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
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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 Positioning& 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 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 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 & clamping;assembly internal stress;assembly damage;shape & force coupling analysis;collaborative adjustment & 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。（剩余35807字）