°</sup> \~60<sup>°</sup> )該結(jié)構(gòu)的試驗和數(shù)值仿真研究。構(gòu)建了包含微孔洞、SiC 基體、橫向/縱向纖維束的C/SiC復(fù)合材料細觀模型,并利用哈希準(zhǔn)則對復(fù)合材料進行損傷判定。侵徹過程中,C/SiC對沖擊波的強烈衰減作用導(dǎo)致靶板背面未出現(xiàn)層裂,C/SiC前板中部出現(xiàn)分層和纖維斷裂并形成向背面傾斜擴展的裂紋,彈丸與TC4后板接觸后該板才出現(xiàn)顯著彎曲變形繼而被擊穿。該層合結(jié)構(gòu)的侵徹破壞模式包括:纖維束斷裂、微孔洞塌陷、復(fù)合材料內(nèi)部分層、C/SiC與TC4界面分層。隨著侵徹速度的增大,剪應(yīng)力的增加導(dǎo)致C/SiC復(fù)合材料的破壞模式從分層向纖維剪切斷裂轉(zhuǎn)變,斜裂紋的傾角增加,擴展距離增長。隨著侵徹傾角的增大,彈丸面外方向的速度分量降低,TC4后板的彎曲變形量減少,C/SiC與TC4界面分層裂紋的起裂時刻延遲,但分層面積增加。-龍源期刊網(wǎng)" />

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C/SiC與TC4層合結(jié)構(gòu)的斜侵徹破壞行為和機理

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Oblique penetration failure behavior and mechanisms of C/SiC and TC4 layered structures

CHENG Ran,LI Tao,ZHU Zhiwu * (School of Mechanics and Aerospace Engineering, Southwest Jiaotong University, Sichuan Province Key Laboratory of Advanced Structural Materials Mechanical Behavior and Service Safety,Chengdu 611756)

Abstract:Toinvestigatethemesostructural response,failure modes,and failure mechanismsof thelayered structurecomposed of composite material (C/SiC)and titanium aloy(TC4)during oblique penetration,aswell as theirdependenceon penetration velocityandobliquity,experimentaland numerical studies wereconductedontheoblique penetrationof spherical projectiles into this structure at velocities ranging from 35O to 550 m/sand obliquity angles between 30° and 60° . Amesoscopicmodel ofthe C/SiCcompositewas developed,incorporating microvoids,a SiC matrix,and transverse/longitudinal fiber bundles.The Hashin criterion was employed to assess damage in thecomposite material.During penetration,the strong attenuation efectofC/SiConshock waves prevented spalltiononthebackofthe target.DelaminationandfiberfractureoccurredinthecentralregionoftheC/SiCfrontplate,formingcracksthatpropagatedobliquelytowardtherear.SignificantbendingdeformationoftheTC4rearplateonlyoccurreduponcontact with the projectile,eventuallyleading toperforation.Thepenetrationfailure modesofthislayered structureincludefiberbundlefracture,microvoidcolapse,internal delamination ofthecomposite,andinterfacedelaminationbetween C/SiCandTC4.Asthepenetrationvelocityincreases,the riseinshearstresscausesthefailuremodeoftheC/SiCcompositetoshiftfromdelaminationtofibershearfracture,withan increase in the inclinationangleand propagationdistance of obliquecracks.Asthe penetration obliquity increases,theout -of-plane velocitycomponent of the projectile decreases,reducing the bending deformation of the TC4 rear plate.Meanwhile,theinitiationof interfacedelaminationbetween C/SiCandTC4isdelayed,butthedelaminationareaincreases. Keywords: C/SiC and TC4 layered structure;oblique penetration;failure mode;failure mechanisms

1引言

超高速飛行器在高馬赫數(shù)飛行時,氣動熱導(dǎo)致其局部表面達到 1000‰ 以上的高溫,這些局部高溫區(qū)域通常采用耐高溫表面層(C/SiC、C/C、SiC/SiC 等)和金屬底襯層(鈦合金、鎳基合金等)的層合結(jié)構(gòu)[1-2]。(剩余15838字)

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