틸트로터 항공기의 탑재장비 상세 지지구조 형상을 고려한 전산진동해석 및 평가 = Computation Vibration Analysis and Evaluation of a Tilt-Rotor Aircraft Considering Equipment Supporting Structures

다국어 초록 (Multilingual Abstract)

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.

참고문헌 (Reference)

1 "회전로터 및 후류 동하중을 고려한 스마트 무인기 천이응답해석" 16 (16): 926-936, 2006

2 Bathe, K.J, "Finite Element Procedures" Prentice-Hall Inc 1996

3 2nd Ed, "Elements of Vibrational Analysis" McGraw-Hill 1986

4 "Computational methods in Structural Dynamics" Sijthoff & Noordhoff International Publishers 1980