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대체 비상탈출 조건을 고려한 초음속 전투기용 캐노피 작동부 구조해석
김동현,김동만,김영우,양건명,Kim, Dong-Hyun,Kim, Dong-Man,Kim, Young-Woo,Yang, Jian-Ming 한국군사과학기술학회 2007 한국군사과학기술학회지 Vol.10 No.4
In this study, analysis of structural design criteria for the canopy actuating device has been conducted considering the aerodynamic breakaway capabilities of jettisonable canopy system. Unsteady aerodynamic loads for the opened canopy configuration at passively controlled jettision mode were computed using CFD method. The general purpose multi-body finite element code, SAMCEF Mecano, is used in the implemented analyses for the passive jettision condition. The recommended altitude and speed of aircraft was suggested as design criteria of aerodynamic breakaway capability of jettisonable canopy system as a bakup egress method when normal canopy jettison sequence malfunctioned. Aerodynamic breakaway condition of jettisonable canopy was also simulated and the fracture load conditions of canopy actuator were investigated.
틸트로터 항공기의 탑재장비 상세 지지구조 형상을 고려한 전산진동해석 및 평가
김유성 ( Yu Sung Kim ),김동현 ( Dong Hyun Kim ),김동만 ( Dong Man Kim ),양건명 ( Jian Ming Yang ),이정진 ( Jung Jin Lee ) 한국항공운항학회 2007 한국항공운항학회지 Vol.15 No.4
In this study, computational structural vibration analyses of a smart unmanned aerial vehicle (SUAV) with tilt-rotors due to dynamic hub loads have been conducted considering detailed supporting structures of installed equipments. Three-dimensional dynamic finite element model has been constructed for different fuel conditions and tilting angles corresponding to helicopter, transition and airplane flight modes. Practical computational procedure for modal transient response analysis is successfully established. Also, dynamic loads generated by rotating blades and wakes in the transient and forward flight conditions are calculated by unsteady computational fluid dynamics technique with sliding mesh concept. As the results of present study, transient structural displacements and accelerations of the vibration sensitive equipments are presented in detail. In addition, vibration characteristics of structures and installed equipments of which safe operation is normally limited by the vibration environment specifications are physically investigated for different flight conditions.