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

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.