民用客机大型复合材料蜂窝夹芯尾缘胶接技术研究

Studying on the Adhesion Technology of Large Honeycomb Sandwich Trailing Edge of Composite Part for Civil Aircraft

本论文以民用大型复合材料尾缘为研究对象,创新研制双曲面蜂窝数控切削及检测一体化工装,确保加工与检测基准的一致性,提高了蜂窝检测的可靠性;研制的蜂窝芯实现表面平整度在±1.25mm内;蜂窝芯分段处阶差≤0.15mm;蜂窝零件装配型面精度±0.15mm。开展次级零件及胶接组件复合材料工装热分布分析,合理选取固化参数;首次采用楔形活块工装设计,对窄腔薄壁复合材料蒙皮变形进行补偿,实现窄腔薄壁蒙皮高质量成型。成型蒙皮的外形尺寸轮廓度为0.2,薄壁窄腔蒙皮窄腔处U型位置厚度公差≤±2%;成型后薄壁窄腔蒙皮孔隙率≤1%;民用客机大型复合材料尾缘的成功研制,对于推进复合材料胶接技术水平,推动复杂大型复合材料整体构件的应用意义重大。

Research on the civilian large composite trailing edge,the hyperboloid honeycomb CNC cutting and detection integration tool was creatively developed,the machining and testing datum consistency was ensured,the reliability of honeycomb detection was improved.The surface flatness of the finished cell could achieved within±1.25 mm,the step difference between section was less than or equal to 0.15 mm,and its assembly profile precision was 0.15 mm.The thermal profile of secondary parts and adhesion component composites were analyzed,selecting reasonably curing parameters.The deformation of thin-walled composite skin was compensated with designing the wedge free piece of equipment.The high quality narrow skin was get.The dimension of finished skin was 0.2,the U thickness tolerance of flanging position was less than or equal to 2%,the porosity was less than or equal to 1%.The successful development of the trailing edge of composite material for civil aircraft was a great significance to the promotion of the technical level of composite bonding and the application of complex and large composite integral components.