強迫定位裝夾對航空復合材料構(gòu)件幾何-物理裝配性能的影響與協(xié)同保障

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關(guān)鍵詞：強迫定位裝夾；裝配內(nèi)應(yīng)力；裝配損傷；形性耦合分析；協(xié)同調(diào)控中圖分類號：V262DOI：10.3969/j.issn.1004-132X.2025.04.002 開放科學（資源服務(wù)）標識碼（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

碳纖維增強樹脂基復合材料（carbonfiberreinforcedplastic，CFRP）具有密度小、比強度高、耐沖擊性強、耐磨耐腐蝕性好等特點[1]，符合航空新型號對結(jié)構(gòu)服役力學性能的要求，例如結(jié)構(gòu)強度與疲勞等指標。（剩余35807字）