弹性全模突风动载荷风洞试验技术研究  

Study on gust wind tunnel test for a full elastic aircraft model

作　　者：赵冬强 杨智春[2] 于金革 曾宪昂 黄国宁 ZHAO Dong-qiang;YANG Zhi-chun;YU Jin-ge;ZENG Xian-ang;HUANG Guo-ning(The First Aircraft Institute of AVIC,Xi’an 710089,China;School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;AVIC Aerodynamics Research Institute,Harbin 150001,China)

机构地区：[1]航空工业第一飞机设计研究院,陕西西安710089 [2]西北工业大学航空学院,陕西西安710072 [3]航空工业空气动力研究院,黑龙江哈尔滨150001

出　　处：《振动工程学报》2024年第10期1775-1782,共8页Journal of Vibration Engineering

基　　金：国家自然科学基金资助项目(11972296);工信部民机专项(MJ-2017-F-08)。

摘　　要：目前,欧美等世界主要航空大国已经具备较为成熟的突风风洞试验技术,但中国突风风洞试验技术相对落后,特别是缺少大型风洞全机级突风试验装置和相关技术。本文研制了突风发生器、五自由度支撑系统和全机弹性模型,并进行了全机模型突风动载荷风洞试验验证。试验结果表明:突风流场稳定,叶片两端与风洞中心位置突风速度偏差小于25%;全机支撑系统支持刚度小而稳定性好,能够满足突风动载荷试验模型悬挂要求;采用非均匀突风场仿真计算结果与风洞试验实测结果接近,翼根弯矩误差小于15%,翼尖过载绝对值误差小于0.2g。At present,the big aviation countries already have mature gust wind tunnel test technology,but which is relatively backward in China,especially the gust wind tunnel tests equipment and technology of full aircraft model are lack.In this paper,a gust generator,a five-degree-of-freedom suspension system and a full elastic aircraft model are developed,and the wind tunnel tests of the whole model are carried out.The test results show that the gust field is stable,and the deviation of the gust velocity between the two ends and the center of the wind tunnel is less than 25%.The support stiffness of the model suspension system is small and the stability is good,which can meet the requirements of the gust wind tunnel test.The simulation results of the non-uniform gust field are close to those of the wind tunnel test,and the error of the moment of the wing root is less than 15%,and the error of wing tip overload is less than 0.2g.

关 键 词：风洞试验 突风发生器 悬挂系统 弹性全模 突风动载荷 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]