基于载荷-位移协同控制的机翼风洞模型随动加载单元设计  

Development of the fellow-up loading element of the wing wind tunnel model based on load-displacement cooperative control

作　　者：张凯航 曲文智 池鸿刚 杨睿[1] 孙士勇[1] Zhang Kaihang;Qu Wenzhi;Chi Honggang;Yang Rui;Sun Shiyong(College of Mechanical Engineering,Dalian University of Technology,Liaoning Dalian,116024,China)

机构地区：[1]大连理工大学机械工程学院,辽宁大连116024

出　　处：《机械设计与制造工程》2025年第3期84-89,共6页Machine Design and Manufacturing Engineering

基　　金：中央高校基本科研业务费专项资金(DUT21GF405);国家重点研发计划(2020YFB1506704)。

摘　　要：对机翼风洞模型进行静强度试验,可以防止模型在风洞试验时发生破坏造成巨大经济损失。基于机翼模型大变形特征设计了一种新型随动加载装置,采用载荷-位移协同控制方法进行精准加载,保证模型发生大变形时翼面加载点受力方向始终垂直于模型表面,通过机构-结构联合仿真和相关试验对加载单元原理与控制方法进行了验证。结果表明,该加载单元原理正确,控制方法能够满足加载载荷的准确性、稳定性和方向的跟随性,高效可行,为机翼风洞模型的静强度试验提供了一套合理可行的方法。The static strength test of the wing wind tunnel model can prevent the damage of the model during the wind tunnel test from causing huge economic losses.Based on the large deformation characteristics of the wing model,a new type of follow-up loading device is designed.The load-displacement collaborative control method is used to accurately load,ensuring that the force direction of the loading point on the wing surface is always perpendicular to the model surface when the model had large deformation.The principle and control method of the loading element are verified by the mechanism-structure joint simulation and related tests.The results show that the principle of the loading element is correct,and the control method can meet the accuracy,stability and direction of the loading load,which is efficient and feasible.It provides a reasonable and feasible method for the static strength test of the wing wind tunnel model.

关 键 词：风洞模型 强度试验 大变形 随动加载 协同控制 机构-结构联合仿真 

分 类 号：TH113.2[机械工程—机械设计及理论] V216.11[航空宇航科学与技术—航空宇航推进理论与工程]