서지주요정보
롤 운동을 고려한 발사체 곡면날개의 플러터 해석 = Flutter analysis of launch vehicle curved fin considering roll motion
서명 / 저자 롤 운동을 고려한 발사체 곡면날개의 플러터 해석 = Flutter analysis of launch vehicle curved fin considering roll motion / 백승길.
저자명 백승길 ; Paek, Seung-Kil
발행사항 [대전 : 한국과학기술원, 1998].
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소장정보

등록번호

8008346

소장위치/청구기호

학술문화관(문화관) 보존서고

DAE 98005

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초록정보

The aeroelastic stabilities of curved fins(or wrap-around fins) in roll spin are investigated in the supersonic flow region. Due to the inherent spin, wrap-around fins are subjected to both aerodynamic and centrifugal force. The aerodynamic force is computed by solving Euler equations in a body-fixed rotating coordinate frame. The finite element structural modeling, static and normal mode analyses of the spinning structure are performed by using EMRC/NISA. For the consistent analysis, a nondimensionalized aeroelastic equation considering the roll spin motion is derived and aeroelastic parameters, such as velocity index and mass ratio, are devised. An efficient procedure to analyze the flutter characteristics of the spinning elastic wing is suggested. Many comparisons with the previous experimental and numerical results had been made for the steady and unsteady aerodynamic load computation and proved the reliability of the developed Euler code. The equilibrium spin rate of an elastic wrap-around fin projectile, defined as the spin rate at which the net roll moment is zero, is computed at various velocity indices and mass ratios. The effect of aerodynamic force increases the equilibrium roll rate, while the effect of centrifugal force decreases the equilibrium roll rate. From the flutter analyses for wrap-around fins with various attachment angles, it is observed that the flutter characteristics with spin are very different from those without spin. It indicates that the consideration of the roll spin must be made to predict the flutter stability accurately. Due to geometric asymmetry of the wrap-around fin, the flutter characteristics in each spin directions are different each other. Flutter analyses in each spin directions indicate that there exists the more stable spin direction for Flutter.

서지기타정보

서지기타정보
청구기호 {DAE 98005
형태사항 x, 181 p. : 삽도 ; 26 cm
언어 한국어
일반주기 저자명의 영문표기 : Seung-Kil Paek
지도교수의 한글표기 : 이인
지도교수의 영문표기 : In Lee
학위논문 학위논문(박사) - 한국과학기술원 : 항공우주공학과,
서지주기 참고문헌 : p. 173-181
주제 곡면 날개
롤 회전
공력탄성학
플러터
오일러 방정식
Wrap-around fin(WAF)
Roll spin
Aeroelasticity
Flutter
Euler equations
Multiple delaminations
Composite laminated panel
Buckling
Post buckling analysis
Delamination buckling
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