프로펠러 가진 주파수를 고려한 소형 항공기 서스펜션 마운트의 동적 응답 해석 및 진동 분석
Dynamic Response and Vibration Analysis of a Light Aircraft Suspension Mount Considering Propeller Excitation Frequencies
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원문정보
초록
영어
This study evaluated the dynamic response and vibration characteristics of a Rotax 915 iS engine suspension mount for personal air vehicles (PAV) using finite element analysis. A 3D CAD model was developed in CATIA V5, and modal and harmonic response analyses (Modal SSD) were performed in Abaqus. At the primary excitation frequency (4,000 RPM, 66.67 Hz), the support node (Node 164) showed a peak velocity of 0.0437 IPS, satisfying the vibration criterion (≤0.05 IPS), while the critical node (Node 34207) reached 0.1850 IPS with 76.4% attenuation to the support. In the high-frequency range (800–3,600 Hz), responses at 1.62 kHz (0.1063 IPS) and 2.43 kHz (1.1024 IPS) exceeded the criterion despite 90.4% attenuation. These results indicate that the mount satisfies the vibration criterion at the primary operating speed, but additional damping or structural reinforcement is required to reduce high-frequency resonance.
목차
Abstract 1. 서론 2. 본론 2.1 해석 방법 2.2 해석 결과 3. 결론 후기 References