Scholarlink

<p>Urban Air Mobility (UAM), designed for passenger and cargo transport in cities, is emerging as a next-generation transportation solution. However, structural components face risks from turbulence and vibrations unique to urban environments. Ensuring passenger safety and comfort requires rigorous structural integrity evaluations under random load conditions aligned with certification standards. This study presents analytical methods to evaluate the structural safety of eVTOL components under random vibrations, meeting airworthiness requirements. A conservative fatigue life assessment was performed using a 1% failure-probability S–N curve. Modal analysis identified key modes, applied in steady-state and random vibration analyses based on actuator responses and DO-160G standards. Results showed a safety margin above 2 (3 Sigma) and a fatigue life exceeding 10<sup>7</sup> cycles, confirming structural reliability. These methods provide a framework for airworthiness certification of eVTOL aircraft.</p>

错误：搜索内容不能为空，请输入英文关键词
错误：关键词超出字数限制，请精简
高级检索

Fatigue Assessment of the Electro-mechanical Actuator for Individual Blade Control System Under Random Vibration

  • 期刊论文

  • 发表日期：

    2025年7月4日

查看全文
  • Young-Cheol Kim,
  • Dong-Hyeop Kim,
  • Sang-Woo Kim,
  • Seongpil Cho

摘要

Urban Air Mobility (UAM), designed for passenger and cargo transport in cities, is emerging as a next-generation transportation solution. However, structural components face risks from turbulence and vibrations unique to urban environments. Ensuring passenger safety and comfort requires rigorous structural integrity evaluations under random load conditions aligned with certification standards. This study presents analytical methods to evaluate the structural safety of eVTOL components under random vibrations, meeting airworthiness requirements. A conservative fatigue life assessment was performed using a 1% failure-probability S–N curve. Modal analysis identified key modes, applied in steady-state and random vibration analyses based on actuator responses and DO-160G standards. Results showed a safety margin above 2 (3 Sigma) and a fatigue life exceeding 107 cycles, confirming structural reliability. These methods provide a framework for airworthiness certification of eVTOL aircraft.