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不同壓剪比下復(fù)合材料加筋壁板屈曲行為及承載能力試驗(yàn)研究

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關(guān)鍵詞:復(fù)合材料加筋壁板;復(fù)合載荷;壓剪比;屈曲;承載能力中圖分類(lèi)號(hào): 文獻(xiàn)標(biāo)志碼:A 文章編號(hào):2095-2945(2025)14-0084-04

Abstract:Aimedatthestabilitydesign challngesof compositestiffnedpanelsundercombinedcompressive-shearloading, this paper investigated the mechanism by which the axial-shear stress ratio( R= compressive load/shear load) regulates buckling behaviorthroughexperimentalstudies.Aself-developedflatpanelaxial-sheartesting devicewasused,whilstagradient experimentalmatrixwithsixaxial-shearstressratioconditionswasestablished.Theenvelopecurvesofcompressiveandshear buckling loads were mapped,,and failure test on the specimen under a loading condition with R=2 was conducted.The experimentalresultsrevealthattheriticalcompresivebucklingloadincreaseswithhigheraxial-shearratios,whilethecritical shearbuckling load decreases with increasing R .An exponential function model based onthe natural logarithm achieves good predictionaccuracyfortheloadenvelopecurves.Specimenfalureprimarilyresultedfromlarge-areadebondingbetweentheskin andstffeners,withpost-bucklingload-caryingcapacityreaching1.45timesthebucklingload.Thisstudyprovidesvaluable references for the design of primary load-bearing composite structures.

Keywords: composite stiffned panel; combined loading; axial-to-shear ratio; buckling; carrying capacity

復(fù)合材料加筋壁板結(jié)構(gòu)通常由薄壁面板與規(guī)則排列的加強(qiáng)筋構(gòu)成,因其輕量化、高比強(qiáng)度及抗疲勞性能等優(yōu)勢(shì),成為飛行器機(jī)身、機(jī)翼等關(guān)鍵承載部件的常見(jiàn)結(jié)構(gòu)形式。(剩余6402字)

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