C/SiC與TC4層合結(jié)構(gòu)的斜侵徹破壞行為和機理
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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- 纖維復(fù)合材料
- 2025年02期
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