典型大开口结构加筋壁板成型控制及固化变形特征

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Formation control and curing deformation characteristics of stiffened panels with large openings

RENXueming*，LIANGRuilin，SI Bowen （AVIC Xi'an Aircraft Industry Group Company Ltd.，Xi'an 710089）

Abstract：This paperinvestigates thechallenges ofcontrolingformingqualityandcuringdeformationin the manufacturing of stiffenedcarbonfibercompositeaircraftpanelswithlargeopenings.Thetestarticle，madeofT8O-gradecarbonfibermaterial，wasfabricatedusing co-bonding processwith“drystifenersandwetskin”.Aco-cured patchedreinforcementand a steppedrecess structure wereadoptedattheelipticalopeningarea.Tocontroldeformationand ensurequality，aninovative hollowcoremold withareinforced flange structurewas employed.Thisdesigneffectivelyaddressdtheissueofslow heatingrateandtemperatureinhomogeneityinthethickenedreinforcementarea，therebyreducingthecuring-inducedinternal stress.Afiniteelement modelforpredictingcuringdeformationwas establishedusing Abaqussoftware，andthesimulationresults showed goodagreementwithlaserscanning measurements，validating themodel'saccuracy.Theresultsdemonstrate that theproposed hollowcore mold strategy efectivelycontrolledthe panel'scuring deformation withinanenginering acceptablerange（maximum deformationapproximately3.1mm）.Meanwhile，thenet-size forming methodasisted by the core mold successullyensured theformingqualityof the polygonal steppedopening without any delamination.Finaly，，a draft angle of no less than 10∘ is recommended for such structures to mitigate demolding risks.This study provides a reliable process solution and theoretical basis for manufacturing similar large-opening composite structures.

Keywords：compositematerials;stifened panel; large opening;co-bonding;curing deformation;tolingdesign;finiteelement analysis （FEA）

1引言

碳纤维复合材料应用于飞机结构上可提高飞机的结构效率，降低结构重量，提升燃油经济性。（剩余4929字）