AVIC Composite Corporation. Ltd

Beijing, China

AVIC Composite Corporation. Ltd

Beijing, China
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Xie W.-J.,AVIC Composite Corporation LTD | Chen M.-W.,AVIC Composite Corporation LTD
Rengong Jingti Xuebao/Journal of Synthetic Crystals | Year: 2016

SiC fiber reinforced SiC matrix (SiC/SiC) composites were prepared by polymer impregnation pyrolysis (PIP) progress with polycarbosilane (PCS) as impregnant and SiC fiber as reinforcement, and the microscopic morphology, phase structure, bending strength and fracture toughness were measured by SEM, XRD, energy spectrum analysis, three-point bending and single edge notched beam techniques. The results show that SiC/SiC composites prepared by PIP progress possess excellent mechanical properties, and the bending strength and fracture toughness reached 400 MPa and 16.5 MPa·m1/2 at room temperature respectively. Moreover, SiC/SiC composites achieved relative stable high temperature properties. As the temperature increasing, the bending strength nearly unchanged, and the fracture toughness decline slightly because of the destruction of the interface layer at 1350℃. © 2016, Chinese Ceramic Society. All right reserved.


Li X.,AVIC Composite Corporation Ltd. | Chen K.,Naval Academy of Armament | Liu G.,AVIC Composite Corporation Ltd.
Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica | Year: 2017

The shell elements with different section parameters and the solid elements with different equivalent material properties were used in the finite elements analysis of the composite marine propeller blade. The modal analysis, the response under uniformly distributed pressure loads and the thermal deformation in uniformly distributed temperature fields of the shell finite element modeling (FEM) were compared with those of the solid FEM. The results show that each of the two modeling methods has its own advantages and disadvantages on the modeling time and the layup adjusting convenience for blade with a variable layup from root to tip. There are some differences in the frequencies and the mode shapes in the modal analysis between two different FEMs, and each FEM is practicable for the modal analysis of the composite propeller blade under a given condition. For the two models, the shell FEM should be used in the response simulation under uniformly distributed pressure loads, while the solid FEM is suggested to analyze the thermal deformation of the blade in uniformly distributed temperature fields. © 2017, Chinese Society for Composite Materials. All right reserved.


Xu X.,AVIC Composite Corporation Ltd. | Zhou Z.,AVIC Composite Corporation Ltd.
AIP Conference Proceedings | Year: 2017

Inspired by the residual iron nanoparticles wrapped in the CNTs tips, we developed a method to induce efficient orientation of multiwalled CNTs bundles by relatively low magnetic fields. Laminates were fabricated to investigate the effect of magnet oriented CNTs on GIIC properties. Microstructure anisotropy of nanotube bundles demonstrated the orientation of CNT bundles by magnet. Furthermore, the application of magnet increased mode II interlaminar fracture toughness by 29% compared to plain laminates. © 2017 Author(s).


Zhong X.-Y.,AVIC Composite Corporation LTD | Zhang D.-J.,AVIC Composite Corporation LTD | Bao J.-W.,AVIC Composite Corporation LTD | Li W.-D.,AVIC Composite Corporation LTD
Guti Huojian Jishu/Journal of Solid Rocket Technology | Year: 2017

The toughened composites reinforced by domestic intermediate modulus carbon fiber(CCF800H)and based on epoxy matrix were prepared.The effects of contents of toughening thermoplastic filler on impact resistance, compression-after-impact(CAI)of composites were investigated in this paper.The results show the damage threshold load(DTL)of laminates was increased but the subtract value of the load of DTL was decreased with using interlaminar toughening method and increasing of toughening thermoplastic contents.Moreover, the increase in content of toughening thermoplastic, the damage area of laminates has been reduced in size, showing the impact resistance of composites has been improved.The failure mode of the composites becomes to matrix spitting and fiber broken from delamination on the large scale, and the compressive residual strength after impact being increased remarkably as well.Thanks to the interlaminar high toughness structure, the impact resistance of laminates could be greatly improved with the interleaves toughening method. © 2017, Editorial Dept. of JSRT. All right reserved.


Li G.,AVIC Composite Corporation Ltd. | Peng G.,AVIC Composite Corporation Ltd. | Wang Y.,AVIC Composite Corporation Ltd. | Xie F.,AVIC Composite Corporation Ltd.
Hangkong Cailiao Xuebao/Journal of Aeronautical Materials | Year: 2017

The morphologies, surface energies and surface chemical properties of the domestic T700 grade carbon fiber and the T700S carbon fiber were characterized by using scanning electronic microscopy (SEM), inverse gas chromatography(IGC) and X-ray photoelectron spectroscopy (XPS)respectively.The mechanical properties of the two carbon fibers/QY9611 composites were also discussed. The results indicate that the surface properties of carbon fibers have an important influence on the interfacial properties of composites. The interfacial properties of domestic T700 grade carbon fibers/QY9611 composite at room temperature/dry conditions are superior to T700S/QY9611 composite. The toughness of domestic T700 grade carbon fibers/QY9611composite is outstanding as well. The value of CAI has reached the level of foreign advanced composite IM7/5250-4. After hydrothermal treatment, the interfacial strength of domestic T700 grade carbon fibers/QY9611 composite is equal to that of T700S/QY9611 composite. It shows that domestic T700 grade carbon fibers/QY9611 composite has good hydrothermal-resistant properties. © 2017, Editorial Board of Journal of Aeronautical Materials. All right reserved.


