헬기의 진동과 피로에 대한 내구성 연구 = Study on Durability by Vibration and Fatigue of the Helicopter

다국어 초록 (Multilingual Abstract)

This study analyzes stress, fatigue and vibration on main rotor and body of helicopter. The maximum stress is shown on adjoint part between body and main rotor at the lower position of main rotor. As the maximum displacement amplitude is happened at 4000Hz, there is no resonance and the state of helicopter becomes safe at hovering without the abnormal air current and the disabled rotor. Among the cases of nonuniform fatigue loads, "SAE bracket history" with the severest change of load becomes most unstable but "Sample history" becomes most stable. In case of "Sample History" with the average stress of 0MPa to -105MPa and the amplitude stress of 0MPa to 8.539×105MPa, the possibility of maximum damage becomes 3%. This stress state can be shown with 5 times more than the damage possibility of "SAE bracket history" or "SAE transmission". The structural result of this study by using the analysis of vibration and fatigue can be effectively utilized for safe and durable design of helicopter.

목차 (Table of Contents)

• ABSTRACT
• 1. 서론
• 2. 해석 결과
• 3. 결론
• 참고문헌

참고문헌 (Reference)

1 허선철, "자동차엔진용 금속기 복합재료의 피로균열거동에 관한 연구" 한국자동차공학회 11 (11): 140-146, 2003

2 한문식, "쇽업소버의 구조강도 해석" 한국기계가공학회 9 (9): 53-59, 2010

3 김상덕, "동축반전 헬리콥터형 소형 무인항공기 설계 및 제작" 한국항공우주학회 37 (37): 293-300, 2009

4 기영중, "공진현상을 이용한 실물 복합재 헬리콥터 블레이드의 피로수명 평가" 한국항공우주연구원 9 (9): 1-7, 2010

5 Suh, C. W., "Fatigue Life Prediction of Composite Rotor Blade for Multipurpose Helicopter" 423-426, 2000

6 Cho, H. D., "Development of Loader with Four Wheel Driving and Four-Type Wheel Steering System" 3 (3): 71-78, 2004

7 Swanson, J., "Ansys 12.0" Ansys Inc 2009

8 Lee, H. S., "A Study on the Vibration Characteristics of Helicopter Rotating Blades with Multiple Load Paths" 564-567, 1994