COMPOSITES SCIENCE AND ENGINEERING

Mechanical and thermal properties of 2.5D quartz fiber reinforced nano-porous resin-based composites

SHEN Haochen, NIU Bo, ZHANG Qikai, HAO Jingying, ZHANG Yayun, LONG Donghui

2023, 0(4): 5-13. DOI: 10.19936/j.cnki.2096-8000.20230428.001

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In this paper, 2.5D quartz fiber/nanoporous phenolic resin-based composites with excellent mechanical properties and low thermal conductivity were prepared by sol-gel process using 2.5D quartz fiber preform as reinforcement and nanoporous phenolic resin as matrix. The microstructure, heat transfer and mechanical properties of the composite were systematically studied based on the characterization and finite element analysis of mechanical and thermal conductivity. The results show that the resin presents a nanoporous three-dimensional network structure which effectively reduces the density (1.35 g/cm³) and thermal conductivity (0.18 W·m^-1·K^-1), and improves the thermal insulation performance of the material. Meanwhile, the mechanical properties and fracture behavior of 2.5D woven composites exhibit obvious anisotropy due to the bending warp and straight weft . In addition, a finite element model based on the actual material structure, mechanical and thermal properties was established and the effects of fiber volume fraction, matrix parameters and fiber parameters on thermal conductivity and elasticity modulus in different directions were studied.

Numerical simulation of size effect of carbon fiber reinforced composites in SHPB test

WEN Zhichao, QU Meijiao, LI Zhexu, LI Mengqi, DONG Qiuyu, SUN Jian

2023, 0(4): 14-20. DOI: 10.19936/j.cnki.2096-8000.20230428.002

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Split Hopkinson Pressure Bar (SHPB) experiment is one of the important means to study the compressive properties of materials under medium and high strain rates. In this paper, ABAQUS simulation was used to study the size effect of carbon fiber reinforced resin matrix composites in Hopkinson pressure bar experiment. The effects of different impact velocities, impact directions and sample sizes on the stress of the samples were investigated. The results show that when the sample is impacted along the fiber direction, the stress of the sample is not affected by the length of the compression direction, but is greatly affected by the impact velocity, and the smaller the sample size is, the more obvious the effect is. When the specimen is impacted perpendicular to the fiber direction, both the compression direction length and the impact velocity have great influence on the stress of the specimen. The stress of the specimen increases with the decrease of the specimen size and the increase of the impact velocity.

Effect of binding yarn linear density change on properties of non-crimp fabrics composites

GOU Yikun, DUAN Yuexin, NING Bo, YANG Yang

2023, 0(4): 21-26. DOI: 10.19936/j.cnki.2096-8000.20230428.003

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Using linear density of 30 dtex and 50 dtex non-crimp fabrics as raw materials, the effect of linear density change of binding yarn on the properties of non-crimp fabrics involved in LCM process was investigated. The results show that the decrease of linear density of binding yarn is beneficial to improve the permeability of non-crimp fabrics. Metallographic pictures show that the binding yarn with lower linear density has a smaller volume and the fiber volume fraction at the binding yarn is smaller. The decrease of linear density of binding yarn is beneficial to slip and nesting between fibers, and the non-crimp fabrics can be compressed to a thinner thickness. In the range of 30 dtex to 50 dtex, the change of linear density of binding yarn has no obvious influence on the springback effect of non-crimp fabrics after deformation. When the binding yarn density is reduced from 50 dtex to 30 dtex, the 0° tensile strength decreased by 10.1%, the 0° compression strength increased by 21.9%, the bending strength increased by 9.5%, the interlaminar shear strength increased by 3.3%, the 0° tensile modulus increased by 6.3%, the 0° compression modulus increased by 11.3%, and the bending modulus increased by 9.9%. Metallographic pictures show that the interlaminar resin distribution of the composites prepared by 30 dtex binding yarn is easy to be nonuniform.

