항공기 프레임 구조의 모달 해석 기반 공진 특성 및 구조 안전성 평가 = Resonance Characteristic Analysis of an Aircraft Frame Structure Based on Modal Analysis for Structural Safety Evaluation

다국어 초록 (Multilingual Abstract)

With the rapid expansion of Personal Air Vehicle (PAV) and Urban Air Mobility (UAM) markets, there is a growing need for efficient maintenance approaches to ensure the structural safety of small-scale aircraft. In this study, finite element analysis was conducted on a small aircraft fuselage structure to identify its dynamic characteristics and potential resonance regions, and to evaluate its structural integrity. Frequency response analysis showed an increase in structural response around 78.29Hz, where the structure exhibited a vertical bending deformation pattern. In addition, stress distribution analysis indicated that relatively higher stress concentration occurred at specific locations. The corresponding frequency was converted to engine rotational speed and compared with actual operating conditions, confirming a sufficient separation margin from the response-increase region. These results provide fundamental data for structural integrity assessment, vibration-based condition monitoring, and maintenance planning of small aircraft structures.