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.

Abstract
1. 서 론
2. 본 론
    2.1 사용 프로그램 및 수치 해석 환경 설정
    2.2 해석 대상 및 재료 물성
    2.3 해석 조건 정의
    2.4 공진 위험 평가 지표 정의
3. 분석 및 결과
    3.1 주파수 응답 기반 공진 특성 분석
    3.2 공진 구간에서의 구조 거동 분석
    3.3 주요 노드별 국부적 응력 분석
    3.4 공진주파수와 운용 회전수 비교
4. 결 론
후 기
References

• 원동해(Dept. of Aero Mechanical Engineering, Kyungwoon University) | Won Dong Hae
• 김재필(Kyungwoon University of Aero Mechanical Engineering, Professor) | Kim Jae Pil Corresponding author