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균일분포 온도하의 두꺼운 복합 재료 적층판의 열적 좌굴 해석
이영신,이열화,양명석,박복선,이종수,Lee, Young-Shin,Lee, Yeol-Wha,Yang, Myung-Seog,Park, Bock-Sun,Lee, Jong-Soo 대한기계학회 1993 대한기계학회논문집 Vol.17 No.7
In this paper, the thermal buckling of thick composite angle-ply laminates subject to uniform temperature distribution is studied. For the plates of 4-edges simply supported condition and those of 4-edges clamped condition, the critical buckling temperatue is derived, using tile finite element method based on the shear deformation theory. The effects of lamination angle, layer number, laminate thickness, plate aspect ratio and boundary constraints upon the critical buckling temperature are presented.
최대 열적 좌굴하중을 갖는 두꺼운 복합재료 적층판의 설계
이영신,이열화,양명석,박복선,Lee, Young-Shin,Lee, Yeol-Wha,Yang, Myung-Seog,Park, Bock-Sun 대한기계학회 1993 대한기계학회논문집 Vol.17 No.7
In this paper, the design of thick laminated composite plate subjected to thermal buckling load under uniform temperature distribution is presented. In the design procedures of composite laminated plates for maximum thermal buckling load. the finite element method based on shear deformed theory is used for the analysis or laminated plates. One-demensional search method is used to find optimal fiber orientation and, in the next step, optimal thickness is investigated. Design variables such as fiber orientation and ply thicknesses coefficient of plates are adopted. The optimal design for the symmetric or antisymmetric laminated plates consisted of 4 layers with maximum thermal buckling load is performed.
신영석,황철규,양해석,이열화,Shin Young-Sug,Hwang Cheol-Gyu,Yang Hae-Seok,Lee Yeol-Wha 한국군사과학기술학회 2004 한국군사과학기술학회지 Vol.7 No.4
In order to model a connection part between a control fin and actuator, the related characteristics of a dynamic stiffness were extracted from experiments. These characteristics include the static stiffness of a control fin and the dynamic stiffness of an actuator, so they are called the mixed dynamic stiffness here. This mixed dynamic stiffness is used as the boundary condition of a control fin connected to an actuator when the flutter characteristics are analyzed. The simulated stiffness of an actuator is corrected from the experiment results and the mixed dynamic is finally formulated in the domain of frequencies.
구동장치의 동강성을 고려한 미사일 조종날개의 비선형 플러터 해석
신원호(Won-Ho Shin),배재성(Jae-Sung Bae),이인(In Lee),한재흥(Jae-Hung Han),신영석(Young-Suk Shin),이열화(Yeol-Wha Lee) 한국항공우주학회 2005 韓國航空宇宙學會誌 Vol.33 No.2
구동기의 백래쉬와 동강성을 고려한 미사일 조종날개의 비선형 공탄성 해석이 수행되었다. 아음속 비정상 공기력 계산을 위해 DHM을 사용하였고 최소상태접근법을 사용하여 근사하였다. 비선형 플러터 해석을 위해 백래쉬는 유격으로 모델하고 기술 함수법을 사용하여 선형화하였다. 또한, 동강성은 주파수의 함수로 모터의 운동방정식으로부터 계산하였다. 선형 및 비선형 플러터 해석 결과들은 공력탄성학적 특성들이 백래쉬와 동강성에 중요한 영향을 받는다는 것을 보여준다. 비선형 플러터 해석에서 다양한 제한 주기 운동이 선형플러터 속도 이하에서 관측되었다. 또한 플러터 특성과 응답을 시간영역에서도 조사하였다. Nonlinear aeroelastic analyses of a missile control fin are performed considering backlash and dynamic stiffness of actuator. Doublet-Hybrid method is used for the calculation of subsonic unsteady aerodynamic forces, and aerodynamic forces are approximated by the minimum-state approximation. For nonlinear flutter analysis backlash is represented by a free-play and is linearized by using the describing function method. Also, dynamic stiffness is function of frequency and is calculated by solving equation of motion for actuator. The linear and nonlinear flutter analyses show that the aero elastic characteristics are significantly dependent on the backlash and dynamic stiffness. From the nonlinear flutter analysis, various types of limit cycle oscillations are observed in a range of air speeds below the linear divergent flutter boundary. The nonlinear flutter characteristics and the nonlinear aeroelastic responses are also investigated in the time domain.