3D打印飞机颤振风洞试验模型设计与应用  

Design and Application of 3D Printed Aircraft Flutter Wind Tunnel Test Model

作　　者：胡家亮[1] 吴江鹏[1] 脱朝智[1] 张辉[1] 胡鑫[1] 沈恩楠 Hu Jialiang;Wu Jiangpeng;Tuo Chaozhi;Zhang Hui;Hu Xin;Shen En’nan(AVIC Shenyang Aircraft Design and Research Institute,Shenyang 110035,China)

机构地区：[1]航空工业沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《航空科学技术》2022年第9期43-50,共8页Aeronautical Science & Technology

摘　　要：颤振风洞试验是飞机气动弹性设计中的必要手段,随着先进飞机对气动弹性品质要求的不断提高,通过颤振风洞试验进行快速结构选参的需求更加迫切,为实现多样化的变参设计需求并压缩模型设计、制造周期,探索并发展了一种基于3D打印技术的低速颤振模型设计方法。针对某机翼变刚度低速颤振风洞试验要求,采用3D打印结构相似颤振模型方案,通过可拆卸蒙皮设计实现模型局部刚度可变,完成了模型结构设计、综合优化、制造和风洞试验,研究了机翼颤振耦合机理和局部刚度对颤振特性的影响,验证了3D打印颤振模型设计方法的可行性和有效性。Flutter wind tunnel test is a necessary technique in the aeroelasticity design of aircraft.With the increasing requirement of aeroelastic quality of advanced aircraft,it is more urgent to rapid structural parameter design by flutter wind tunnel test.In order to achieve the requirements for structural parameter design and simultaneously reduce the design and manufacturing period of flutter model,a low-speed flutter model design method based on 3D printing technology is explored and developed.According to the low-speed flutter wind tunnel test requirements of a wing variable stiffness,the 3D printed structural similarity flutter model scheme is adopted,and the local stiffness of the model is variable by removable local skin design.The structural design,integrated optimization,manufacture and wind tunnel test of the model are performed.Flutter coupling mechanism and the effects of local stiffness on flutter characteristic of the wing are studied.The feasibility and validity of the 3D printed flutter model design method are verified.

关 键 词：3D打印 颤振 模型设计 优化设计 风洞试验 低速风洞 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]