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Finite element analysis of helicopter main rotor hub plates to evaluate the possibility of increasing the time to retirement.

机译：直升机主旋翼毂板的有限元分析，以评估增加退役时间的可能性。

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摘要

Rotorcraft main rotor systems have multiple components that are subject to very high loads and moments. These loads and moments dictate the life expectancy of the parts based upon the components material of composition. This project will focus on the upper and lower hub plates on the main rotor system of a typical four bladed commercial helicopter. The upper and lower plates are machined from 7075-T73 aluminum forgings. The upper and lower plates were laboratory fatigue tested during product development as supporting parts in the test of the main rotor assembly. With recent advances in finite element analysis, there are situations were a computer generated three dimensional model analysis would be more economical and time beneficial to determine if the life expectancy of a part can be increased above the published safe life component retirement time. The applied loads are measured flight loads under maximum peak conditions and also ground-air-ground cycle loads. The stress values obtained from the loads are plotted on a Soderberg diagram and evaluated to determine if the retirement time of the part can be increased above the current value based on the steady and oscillatory stresses encountered.
机译：旋翼飞机的主旋翼系统具有多个组件，这些组件会承受很高的负载和力矩。这些载荷和力矩根据组成材料决定了零件的预期寿命。该项目将集中于典型的四叶片商用直升机主旋翼系统的上下轮毂板。上板和下板由7075-T73铝锻件加工而成。上板和下板在产品开发过程中经过实验室疲劳测试，作为主旋翼组件测试中的支撑部件。随着有限元分析的最新进展，存在一种情况，即计算机生成的三维模型分析将更经济，并且时间更有利于确定零件的预期寿命是否可以增加到已公布的安全寿命组件退役时间以上。施加的载荷是在最大峰值条件下测得的飞行载荷以及地空对地循环载荷。从载荷获得的应力值绘制在Soderberg图上，并进行评估，以基于遇到的稳态和​​振荡应力确定零件的退役时间是否可以增加到当前值以上。

著录项

  • 作者

    Wittig, Douglas.;

  • 作者单位

    The University of Texas at Arlington.;

  • 授予单位 The University of Texas at Arlington.;
  • 学科 Engineering Aerospace.;Engineering Mechanical.
  • 学位 M.S.
  • 年度 2008
  • 页码 65 p.
  • 总页数 65
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 航空、航天技术的研究与探索;机械、仪表工业;
  • 关键词

  • 入库时间 2022-08-17 11:39:06

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