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Design improvements of the smart active trailing-edge flap (ATF) for rotating test : 헬리콥터 진동제어용 지능형 능동뒷전 플랩의 회전시험을 위한 설계의 개선
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- Authors
- Advisor
- 신상준
- Major
- 공과대학 기계항공공학부
- Issue Date
- 2015-02
- Publisher
- 서울대학교 대학원
- Keywords
- Active Trailing-edge Flap (ATF) ; piezoelectric actuator ; vibration control ; active rotor blade
- Description
- 학위논문 (석사)-- 서울대학교 대학원 : 기계항공공학부, 2015. 2. 신상준.
- Abstract
- In this dissertation, small-scaled blade prototypes with the flap-driving mechanism, called SNUF (Seoul National University Flap), were manufactured, and tested in order to realize vibratory load reduction in the rotor system. It was achieved by an active trailing-edge flap which is based on piezoelectric actuator. However, it turned out that the target value (±4°) of the flap deflection angle was not accomplished in the previous designs. Therefore, the flap driving mechanism needs to be amended. Thus, a new piezoelectric actuator was selected to achieve the target deflection by considering the nonlinear relationship between flap deflection angle and the moment arm length. Re-selection of the actuator required increase of the blade inner space and its size. Therefore, it was required to validate the cross-sectional design of the improved blade configuration. So as to verify the structural integrity, cross-sectional analysis was conducted by using UM/VABS. Revised flap driving mechanism and its test-bed shows quite satisfactory result during the static bench test even though there still remain several issues which should be solved. After completion of the non-rotating static test of the new flap-driving mechanism, a prototype blade will be manufactured and tested in the whirl tower
- Language
- English
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