Research on variable tension control method based on tension compensation

XU Jiazhong, NI Mengjian, LI Xin, LI Bin, YANG Hai

2023, 0(4): 27-33. DOI: 10.19936/j.cnki.2096-8000.20220728.032

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Aiming at the problem of the friction resistance and the change in suspension length caused by the fiber tension change at the doffing point when the yarn is wound from the yarn outlet mechanism to the main shaft in the process of fiber winding of rotary components, a variable tension control method based on tension compensation is proposed. The tension relationship of yarn before and after passing through the guide roller at any wrap angle is analyzed. The trajectory of the yarn outlet guide head is planned by the geodesic winding theory, and the trajectory equation of the yarn outlet guide head is obtained. The mathematical model of mandrel winding is established, and the influence of suspension length on tension change during mandrel winding is analyzed. The relationship between tension at different doffing points and tension needed to be provided by the doffing end is obtained, and the tension fluctuation caused by suspension length change is compensated, so that the tension value at doffing point is constant. The fiber winding test of rotary components with tension compensation is carried out. The winding experiment results show that after adding tension compensation, the winding tension is more stable. It is verified that the proposed variable tension control method based on tension compensation can effectively suppress the fluctuation of tension in the winding process.

Effect of coupling agent on the interfacial properties of carbon fiber reinforced vinyl resin composites

ZHANG Zhen, WANG Wanjie, PENG Yunsong, CAO Yanxia, LI Xiang

2023, 0(4): 34-40. DOI: 10.19936/j.cnki.2096-8000.20230428.005

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In this paper, the effects of the types of coupling agent, the amounts of coupling agent and the adding process on the properties of carbon fiber reinforced vinyl resin composites were studied by adding coupling agent. Silane coupling agent and macromolecule coupling agent were used to modify the composites respectively. The results showed that macromolecule coupling agent improved the properties of carbon fiber reinforced vinyl resin composites more significantly. For different kinds of carbon fiber fabric, the enhancement effect of macromolecule coupling agent is different. For a domestic T700 carbon fiber fabric, with the addition of macromolecular coupling agent, the performance of the composite material is constantly improved, and when the dosage is 1.5%, the interlaminar shear strength increases 41.4% (from 24.4 MPa to 34.5 MPa). However, when the macromolecule coupling agent is used to modify a Toray T700 carbon fiber fabric, its properties show a trend of decline. In addition, by comparing the performance improvement and data dispersion of composite materials with different adding processes, it is found that the process of adding macromolecule coupling agent into resin is better than that of spraying on the surface of carbon fiber fabric.

Study on the influence of damp heat on the mechanical and electrical properties of quartz fiber reinforced bismaleimide resin matrix composite

SUN Jianming, WEN Lei, LI Bintai, SHI Fenghui

2023, 0(4): 41-44. DOI: 10.19936/j.cnki.2096-8000.20230428.006

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In this paper, a kind of unidirectional quartz fiber reinforced bismaleic resin matrix (brand:QF210/5429) composite with low loss and high transmission was treated by damp heat aging. The moisture absorption change law of QF210/5429 composite was studied. The mechanical properties and electrical energy of the composite after damp heat treatment were studied, and the influence mechanism of damp heat treatment on the properties of the composite was analyzed. The results showed that the saturated moisture absorption rate of QF210/5429 composite is 0.6%. After saturated moisture absorption, the tensile strength and interlaminar shear strength of the composite are 1 450 MPa and 105 MPa respectively. Compared with the tensile strength and inter laminar shear strength of the composite without damp heat treatment, the inter laminar shear strength is reduced by 20.5% and 13.9% respectively. The bending and compression properties of the composite have no obvious change. After saturated moisture absorption, the dielectric constant of the composite is about 3.55, and the tangent value of dielectric loss is about 1.1×10^-2. Compared with the composites without damp heat treatment, the dielectric constant has no obvious change, but the tangent value of electrical loss increases by 120%.

