정적 공탄성 효과를 고려한 Wing-Box 구조 날개의 천음속/초음속 공탄성 해석

Abstract

In this study, a nonlinear aeroelastic analysis system for a realistic wing-box structure has been developed in the transonic and supersonic flow region. The transonic small disturbance code has been incorporated into the analysis system to consider nonlinear aerodynamic effect. The fully coupled time-integration method(CTIM) is applied to observe the detailed aeroelastic responses with static aeroelastic deformation effect. A conservative wing-box model of a fighter wing is constructed and the corresponding free vibration analysis has been performed using MSC/NASTRAN. The computed aeroelastic stability of the fighter type wing are presented in the subsonic, transonic and supersonic flow regime. The linear aerodynamic theories of doublet lattice and doublet point techniques are also applied int the subsonic and supersonic flow region and the results are compared with the time-domain analysis considering nonlinear aerodynamic effect.