Zhong X.-Y.,AVIC Composite Corporation LTD | Bao J.-W.,AVIC Composite Corporation LTD | Zhang D.-J.,AVIC Composite Corporation LTD | Zhang L.-W.,AVIC Composite Corporation LTD
Guti Huojian Jishu/Journal of Solid Rocket Technology | Year: 2017

The compression performance of composite reinforced by domestic aramid(Fanglun III) fiber based by epoxy matric with different elastic modulus was studied. The effects of modulus of matrix, tension of tow, test methods of compression on compression performance of composite were investigated. The results show the compression strength of composites could be improved with the increasing of modulus of epoxy matrix and tow tension. The samples of orthogonal ply show the higher intrinsic compression strength of aramid composite than unidirectional ply. The failure mechanism on compression was discussed and the methods of increasing compression performance of aramid composite were recommended. © 2017, Editorial Dept. of JSRT. All right reserved.


Jiang M.,Beijing Institute of Technology | Zhao L.,AVIC Composite Corporation. Ltd | Liu Q.,AVIC Composite Corporation. Ltd | Zhuo P.,AVIC Composite Corporation. Ltd
Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica | Year: 2013

In the liquid composite molding (LCM), we can use computer-aided simulation to forecast the filling time and process of the resin, which can assist us to design the flow runner of resin. This paper carried on the simulation of Vacuum Assisted Resin Infusion (VARI, a kind of LCM), based on a cap-shaped foam core sandwich structure. According to the Darcy's law, the calculation formula of the permeability is deduced, measuring the permeability include the carbon fiber, suture, the interface of foam and fiber, the sealing edge. Using the measured results, create some viable flow runner project to simulate and analysis. According to the results, we chosen the project with reasonable injection mode and flow runner to manufacture the cap-shaped foam core sandwich structure by VARI process, the result of the nondestructive testing show that internal defect is barely exist in the component, which proved that the simulation is effective.


Patent
Avic Composite Corporation Ltd. and Avic Beijing Institute Of Aeranutical Materials | Date: 2013-03-01

The present disclosure provides a plant fiber textile, a laminate with the plant fiber textile and a fabricating method of the laminate. The plant fiber textile has a matrix resin and continuous plant fibers distributed within the matrix resin. The plant fibers are subjected to a surface modification pretreatment including a coupling treatment with a coupling agent and/or a fire retardation treatment with a fire retardant. The laminate has a stack structure including a layer of the plant fiber textile and at least one layer selected from a group consisting of following layers: glass fiber, aramid fiber or carbon fiber non-woven cloth or textile, preferably distributed within the matrix resin; polymer fiber non-woven cloth or textile, preferably distributed within the matrix resin; or polymer foam or rubber material.


Patent
Avic Composite Corporation Ltd. and Avic Beijing Institute Of Aeranutical Materials | Date: 2015-01-07

Provided in the present invention are a composite material containing plant fibre fabrics and a preparation method thereof. The composite material comprises matrix resin and plant fibre fabrics distributed in the matrix resin, wherein the plant fibres of the plant fibre fabrics are pre-treated with surface modifications, and the pre-treatment with surface modifications comprises coupling treatment using a coupling agent, and/or surface flame retardant treatment using a flame retardant. The matrix resin comprises biomass matrix resin. The prepared composite material has the properties of green environmental protection, flame retardancy, sound isolation, etc.; and can be used as a cabin or trim component and can be applied to the following fields: the interiors of an airplane, high-speed train, or car, and furniture, etc.


Liu S.,AVIC Composite Corporation Ltd. | Liu F.,AVIC Composite Corporation Ltd. | Guo E.,AVIC Composite Corporation Ltd.
Jixie Gongcheng Xuebao/Journal of Mechanical Engineering | Year: 2014

Composite laminates are very sensitive to foreign impact because of their anisotropy and good absorbing ability to impact energy. They may exhibit different impact damage behavior in body under impact loading. Two kinds of specimens-RTM-stitched and prepreg composite laminate, are manufactured to investigate their behaviors of impact damages. The specimens are subjected to a given energy impact. An ultrasonic B-scan is arranged to the specimens by using focal system in order to study behaviors of impact damages in cross-sections of the specimen bodies. Experimental results have demonstrated that interior damaged area is much larger than damage on surface; new damages occur in different inetrlaminar layers with impact energy going into specimen body deeper and deeper, and they evolve not only along interfaces of layers; the distribution and orientation of damages between near- and far-impact point are significantly different; a clear difference in damage behavior between RTM-stitched and prepreg composite laminates is demonstrated very well, and the stitching fiber thread in depth direction of RTM-stitched composite laminate has obvious help on restriction to development of damages along interlaminar interfaces. The results provide very helpful and practical understanding of the damage behavior in different composite laminate bodies. That may motivate to find new mechanism to improve damage behavior of composite laminates. © 2014 Journal of Mechanical Engineering.

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