The non-linear behavior of continuous fiber reinforced C/SiC ceramic matrix composites(CMCs)under tensile loading is modeled by three-dimensional representative volume element(RVE)models of the composite. The theoreti...The non-linear behavior of continuous fiber reinforced C/SiC ceramic matrix composites(CMCs)under tensile loading is modeled by three-dimensional representative volume element(RVE)models of the composite. The theoretical background of the multi-scale approach solved by the finite element method(FEM)is recalled firstly.Then the geometric characters of three kinds of damage mechanisms,i.e.micro matrix cracks,fiber/matrix interface debonding and fiber fracture,are studied.Three kinds of RVE are proposed to model the microstructure of C/SiC with above damage mechanisms respectively.The matrix cracking is modeled by critical matrix strain energy(CMSE)principle while a maximum shear stress criterion is used for modeling fiber/matrix interface debonding. The behavior of fiber fracture is modeled by the famous Weibull statistic theory.A numerical example of continuous fiber reinforced C/SiC composite under tensile loading is performed.The results show that the stress/strain curve predicted by the developed model agrees with experimental data.展开更多
Advanced propulsion systems experience critical challenges under extreme service conditions,including aerodynamic loads and thermal loads.Especially,flutter stability is a key bottleneck restricting the design and saf...Advanced propulsion systems experience critical challenges under extreme service conditions,including aerodynamic loads and thermal loads.Especially,flutter stability is a key bottleneck restricting the design and safe op⁃eration of hot structures in advanced propulsion systems employing ceramic matrix composites(CMCs).Compared to traditional nickel-based alloys,CMCs offer superior high-temperature resistance and specific strength,making them ideal for next-generation engine hot structures.The inherent anisotropy,heterogeneity,and complex nonlinear behav⁃ior of CMCs,coupled with extreme operating environments,result in strong multi-physics interactions,including aero-thermo-structural,thermo-mechanical,and damage-aeroelastic coupling.These complexities significantly com⁃plicate vibration stability and flutter analysis.The recent research progresses on these problems are systematically ex⁃amined,focusing on multi-field coupling mechanisms,material constitutive and damage evolution models,multi-scale modeling methods,coupled solution strategies,and the influence of key parameters on flutter characteristics.The current challenges are highlighted,including the complexity of high-temperature nonlinear modeling,the effi⁃ciency of multi-field coupling calculations,and the multi-scale modeling of complex weaving structures.Finally,an outlook on future development directions is presented to provide theoretical support for the design and safety assess⁃ment of hot structures of advanced CMCs.展开更多
A novel approach of decorating graphene surface with graphene quantum dots(abbreviated as GQDs@Gr)was presented to achieve superior tribological properties in Gr/Cu composites.The prepared GQDs@Gr hybrid reinforcement...A novel approach of decorating graphene surface with graphene quantum dots(abbreviated as GQDs@Gr)was presented to achieve superior tribological properties in Gr/Cu composites.The prepared GQDs@Gr hybrid reinforcement possessed superior dispersion and had achieved strong interface bonding with Cu matrix.GQDs@Gr/Cu composite showed a good combination of wear resistance and electrical conductivity due to the synergistic effect of GQDs and Gr.Specifically,the coefficient of friction(COF)was reduced to 0.3,the wear rate(WR)was 2.13×10^(-5) mm^(3)·N^(−1)·m^(−1)(only a quarter of pure copper),and maintained the electrical conductivity of 96.5%IACS(international annealed copper standard).As a result,delamination,fracture,and plow furrows on the wear surface of Gr/Cu composite indicate that fatigue and abrasive adhesive wear are the main wear mechanisms.Wear surface lubrication film and strong interface bonding ensure better comprehensive performance of GQDs@Gr/Cu composite.展开更多
基金Supported by the National Natural Science Foundation of China(51075204,51105195)the Aeronau-tical Science Foundation of China(2011ZB52024)
文摘The non-linear behavior of continuous fiber reinforced C/SiC ceramic matrix composites(CMCs)under tensile loading is modeled by three-dimensional representative volume element(RVE)models of the composite. The theoretical background of the multi-scale approach solved by the finite element method(FEM)is recalled firstly.Then the geometric characters of three kinds of damage mechanisms,i.e.micro matrix cracks,fiber/matrix interface debonding and fiber fracture,are studied.Three kinds of RVE are proposed to model the microstructure of C/SiC with above damage mechanisms respectively.The matrix cracking is modeled by critical matrix strain energy(CMSE)principle while a maximum shear stress criterion is used for modeling fiber/matrix interface debonding. The behavior of fiber fracture is modeled by the famous Weibull statistic theory.A numerical example of continuous fiber reinforced C/SiC composite under tensile loading is performed.The results show that the stress/strain curve predicted by the developed model agrees with experimental data.