Progressive damage analysis of open-hole laminate under tensile load

CAI Congyi, WU Haiyong

2023, 0(4): 45-50. DOI: 10.19936/j.cnki.2096-8000.20230428.007

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The progressive damage model of tensile open-hole laminates is established to study the failure modes of laminates, and analyze the effect of different sizes of open-hole on the ultimate load of open-hole laminates. By compiling VUMAT subroutine, Hashin failure criterion and material degradation model are added to progressive damage analysis. Firstly, the displacement-load curves of open-hole laminate with different mesh numbers are compared with the experiment result, and then the failure modes obtained from the simulation analysis are compared with the test results to verify the correctness of the progressive damage model and the selected failure criteria. Finally, the influence of different sizes of open hole on the tensile ultimate load of open-hole laminates is studied. The results show that the progressive damage model established in this paper can accurately predict the displacement-load curves and failure modes of laminates. The fiber tensile failure firstly occurs at the edge of the hole and expands along the 45° direction. With the increment of the open-hole diameter, the tensile ultimate load of open-hole laminates gradually decreases, and the decline speed begins to decrease linearly, and then the decline speed increases gradually.

Calculating method of projection length of diagonal cracks of RC beams reinforced with CFRP strips

GUO Weidong, YU Feng, TAN Siyong, FANG Yuan, QIN Yin, WANG Zongsen, GUO Shengquan

2023, 0(4): 51-55. DOI: 10.19936/j.cnki.2096-8000.20230428.008

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The shear tests of 18 RC beams reinforced with CFRP strips are carried out, and the impact of shear span ratio, spacing of CFRP strips and pre-cracked degree on the projection length of diagonal cracks of CFRP reinforced RC beams is investigated. The experimental results show that with the decrease of the spacing of CFRP strips, the development rate of the diagonal cracks decreases gradually, while the number of diagonal cracks increases. As the pre-cracked degree increases, the development rate of diagonal cracks increases, the number and projection length of diagonal cracks increase. Shear span ratio is the main parameters affecting the development of diagonal cracks and the length of projection. As shear span ratio increases, the projection length of diagonal cracks increases gradually. On the basis of experimental research, considering the influence of shear span ratio, spacing of CFRP strips and pre-cracked degree, a formula for calculating horizontal projection length of diagonal cracks of the CFRP reinforced RC beams is put forward.

Analysis of longitudinal force interaction of multi-span continuous girder bridge strengthened by prestressed CFRP plates

WU Bitao, LIN Zucai, ZHANG Jian, OUYANG Yao, YANG Junfeng

2023, 0(4): 56-62. DOI: 10.19936/j.cnki.2096-8000.20230428.009

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To study the interaction relationship between the forces of each span of a multi-span continuous girder bridge strengthened by prestressed CFRP plates, based on the engineering background of the Xinshuhe river continuous box girder bridge, this paper established a continuous girder bridge prestressed CFRP plate reinforcement model, and studied the reinforcement of prestressed CFRP plates. The interaction law between spans of multi span continuous beam bridge strengthened with prestressed CFRP plate and the influence law of prestressed anchorage position on the reinforcement effect are studied. Finally, the tensioning prestress ratio of each span when the whole bridge reaches the same reinforcement effect is given. The results show that the prestressed CFRP plate reinforcement of multi span continuous beam bridge will increase the deflection of adjacent odd spans, produce reverse arch effect of adjacent even spans, and significantly reduce the influence on the back of adjacent second spans. Compared with the simply supported beam bridge, the adjacent span of the continuous beam bridge has a weakening and restraining effect on the reinforcement effect, which is related to the position of the strengthened span. When the ratio of tension prestress between the middle span and its adjacent span is 1∶0.3, it can effectively reduce the impact on the adjacent span, and has little impact on the reinforcement effect of the reinforced span, and has the least impact on the smoothness of the bridge deck.

Study on quick repair technology for bullet hole damage of skin of a helicopter

JIN Lei, WANG Gongdong, XU Chengyang, YU Lingjun, YAO Songyang

2023, 0(4): 63-69. DOI: 10.19936/j.cnki.2096-8000.20230428.010

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In wartime, the skin of aircraft will be damaged by bullet attack, which will affect the normal flight of helicopter. In order to solve this problem, a new quick repair technology of skin based on adhesive and fiber prepreg was studied. Firstly, the repair scheme and process of this process are introduced. Secondly, on the basis of the above research, the influence of repairing method and grinding method on the strength of repaired skin was studied by combining simulation and experiment. Finally, the results of the above research were verified by experiment, and the strength of repaired skin by this process method could reach more than 98% of the strength of skin mother plate. Its repair time is reduced to 2/3 of the traditional composite repair process, and its repair weight is 1/3 of the traditional process.

