关键词：强迫定位装夹；装配内应力；装配损伤；形性耦合分析；协同调控中图分类号：V262DOI：10.3969/j.issn.1004-132X.2025.04.002 开放科学（资源服务）标识码（OSID）：

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

GUO Feiyan1ZHANG Yongliang²LIU Jialiang1*ZHANG Hui² 1.School of Mechanical Engineering，University of Science and Technology Beijing，Beijing，100083 2.AVIC Shenyang Aircraft Industrial（Group） Co.，Ltd.，Shenyang，110850

Abstract： The large-size 8. 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 forceamp; 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 stressamp;damage. Then the active control of shape amp; force coupling and macro 8. 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.

Key words： forced positioning amp; clamping;assembly internal stress;assembly damage;shape amp; force coupling analysis;collaborative adjustment amp; control

0 引言

碳纤维增强树脂基复合材料（carbonfiberreinforcedplastic，CFRP）具有密度小、比强度高、耐冲击性强、耐磨耐腐蚀性好等特点[1]，符合航空新型号对结构服役力学性能的要求，例如结构强度与疲劳等指标。随着复合材料（简称“复材\"成形、加工与装配技术的发展，碳纤维增强树脂基复材在航空上的应用逐渐由整流罩、舱口等小型非承力构件过渡到翼肋、机身等大型主承力结构中[2]。复材的使用比例已成为衡量飞机是否先进的重要指标：如美国F-22和F-35等五代机使用的复材分别占自身质量的 26% 和 36% ，国内主力机型歼-20的复材使用比例达到 30% 左右[3]。呈现出大型化、整体化特点的新一代复材构件的自身成形精度较低（厚向尺寸的 5%～ 8% ），大尺寸薄板件的面内翘曲变形可达到毫米级，在装配作业过程中，容易出现型面几何外形超差以及配合间隙不均匀等现象，对机体结构的气动外形影响较大。在装配现场，为保证复材薄壁构件装配作业过程的顺利进行，通常采用强迫定位装夹、强迫校形等方式，即通过施加额外的定位装夹力来保障关键特性点的正确空间位姿以及控制装配变形和损伤状态。

本文首先解析了强迫定位装夹原理，阐述了强迫定位装夹对复材薄壁构件几何与力学装配性能的影响，并从装夹工艺参数、工装力-位柔性装调方面出发，分析强迫定位装夹性能的系统性保障策略及存在的问题，提出并解析所涉及的装夹力限值设定、几何间隙消减、物理装配性能演化预测与测量、工艺参数反求等关键技术，最后指出下一步研究重点。……