基金supported by the Na⁃tional Science and Technology Major Project(No.Y2019-Ⅰ⁃0018-0017)the National Natural Science Foundation of China(No.U24A2051)+2 种基金the Natural Science Foundation of Jiangsu Province(No.BK20232037)the Foundation of Key Laboratory of Aero-engine Thermal Environment and Structure,Ministry of Industry and Information Technology(No.CEPE2024002)the Postgraduate Research&Practice Innovation Program of Jiangsu Province(No.KY⁃CX24_0605)。
文摘Advanced propulsion systems experience critical challenges under extreme service conditions,including aerodynamic loads and thermal loads.Especially,flutter stability is a key bottleneck restricting the design and safe op⁃eration of hot structures in advanced propulsion systems employing ceramic matrix composites(CMCs).Compared to traditional nickel-based alloys,CMCs offer superior high-temperature resistance and specific strength,making them ideal for next-generation engine hot structures.The inherent anisotropy,heterogeneity,and complex nonlinear behav⁃ior of CMCs,coupled with extreme operating environments,result in strong multi-physics interactions,including aero-thermo-structural,thermo-mechanical,and damage-aeroelastic coupling.These complexities significantly com⁃plicate vibration stability and flutter analysis.The recent research progresses on these problems are systematically ex⁃amined,focusing on multi-field coupling mechanisms,material constitutive and damage evolution models,multi-scale modeling methods,coupled solution strategies,and the influence of key parameters on flutter characteristics.The current challenges are highlighted,including the complexity of high-temperature nonlinear modeling,the effi⁃ciency of multi-field coupling calculations,and the multi-scale modeling of complex weaving structures.Finally,an outlook on future development directions is presented to provide theoretical support for the design and safety assess⁃ment of hot structures of advanced CMCs.
基金supported by Yunnan Fundamental Research Projects(No.202401CF070085)Yunnan Engineering Research Projects(No.2023-XMDJ-00617273)+1 种基金Industrial Support Plan Project of Gansu Provincial Education Department(No.2024CYZC-22)the National Natural Science Foundation of China(No.52064032).
文摘A novel approach of decorating graphene surface with graphene quantum dots(abbreviated as GQDs@Gr)was presented to achieve superior tribological properties in Gr/Cu composites.The prepared GQDs@Gr hybrid reinforcement possessed superior dispersion and had achieved strong interface bonding with Cu matrix.GQDs@Gr/Cu composite showed a good combination of wear resistance and electrical conductivity due to the synergistic effect of GQDs and Gr.Specifically,the coefficient of friction(COF)was reduced to 0.3,the wear rate(WR)was 2.13×10^(-5) mm^(3)·N^(−1)·m^(−1)(only a quarter of pure copper),and maintained the electrical conductivity of 96.5%IACS(international annealed copper standard).As a result,delamination,fracture,and plow furrows on the wear surface of Gr/Cu composite indicate that fatigue and abrasive adhesive wear are the main wear mechanisms.Wear surface lubrication film and strong interface bonding ensure better comprehensive performance of GQDs@Gr/Cu composite.