Experimental study on static tension and tension-tension fatigue of scarfing repaired plain woven composite laminates

SHI Xiaojun, WANG Xuan, YANG Chenchen, GAO Junfu

2023, 0(4): 70-77. DOI: 10.19936/j.cnki.2096-8000.20230428.011

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The effects of scarf repairing on static tensile and tension-tension fatigue properties of plain woven composite laminates were studied experimentally, and the fatigue test stress ratio R was 0.1. The results show that the static tensile strength, static tensile modulus, tension-tension fatigue limit and residual load of laminates are reduced by scarf repairing, and the recovery rates are 64.9%, 82.5%, 80.7% and 76.6%, respectively. The recovery extent of tension-tension fatigue life decreases with the increase of load level. The fitted S-N curve has high reliability in the finite life region. After 10⁶ cyclic loading, the remaining loads of intact parts and repaired parts are both less than static tensile failure loads, and the corresponding stiffness increase. Fiber fracture and matrix cracking occur at the fractograph of all the test pieces. Fiber fracture is the main failure mode of the intact test pieces with the delamination damage. Shear failure occur between the patch and adhesive layer at the fractograph of the repaired test pieces, resulting in obvious debonding between the patch and the parent laminate.

Research on geometric nonlinear static aeroelasticity of high-aspect-ratio composite wing

ZHANG Baosheng, WANG Junli, LIU Zhiyuan, LI Jinyang, FENG Yuru

2023, 0(4): 78-86. DOI: 10.19936/j.cnki.2096-8000.20230428.012

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Aeroelastic research has extremely important significance on the stability of the wing. At present, the large size high-aspect-ratio composite wing under the action of aerodynamic force, can produce large bending torsional deformation, making the geometric nonlinear static aeroelasticity problem become more prominent, greatly reducing the stability of this type of plane and seriously affecting the flight safety. Based on the bi-directional coupling method of CFD/CSD, the aerodynamic load under large deformation was solved by N-S governing equation and the balance equation of nonlinear structure was solved by Newton-Raphson iterative method. The large deformation geometric nonlinear static aeroelastic problem of composite wings with large aspect ratio was numerically analyzed. Through the simulation analysis, the structural variation law of the angle of attack and Mach number on the geometric nonlinear static aeroelastic deformation of the high-aspect ratio composite wing is obtained, and the influence degree of the aeroelastic deformation on the longitudinal aerodynamic characteristics of the wing is analyzed.

Sealing design and test verification of helicopter composite fuel tank

XIN Zhibo, ZHU Yansong, DUAN Yugang, WANG Ben, HUANG Zhiwen, WANG Hongxiao, MING Yueke

2023, 0(4): 87-93. DOI: 10.19936/j.cnki.2096-8000.20230428.013

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Composite materials, as a new generation of lightweight and high-strength materials, have been widely used in the aerospace manufacturing industry. In terms of the structural design of composite fuel tanks, the core issue relies on the seal design under the strength requirements. In this paper, firstly, according to the air impermeability requirement, ABAQUS finite element analysis software was used to analyze the overall composite strain distribution, and then the seal structure design was optimized. After that, the composite fuel tank components are manufactured according to the design requirements, and finally the assembled overall composite fuel tank was verified. The results show that the designed composite fuel tank can fully meet the requirements of air impermeability pressure test and the oil resistance test as well.

