有间隙翼的模态试验和颤振分析  

Modal test and flutter analysis of wings with freeplay

作　　者：蒋雯霄 童轶男[1] 王成华[1] 杨永刚[1] 秦玉灵 孟强 Jiang Wenxiao;Tong Yinan;Wang Chenghua;Yang Yonggang;Qin Yuling;Meng Qiang(Beijing Institute of Space Long March Vehicle,Beijing 100076,China;Shanxi Jianghuai Heavy Industry Co.,Ltd.,Jincheng 048000,China)

机构地区：[1]北京航天长征飞行器研究所,北京100076 [2]山西江淮重工有限责任公司,晋城048000

出　　处：《战术导弹技术》2025年第1期53-59,共7页Tactical Missile Technology

摘　　要：针对轴承、摇臂等机构连接间隙对翼结构模态参数及颤振特性的影响,开展不同负载和不同翼偏角组合工况下的翼结构模态试验,获得模态频率随负载和翼偏角的变化规律。根据模态试验结果,修正有限元模型,并将分析所得模态参数作为颤振分析输入,用ZONA7统一升力面理论计算非定常气动力,建立颤振运动方程,采用P-K法进行翼结构各工况颤振分析,研究颤振频率和颤振动压随负载、频率差和翼偏角的变化规律。结果表明:间隙导致翼结构的模态参数表现出较强的非线性特性,进而影响颤振分析结果,所有试验工况的最大颤振动压是最小颤振动压的4倍。0°翼偏状态下,颤振频率随着固有频率的增加而增加,颤振动压随着一阶、二阶频率的频率差增加而增加。负载相同的情况下,颤振频率及颤振动压随翼偏角增加而降低。Aiming at the influence of bearing, rocker and other mechanism connection freeplay on the modal parameters and flutter characteristics of wing structure, the modal test is carried out under the combination of different loads and different wing deflections to obtain the change rule of modal frequency with load and wing deflection. According to the results of modal test, the finite element model is modified, and the modal parameters obtained from the analysis are used as inputs of the flutter analysis, and the non-stationary aerodynamic forces are calculated by using the theory of ZONA7 unified lifting surface. The flutter equations of motion are established, and the P-K method is adopted to carry out the flutter analysis of the wing structure under various working conditions for studying the variation rules of flutter frequency and flutter dynamic pressure with load, frequency difference and wing deflection angle. The results show that the modal parameters of the wing structure show strong nonlinear characteristics due to the freeplay, which affects the results of the flutter analysis, and the maximal flutter dynamic pressure of all the test conditions is 4 times of the minimal one. In the 0° wing deflection condition, the flutter frequency increases with the increase of natural frequency,and the flutter dynamic pressure increases with the increase of the frequency difference between the first-order and second-order frequencies. Under the same load condition, the flutter frequency and the flutter dynamic pressure will decrease with the increase of wing deflection angle.

关 键 词：间隙 翼结构 模态试验 负载 翼偏角 颤振动压 颤振频率 

分 类 号：TB332[一般工业技术—材料科学与工程]