서지주요정보
정지 및 전진 비행시 복합재료 무힌지 로우터 블레이드의 공탄성 해석 = Aeroelastic analysis of composite hingeless rotor blades in hovering and forward flights
서명 / 저자 정지 및 전진 비행시 복합재료 무힌지 로우터 블레이드의 공탄성 해석 = Aeroelastic analysis of composite hingeless rotor blades in hovering and forward flights / 전성민.
저자명 전성민 ; Seong, Min-Jeon
발행사항 [대전 : 한국과학기술원, 1999].
Online Access 원문보기 원문인쇄

소장정보

등록번호

8009649

소장위치/청구기호

학술문화관(문화관) 보존서고

DAE 99007

휴대폰 전송

도서상태

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반납예정일

초록정보

The aeroelastic response and stability of isotropic and composite rotor blades are investigated using a large deflection-type beam theory in hovering and forward flight. The finite element equations of motion for beams undergoing arbitrary large displacements and rotations, but small strains, are obtained from Hamilton's principle. The sectional elastic constants of a composite box beam including warping deformations are determined from the refined cross-sectional finite element method. Static and dynamic behavior of composite box beams is compared with the previously published experimental and theoretical results for verification. A two-dimensional, quasi-steady strip theory with the Drees linear inflow model is applied for the aerodynamic calculation. The nonlinear, periodic blade response is obtained by integrating the full finite element equation in time through a coupled vehicle trim procedure in the forward flight condition. After an equilibrium position is obtained, the aeroelastic stability analysis is performed for the linearized stability equations with respect to this equilibrium position. In the hovering case, numerical results of stability analysis are verified and the effects of the structural couplings on the stability are systematically investigated for six ply configurations of the composite box beams. In the forward flight condition, the results of a full finite element analysis using the large deflection-type beam theory are compared with those of a previously published modal analysis using the moderate deflection-type beam theory and it is found that the nonlinear kinematic effects play an important role in the hingeless rotor aeroelastic analysis.

서지기타정보

서지기타정보
청구기호 {DAE 99007
형태사항 xv, 126 p. : 삽도 ; 26 cm
언어 한국어
일반주기 부록 수록
저자명의 영문표기 : Seong-Min Jeon
지도교수의 한글표기 : 이인
지도교수의 영문표기 : In Lee
학위논문 학위논문(박사) - 한국과학기술원 : 항공우주공학과,
서지주기 참고문헌 : p. 66-73
주제 헬리콥터 로우터 블레이드
상자형 복합재료 보
공력탄성학
비선형 유한요소법
Helicopter rotor blade
Composite box beam
Aeroelasticity
Nonlinear FEM
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