直升机舱门不均匀分布气动载荷加载方法研究

ASYMMETRIC DISTRIBUTED AERODYNAMIN LOADS ON HELICOPTER DOOR

针对直升机舱门结构强度有限元力学分析中,不均匀分布气动载荷难以施加的问题,提出基于数学分析,采用最小二乘法,对直升机机身局部结构的气动压力点的压力值进行压力分布曲面拟合,快速得到所有有限元节点的压力值,并通过Patran分析软件前处理中的Field(域)功能实现对有限元节点快速加载。该方法对某型机舱门的不均匀分布气动载荷加载进行验证,结果表明该方法精度高,可快速实现不均匀分布载荷的施加,有效解决有限元仿真分析前处理中不均匀载荷的加载问题。

In order to solve the problem of asymmetric distributed aerodynamic loads on the helicopter door,a least squares method is used to fit the data of the existing pressure on the aerodynamic nodes of the helicopter door,and to calculate the pressure on the FEM nodes,by the use of the function of the patran field,to realize the quick loading on FEM nodes.This method is proved to be steady and reliable through the experiment of putting the asymmetric distributed aerodynamic load on the helicopter door.The asymmetric distributed aerodynamic loading on the surface can be implemented faster by using this method,and the FEM analysis with the asymmetric distributed load can be made effectively.