제자리 비행 조건에서의 고정밀 공력-구조 연계 해석을 통한 로터 블레이드 하중 해석 모델 개발

In this study, a structural model of a composite rotor blade was developed through a three-dimensional finite element formulation, and it was integrated with a panel method-based aerodynamic analysis model to enable high-fidelity fluid-structure coupled analysis. For the rotor blade structural model, the Updated Lagrangian (UL) formulation was employed to account for geometric nonlinear behavior, and the force and moment balance method was used to evaluate the structural loads acting on the blade cross-sections. Additionally, the aerodynamic analysis model was developed using a source-doublet panel and vortex particle method, enabling the prediction of aerodynamic loads and the wake characteristics of the rotor blade. To validate the developed rotor blade load analysis model, the main rotor blade design and test data of the Multi-Purpose Unmanned Helicopter developed by the KARI(Korea Aerospace Research Institute) were utilized.