机翼碳纤维复合材料力学特性及振动性能分析  

Analysis of Mechanical Properties and Vibration Performance of Carbon Fiber Composite Materials for Wings

作　　者：曾光 梁兆威 李凯旋 刘元朋[1] ZENG Guang;LIANG Zhao-wei;LI Kai-xuan;LIU Yuan-peng(School of Mechanical Engineering,Zhengzhou University of Aeronautics,Zhengzhou Henan 450046,China)

机构地区：[1]郑州航空工业管理学院机械工程学院,河南郑州450046

出　　处：《计算机仿真》2025年第3期23-29,共7页Computer Simulation

基　　金：河南省科技攻关项目(222102240017,232102241030);河南省高等学校重点项目(23B460001);郑州航空工业管理学院实验室开放项目(ZHSK24-55)。

摘　　要：为了研究机翼碳纤维复合材料的力学特性及振动性能,以T-300碳纤维和铝合金分别作为机翼蒙皮和翼梁、翼肋、桁条结构材料,建立机翼三维模型;借助Simpson厚度积分规律完成蒙皮5层碳纤维铺层,在此基础上构建起机翼数值模型。基于机翼受载特性与强度理论,研究了机翼典型部位变形规律、力学特性、振动性能及谐响应频谱。研究结果表明,应力集中区域主要位于机翼后侧的桁条侧区域;机翼前侧发生屈曲变形风险较大,设计时应对机翼前侧进行加固;机翼在固有频率较高时发生变形概率较大,应尽可能避免在高频率下工作;此外机翼在4.79 Hz空间位移发生急剧变化,达到峰值,在此频率易产生共振,机翼工作时应当避免此频率。In order to study the mechanical properties and vibration performance of wing carbon fiber composites,this paper uses T-300 carbon fiber and aluminum alloy as wing skin,wing beam,wing rib and stringer structural materials to establish a three-dimensional model of the wing.Based on the Simpson thickness integral law,the five-layer carbon fiber layer of the skin is completed,and the numerical model of the wing is constructed.Based on the load characteristics and strength theory of the wing,the deformation law,mechanical properties,vibration performance and harmonic response spectrum of typical parts of the wing are studied.The results show that the stress concentration area is mainly located in the truss side area of the rear wing.The risk of buckling deformation on the front side of the wing is high,and the front side of the wing should be strengthened in design.The deformation probability of the wing is large when the natural frequency is high,and the wing should avoid working at high frequency as far as possible.In addition,the wing's spatial displacement changes sharply at 4.79 Hz,reaching the peak value.At this frequency,resonance is easy to occur,and this frequency should be avoided when the wing works.

关 键 词：碳纤维复合材料 机翼 结构设计 模态振动分析 谐响应分析 

分 类 号：V271.4[航空宇航科学与技术—飞行器设计]