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建立了某无人机用小型涡喷发动机主轴有限元模型,对该主轴进行有限元分析,得到该主轴的应力分布;采用蒙特卡洛与响应面相结合的方法,利用ANSYS软件,对该主轴进行可靠性分析,得到了不同概率下的主轴应力分布;这种方法可为发动机其它部件可靠性分析提供借鉴。
The finite element model of a small turbojet engine for a UAV is established. The stress distribution of the main shaft is obtained by finite element analysis. The Monte Carlo method is combined with the response surface. The ANSYS software is used to analyze the main axis. Reliability analysis of the spindle stress distribution under different probabilities; this method can provide reference for the reliability analysis of other components of the engine.