基于灵敏度分析的直升机旋翼桨叶模型修正方法  

Helicopter rotor blade model updating method based on sensitivity analysis

作　　者：苏子献 韩东[1] 崔钊 SU Zixian;HAN Dong;CUI Zhao(National Key Laboratory of Helicopter Aeromechanics,College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Aircraft Flight Test Technology Institute,Chinese Flight Test Establishment,Xi’an 710089,China)

机构地区：[1]南京航空航天大学航空学院直升机动力学全国重点实验室,南京210016 [2]中国飞行试验研究院飞机所,西安710089

出　　处：《航空动力学报》2024年第11期111-118,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(11972181);江苏高校优势学科建设工程资助项目(PAPD)。

摘　　要：为缩减直升机旋翼桨叶结构有限元模型与实际模型之间模态响应结果之间的偏差,采用一种基于灵敏度分析的模型修正方法,由于传统的灵敏度方法未考虑设计参数变化对灵敏度计算结果的影响,以及出现量化不统一等问题,针对直升机旋翼桨叶模型对该方法进行适当的改进。以碳纤维复合材料直升机旋翼模型桨叶为例,通过试验与有限元分析分别得到其实际模型与有限元分析模型的前6阶模态的固有频率,利用灵敏度方法对桨叶有限元模型的主要设计参数进行优化,使旋翼有限元模型与实际模型间固有频率的平均误差由8.15%降低至1%以内,误差有了明显的降低、精度有明显的提升。修正结果表明,基于灵敏度分析的模型修正方法能够有效提升直升机桨叶结构模型的精度。In order to reduce the deviation between the modal response results of the finite element model and the actual model of the helicopter rotor blade structure,a model updating method based on sensitivity analysis was used.In view of traditional sensitivity method without consideration of the influence of the change of design parameters on the sensitivity calculation results,as well as the problem of non-uniform quantification,the method was appropriately improved for the helicopter rotor blade model.Taking the carbon fiber composite helicopter rotor blade model as an example,the natural frequencies of the first six modes of the actual model and the finite element analysis model were obtained through experiments and finite element analysis,respectively,and the main design parameters of the finite element model of the rotor blade were optimized by using the sensitivity method.The average error between the rotor blade finite element model and the actual model was reduced from 8.15%to less than 1%.The error was significantly reduced and the accuracy was significantly improved.The updating results showed that the model updating method based on sensitivity analysis can effectively improve the accuracy of the helicopter propeller structure model.

关 键 词：模型修正 灵敏度分析 旋翼桨叶 有限元模型 实际模型 固有频率 

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]