南京航空航天大学学报2025，Vol.57Issue(2)：252-258,7.DOI:10.16356/j.1005-2615.2025.02.005
基于响应面方法的直升机机身有限元模型参数修正
Parameter Updating of Helicopter Airframe Finite Element Model Based on Response Surface Method
朱尹 1韩东1
作者信息
- 1. 南京航空航天大学直升机动力全国重点实验室,南京 210016
- 折叠
摘要
Abstract
In order to reduce the deviation between the finite element model of helicopter airframe and the actual model,a helicopter airframe model updating method based on the response surface method is adopted,which uses a hypersurface function to approximately replace the actual and implicit complex function relationship,avoiding the traditional parameter updating method of calling the finite element program in each iteration.Meanwhile,the computational efficiency is improved by reducing the number of sample points through Latin hypercube sampling.Taking the 10%scaled down helicopter fuselage model as an example,the first six natural frequencies of its actual model and the finite element model are obtained through experiments and finite element analysis.The design parameters are determined by sensitivity analysis and the response surface method is used to update the parameters of the fuselage model.The average error of the natural frequencies between the predicted results of the finite element model and the experimental test results is reduced from 3.54%to 1.03%,effectively improving the prediction accuracy of the finite element model.The revised results show that the finite element model updating method based on the response surface method can be well applied to the parameter updating of helicopter airframe model.关键词
直升机机身/模型修正/响应面方法/灵敏度分析/有限元分析/拉丁超立方采样Key words
helicopter airframe/model updating/response surface method/sensitivity analysis/finite element analysis/Latin hypercube sampling分类
航空航天引用本文复制引用
朱尹,韩东..基于响应面方法的直升机机身有限元模型参数修正[J].南京航空航天大学学报,2025,57(2):252-258,7.
