强迫定位装夹对航空复合材料构件几何-物理装配性能的影响与协同保障  

Effects of Forced Positioning&Clamping on Geometric and Physical Assembly Performances for Composite Structures and Collaborative Guarantee Strategies

作　　者：郭飞燕 张永亮[2] 刘嘉良 张辉[2] GUO Feiyan;ZHANG Yongliang;LIU Jialiang;ZHANG Hui(School of Mechanical Engineering,University of Science and Technology Beijing,Beijing,100083;AVIC Shenyang Aircraft Industrial(Group)Co.,Ltd.,Shenyang,110850)

机构地区：[1]北京科技大学机械工程学院,北京100083 [2]沈阳飞机工业(集团)有限公司,沈阳110850

出　　处：《中国机械工程》2025年第4期655-670,共16页China Mechanical Engineering

基　　金：国家自然科学基金(52175450);国防基础科研项目(JCKY2023205B006)。

摘　　要：航空用复合材料大尺寸薄壁构件自身成形精度较低、面内翘曲变形大,装配误差累积易在配合连接部位出现不期望的几何间隙与外形超差,在工程中通常采取施加局部装夹力的强迫方式予以被动消减,但此种方法会引发不均衡的装配内应力分布甚至内部损伤等质量问题,直接影响装配结构的飞行服役性能。首先阐述强迫定位装夹原理,解析强迫定位装夹对复合材料弱刚性薄壁件装配几何精度与内应力/损伤等物理性能的影响规律;然后,从分析装配前的强迫装夹工艺参数优化、装配中的工装柔性定位力-位调整两方面出发,解析强迫装配力限值设定、几何间隙消减、应力/损伤演化预测、装夹工艺参数优化反求、应力/损伤精准测量等关键技术及其具体实现步骤方法,以实现强迫定位装夹过程中装配变形、内应力和损伤状态等形性指标的耦合分析、主动控制与协同保障;最后,从实际工程应用的角度出发,提出面向复合材料构件高质高效与低成本装配目标的下一步工作重点。The large-size&thin-walled aviation composite structures had low forming accuracy and huge in-plane warping deformation.The accumulation of assembly errors,unexpected geometric gaps and shape deviations were prone to occur at the joining areas.In engineering,passive reduction actions,such as applying local clamping forces was usually applied,but uneven internal stress distribution and even internal damages would be occurred,which affected the mechanical performances of the structures in service directly.Firstly,the principle of forced positioning clamping was explained,and the affection on geometric accuracy and mechanical properties of weak rigid composite parts was analyzed.Secondly,starting from the analysis of two main aspects,i.e.optimization on forced clamping process parameters before assembly,and flexible positioning force&position adjustment of fixtures during assembly,five key technologies were solved with detailed technical solutions,i.e.setting forced assembly force limits,reduction of geometric gaps,prediction of stress/damage evolution,reverse optimization of forced clamping process parameters,and precise measurement of assembly stress&damage.Then the active control of shape&force coupling and macro&micro collaborative guarantee in the clamping processes for assembly performance,could be achieved.Finally,for the composite assembly structures,from the perspective of practical engineering applications,the future working focus towards high assembly quality and efficient,and low-cost assembly goals were proposed.

关 键 词：强迫定位装夹 装配内应力 装配损伤 形性耦合分析 协同调控 

分 类 号：V262[航空宇航科学与技术—航空宇航制造工程]