无人机机翼用复合材料的胶接与性能研究  

Study on Bonding and Properties of Composite Materials for UAV Wing

作　　者：胡江 苏菠 HU Jiang;SU Bo(Guangxi Police College,Nanning 530200,Guangxi,China)

机构地区：[1]广西警察学院,广西南宁530200

出　　处：《合成材料老化与应用》2023年第5期81-84,共4页Synthetic Materials Aging and Application

摘　　要：为了提升无人机机翼用碳纤维/铝复合材料的胶接强度,采用4因素5水平的正交试验法对超声振动胶接工艺参数进行了优化,并与传统未施加超声振动的胶接接头进行了对比。结果表明,超声振动胶接工艺中对胶接强度影响最大的是振动时间,其次为振动幅值,振动位置的影响最小;正交试验结果表明,碳纤维/铝胶接接头的最佳工艺参数为A3B5C3D5,即振动时间23 s、振动压力0.40 MPa、振动位置30 mm和振动幅值56μm,此时碳纤维/铝胶接接头胶接强度最大。相较于未施加超声振动的胶接接头,正交优化工艺下胶接接头的最大拉伸荷载平均值提高42.13%,胶接强度平均值提高41.59%。In order to improve the bonding strength of carbon fiber/aluminum composites for UAV wings,the orthogonal test method of four factors and five levels was used to optimize the ultrasonic vibration bonding process parameters,and compared with the traditional bonding joints without ultrasonic vibration.The results show that the order of infl uence on bonding strength in ultrasonic vibration bonding process is:vibration time>vibration amplitude>vibration pressure>vibration position;The orthogonal test results show that the optimum process parameters of carbon fiber/aluminum adhesive joint are A3B5C3D5,namely,vibration time 23 s,vibration pressure 0.40 MPa,vibration position 30 mm and vibration amplitude 56μm.At this time,the bonding strength of carbon fiber/aluminum adhesive joint is the largest.Compared with the bonded joint without ultrasonic vibration,the average value of the maximum tensile load and the average value of the bonding strength of the bonded joint under the orthogonal optimization process are increased by 42.13%and 41.59%respectively.

关 键 词：无人机机翼 碳纤维 正交试验法 胶接工艺 胶接强度 

分 类 号：TB33[一般工业技术—材料科学与工程]