Flow-Induced Vibration Characteristics of a Missile Control Surface Considering Shock Wave and Structural Nonlinearity

충격파 및 구조비선형성을 고려한 미사일 조종면의 유체유발 진동특성

Nonlinear aeroelastic characteristics of a missile control surface are investigated in this study. The wing model has freeplay structural nonlinearity at its pitch axis. Nonlinear aerodynamic flows with unsteady shock waves are also considered in high-speed flow region. To effectively consider a freeplay structural nonlinearity, the fictitious mass method (FMM) is applied to structural vibration analysis based on finite element method (FEM). (omitted)