飞机舵机作动器局部应力与疲劳寿命分析  

Local stress and fatigue lifetime analysis of aircraft rudder actuator

作　　者：陈勇[1] 马阅军 夏立群[2] 尹子栋[2] 张伟[2] 熊峻江[1] 

机构地区：[1]北京航空航天大学交通科学与工程学院,北京100191 [2]西安飞行自动控制研究所,西安710065

出　　处：《强度与环境》2014年第1期57-64,共8页Structure & Environment Engineering

基　　金：国家自然科学基金(51075019);航空科学基金(20095251024)资助项目

摘　　要：通过有限元分析软件ANSYS Workbench对飞机舵机作动器进行了力学分析建模,通过引入非线性接触设置模拟了作动器筒体的实际工作的接触效应,分析了结构在复杂工作状态下的局部应力分布,并且根据第四强度理论校核了结构的静强度设计;然后,在静力分析的基础上,根据第一强度理论确定结构的疲劳危险点,并结合名义应力法和线性累积损伤理论估算了结构在设计疲劳谱下的疲劳寿命。本文的分析流程可以给工程设计单位在处理类似复杂航空结构的静强度与安全寿命设计问题方面提供参考。Mechanical Analysis modeling is applied in this paper to analyze the aircraft rudder actuator by means of finite element analysis software ANSYS Workbench. Actual work loads and constrain conditions of Actuator Cylinder are exactly simulated through introduction of nonlinear contact pairs, and accurate analysis of the Actuator Cylinder structure is performed under the complicated work condition to obtain local stress distribution. Meanwhile we have checked static intensity on the basis of Fourth Strength Theory. Then based on static analysis we find fatigue danger point according to First Strength Theory. At last, fatigue life of the structure under designed fatigue spectrum is estimated by adopting Nominal Stress Method and Miner Theory. The analysis process of this paper provides some theoretic reference value aboutstatic strength and safety life design related to similar complex aircraft structure for engineering design academy.

关 键 词：有限元分析 方向舵作动器 局部应力 名义应力法 Miner理论 疲劳寿命 

分 类 号：V215.52[航空宇航科学与技术—航空宇航推进理论与工程]