Study of tensile properties of a land-based inflatable antenna reflective surface material

ZHAI Wenhao, JIANG Jinhua, HAO Enquan, SHAO Huiqi, CHEN Nanliang, SHEN Wei

2023, 0(4): 94-99. DOI: 10.19936/j.cnki.2096-8000.20230428.014

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A three-dimensional structured woven spacer fabric reinforced PVC film composite is proposed as the reflective surface material for land-based inflatable antennas. In order to study the differences in mechanical properties of the surface layer of the reflective surface material in different directions, the relationship between different splice materials and different splice widths and the fracture strength of the splice, as well as the factors influencing the tensile strength of the reflective surface material in the spacing direction, uniaxial tensile tests were conducted on the reflective surface material. The test results show that the tensile breaking strength of the surface layer of the composite material is latitudinal > meridional >45° direction; the breaking strength of the base fabric is increased by 2~3 times in the meridional direction and 10 times in the 45° direction after the lamination of the PVC film. The fracture strength of the splice width and the splice material are positively correlated with the fracture strength of the material splice; the tensile strength in the spacer direction is proportional to the density of the spacer yarn and the density of the tissue structure of the surface fabric, and inversely proportional to the spacer height, in which the density of the spacer yarn has the greatest influence on the tensile strength in the spacer direction.

Effect of skin parameters on the buckling and post-buckling behavior of composite stiffened panels under axial load

XU Liang, BIAN Yubo, SONG Wanwan, ZHOU Song, XING Bendong

2023, 0(4): 100-106. DOI: 10.19936/j.cnki.2096-8000.20230428.015

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There are a large number of stiffened panels in the aircraft, and the use of composite materials to replace traditional metal materials to make stiffened panels can reduce weight and improve performance. In order to study the effect of different skin parameters on the buckling and post-buckling behavior of composite stiffened panels under axial compression loads, a finite element model was established based on ABAQUS. First, the eigenvalue method is used for buckling analysis, then the ABAQUS dynamic explicit is used for quasi-static simulation analysis (post-buckling analysis), and finally the axial compression test is performed. The results show that the finite element analysis results are roughly consistent with the experimental values, that is, the model solution method can correctly forecast the post-buckling load. The difference of the skin parameters changes the buckling mode of the stiffened panels, and has a significant impact on the post-buckling behavior, which significantly changes the load-bearing capacity of the stiffener structure. The research results are of great significance for optimizing the bearing capacity of composite stiffened panels and improving the efficiency of aircraft structure design.

Fracture mechanism and cause analysis of carbon fiber composite core conductor

ZHENG Jianjun, TIAN Feng, ZHANG Tao, CHEN Hao

2023, 0(4): 107-112. DOI: 10.19936/j.cnki.2096-8000.20230428.016

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In this paper, aiming at one fracture fault of the carbon-fiber composite core wire operated in a 220 kV transmission line, the non in-serviced (new) and broken carbon-fiber composite core wires were tested and analyzed by means of macro and micro morphology observations, X-ray energy spectrum detection, fourier infrared spectroscopy analysis, thermal decomposition experiment, compressive performance testing and so on, and the fracture causes and fracture mechanism were also investigated. The results indicate that the fracture of carbon-fiber composite core wire is mainly related to the fretting wear of glass fiber layer and fretting fatigue of carbon fiber core caused by breeze galloping. In addition, partial discharge is induced when the glass fiber layer is worn. And the high temperature and nitric acid produced during discharge lead to the melting of epoxy resin and stress corrosion of glass fiber, further aggravating the fracture of carbon fiber composite core. The fracture mechanism results reveal that the fracture process of carbon-fiber composite core wire can be divided into five stages. When the carbon fiber composite core is entirely broken, the load tension will exceed the allowable tension of T-shaped aluminum lines, resulting in cracking after short-time operation.

Research on the influence of deformation rate on fatigue performance of FRPM pipe culvert

