerical values. The natural frequencies acquired in each condition had an error of up to 1.4%. This confirmed the reliability of the modulus of elasticity, and the overall validity of our experiment.
Finite Element(FE) model of a simplified quad-rotor was built to carry out dynamic characteristic analysis. The model was composed of a rotor-arm assembly with a tip mass to simulate a motor, and a free-free boundary condition was applied to provide flight status condition. Modal tests using an impact hammer instrument were performed on the simplified platform to verify the results of dynamic characteristics measurements. Consequently, a 24% separation margin was confirmed between the hazardous fifth eigen-mode and the operational range of the propeller. On a full platform, the separation margin is expected to be reduced to less than 20% owing to the increase in weight.
Using the Rayleigh’s method, Young’s modulus was calculated for each circular and octagonal type of commercial CFRP tube. Then, we compared the analytically formulated natural frequencies of the tubes with experimental and numerical values. The natural frequencies acquired in each condition had an error of up to 1.4%. This confirmed the reliability of the modulus of elasticity, and the overall validity of our experiment.
Finite Element(FE) model of a simplified quad-rotor was built to carry out dynamic characteristic analysis. The model was composed of a rotor-arm assembly with a tip mass to simulate a motor, and a free-free boundary condition was applied to provide flight status condition. Modal tests using an impact hammer instrument were performed on the simplified platform to verify the results of dynamic characteristics measurements. Consequently, a 24% separation margin was confirmed between the hazardous fifth eigen-mode and the operational range of the propeller. On a full platform, the separation margin is expected to be reduced to less than 20% owing to the increase in weight.
목차
1. 서 론 11.1 연구 배경 및 목적 12. 이론적 배경 42.1 진동의 일반론 42.2 진동의 수학적 모델 62.3 Rayleigh''s method 103. CFRP 소재 튜브의 물성치 획득 143.1 로터암의 진동 해석 및 실험 143.2 해석과 실험 결과 및 신뢰성 평가 174. 쿼드로터형 플랫폼의 진동 해석 194.1 유한요소 해석 모델 194.2 해석 결과 215. 쿼드로터형 플랫폼의 진동 실험 235.1 실험 장치 구성 235.2 실험 결과 246. 결과 분석 및 분리 여유 267. 결 론 28References 30Abstract 63
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