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

作　　者：朱尹 韩东[1] ZHU Yin;HAN Dong(National Key Laboratory of Helicopter Aeromechanics,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机动力全国重点实验室,南京210016

出　　处：《南京航空航天大学学报(自然科学版)》2025年第2期252-258,共7页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：为降低直升机机身的有限元模型与实际模型之间的偏差,采用了一种基于响应面法的直升机机身模型修正方法。该方法使用一个超曲面函数来近似地替代实际的、隐式的复杂函数关系,避免了传统参数修正方法每次迭代时都调用有限元程序的步骤。同时,通过拉丁超立方采样减少样本点数量从而提高了计算效率。以直升机10%缩比机身模型为例,通过试验与有限元分析分别获得其实际模型与有限元模型的前六阶固有频率,通过灵敏度分析确定了设计参数,利用响应面方法对该机身模型进行了参数修正。机身的有限元模型预测结果与试验测试结果之间的固有频率平均误差由3.54%降低至1.03%,有限元模型的预测精度显著提升。修正结果表明,基于响应面方法的有限元模型修正方法能够有效地应用于直升机机身模型参数修正。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 

分 类 号：V214.1[航空宇航科学与技术—航空宇航推进理论与工程]