SUN Chao, WANG Qingzhou, WEI Lianyu, MENG Huilin, WANG Xiaosen

2023, 0(4): 113-120. DOI: 10.19936/j.cnki.2096-8000.20230428.017

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The FRPM pipe culvert fixture is developed according to the force characteristics of the pipe culvert, and the specimens with a deformation rate of 0%, 1%, 2% and 3% are subjected to 10 times, 500 000 times, 1 million times and 2 million times of cyclic loading. The influence of deformation rate on the fatigue performance of FRPM pipe culvert is andyzed. According to the residual stiffness theory linear fatigue damage theory and fatigue test results, the residual stiffness fatigue life prediction model of FRPM pipe culvert is established. The main conclusions are as follows: ①The deformation rate affects the load-bearing capacity of the specimen. The greater the deformation rate, the lower the load-bearing capacity of the specimen after the fatigue test. ②The increase in the number of cyclic fatigue loads can reduce the FRPM pipe culvert when the deformation rate is 0%, after 2 million times of fatigue load, the pipe stiffness of FRPM pipe culvert specimen drops from 50.71 kPa to 46.05 kPa, a decrease of 10.12%. ③After fatigue load, the deformation rate reduces the bearing capacity and stiffness of the pipe culvert. For a pipe culvert with a deformation rate of 3%, after 2 million fatigue loads, the stiffness of the pipe decreases by 24.44%. ④The strain growth rate at each measurement point of the specimen is positively correlated with the number of fatigue loads. The greater the deformation rate, the lower the load-bearing capacity after the fatigue load, and the more the number of fatigue actions, the greater the reduction in its load-bearing capacity. ⑤Establishing a fatigue life prediction model based on residual stiffness through the fatigue life prediction model. When the deformation rate is 0%, 1%, 2% and 3%, the fatigue life of FRPM pipe culvert, when the deformation rate is 0%, the fatigue life of FRPM pipe culvert is 12 529 600 times, and when the deformation rate is 3%, the fatigue life of FRPM pipe culvert was 6 937 100 times. The prediction model shows that FRPM pipe culvert has good fatigue performance, and the fatigue life can meet the service requirements.

Experimental study on thermophysical properties and melting characteristics of carbon fiber composite phase change materials

JI Wei, LIU Weijun

2023, 0(4): 121-127. DOI: 10.19936/j.cnki.2096-8000.20230428.018

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The thermophysical properties and heat transfer characteristics of phase change materials are of great significance for the application of energy storage devices. The composite phase change materials were prepared from paraffin and carbon fiber powder. The thermophysical properties of the composite phase change materials were characterized by scientific instruments. The results show that the addition of carbon fiber can increase the thermal conductivity of the phase change materials and reduce the melting temperature and latent heat. The experiment of melting heat transfer characteristics was completed in the self-built experimental system. The experiment confirmed that the increase of carbon fiber content will accelerate the overall melting speed of composite phase change materials, but the overall melting trend remains unchanged. In the process of upward diffusion in the liquid region, the melting rate is faster in the early stage, and slows down after the solid-liquid interface tends to be horizontal.

Research progress on interface control and plastic deformation behavior of B₄C_p/Al composites

PENG Haokai, LIU Yao, MA Donglin, LENG Yongxiang

2023, 0(4): 128-136. DOI: 10.19936/j.cnki.2096-8000.20230428.019

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B¹⁰ has excellent thermal neutron shielding performance. B₄C_p/Al composite large size sheet with high B¹⁰ content, good fracture toughness and plastic deformation prosessing has a broad application prospect in the post-processing of spent fuel. However, with the increase of the content of B₄C particles, the brittle phases at the interface between B₄C and Al increase, resulting in poor toughness of B₄C_p/Al composites, weakened the plastic deformation ability, and the subsequent plastic processing formability. Therefore, the key to preparing high boron content B₄C_p/Al sheet with good thermal neutron shielding performance is to improve the plastic deformation capacity and hot rolling performance of B₄C_p/Al composites by controlling the interface reaction products of B₄C particles and Al matrix under the premise of ensuring the high content of B₄C particles. This article first introduces the fabrication method of B₄C_p/Al composite and focusing on infiltration especially. This article also introduces the plastic deformation mechanism of B₄C_p/Al, and reviews the effects of hot working temperature, strain rate and interface structure on the plastic deformation capacity and hot rolling properties of B₄C_p/Al, meanwhile, the recent results about controlling the infiltration temperature, adding alloying elements or ceramic phase to adjust the composition and structure of the B₄C_p/Al interface were introduced. In the end, this article points out the future directions of fabrication and processing of high boron content B₄C_p/Al large size composite sheet for spent fuel reprocessing by infiltration and hot rolling.

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