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2017 Vol. 60, No. 16
Published: 2017-08-15
FEATURE
FIGURE
FORUM
NEW VIEWPOINT
C0NTENTS
COVER STORY
PREPARATION FOR COMPOSITES
PROCESSING FOR COMPOSITES
 
       C0NTENTS
6 C0NTENTS
2017 Vol. 60 (16): 6-10 [Abstract] ( 112 ) HTMLNew PDF (4088 KB)  ( 186 )
       FEATURE
16 Effect of C/C Green Density on Friction and Wear Properties of C/C-SiC Composites Prepared by GSI Process
LIU Rongjun, MIAO Huaming, WANG Yanfei, SUN Guoshuai
DOI: 10.16080/j.issn1671-833x.2017.16.016
C/C-SiC composites were prepared by gaseous silicon infiltration (GSI) using C/C as green body. The effect
of C/C density on the phase composition, friction and wear properties was studied. Through analyzing the braking process,
the friction and wear mechanism of C/C-SiC composites is discussed in detail. The results show that, with C/C green density
increasing, the density of GSI C/C-SiC composites decreases, and C content and open porosity gradually increase, while the
contents of SiC and residual Si decrease. Under the self-dual circumstances, the average friction coefficient and wear rate of
the composites increase firstly and then decrease, however, the braking stability coefficient increases continuously. When the
density of C/C is 1.25g/cm3, the average friction coefficient and wear rate reach the maximum value. The braking process
mechanism of GSI C/C-SiC composites is controlled by furrow effect and adhesion effect. The furrow effect is the main part
in initial stage and late stage of braking, while the adhesion effect is the main factor in the middle stage.
2017 Vol. 60 (16): 16-21 [Abstract] ( 305 ) HTMLNew PDF (2830 KB)  ( 395 )
       FIGURE
22 Development of Advanced Ceramics and Its Composites to Improve Core Competency
2017 Vol. 60 (16): 22-24 [Abstract] ( 186 ) HTMLNew PDF (1466 KB)  ( 512 )
       COVER STORY
26 Research and Application of Powder Metallurgy Particle Reinforced Aluminum Matrix Composite Used in Aviation
NIE Junhui, FAN Jianzhong, WEI Shaohua, LIU Yanqiang
DOI: 10.16080/j.issn1671-833x.2017.16.026
In the present study, the performance advantages of particle reinforced aluminum matrix composites were
briefly analyzed. The component matching design of aluminum matrix composites was expounded, and the microstructures
and properties of aluminum matrix composites fabricated by powder metallurgy process were reviewed. In addition, the detailed
engineering preparation and nondestructive testing technologies for Al matrix composites in China and abroad were
introduced. In the end, this paper described and analyzed the application and development of particle reinforced aluminum
matrix composites in aviation.
2017 Vol. 60 (16): 26-36 [Abstract] ( 227 ) HTMLNew PDF (5659 KB)  ( 1094 )
       FORUM
40 Hot Stamping of Carbon Fiber-Reinforced Thermoplastic Composite Boxes
HAN Bin1, WANG Hong1, YU Yanghuiwen1, ZHOU Tao2, ZHANG Qi1
DOI: 10.16080/j.issn1671-833x.2017.16.040
Traditional forming processes of carbon-fiber reinforced thermoplastic composite profiles have many problems,
such as the complex operation, low forming efficiency, high cost and incapability for mass production, which limit the
large-scale applications of composites in the aerospace engineering. A new forming process is proposed, by the direct hotstamping
of a fiber-reinforced composite panel using an instant heating deep-drawing die. Through the tensile tests of composite
panels and hot stamping of the composite square-cup parts, the influences of fiber orientation on the stamping processing
and fiber deformation within the specimens are studied, with the ultimate drawing depth and forming shear angle obtained. For
better forming quality, it is suggested to adopt the parallel arrangement of the fiber orientation and the straight edge of the die
for the hot stamping process of fiber-woven composite box parts.
2017 Vol. 60 (16): 40-45 [Abstract] ( 237 ) HTMLNew PDF (2555 KB)  ( 963 )
46 Research and Study of Temperature Control on Composite Part During Curing Process
CHEN Guiyong, HE Kai, ZHANG Mian
DOI: 10.16080/j.issn1671-833x.2017.16.046
The temperature uniformity of composite part during cure is the key factor on all the mechanical property
for the product. Through the analysis of typical epoxy/carbon fiber composite curing process in industry, the research is made
on part configuration, tool structure and the simulation method of thermocouples to study the temperature control. The results
show that some regularities in curing for epoxy/carbon fiber composite are found, and thus lay a foundation for follow-up researches
on temperature /control of similar parts.
2017 Vol. 60 (16): 46-52 [Abstract] ( 258 ) HTMLNew PDF (2427 KB)  ( 564 )
53 Research on the Resin Flow Process of the Composite Pipe Key-Part in Vacuum Assisted Resin Transfer Molding
WANG Changchun, LIU Jianguang, YUE Guangquan, ZHAO Qinghua
DOI: 10.16080/j.issn1671-833x.2017.16.053
The composite pipe key-part in vacuum assisted resin transfer molding (VARTM) process was studied,
in which the resin flow processes of four possible resin injection methods were simulated with the finite element/control
volume method and the locations of inlet-gates and outlet-vents were estimated by comparing the needed injection time and
resin flow front shapes. Following results can be obtained from the simulation process: the line-injection method can obtain
a much better resin flow front shape as comparing with the point-injection method, which is the very reason of choosing
the line-injection method to obtain the composite pipe scaled-down and whole scale key-parts. The actual experiments
to validate the simulation results were conducted with the testing result that was implemented on the scale-down and wholescale
composite pipe structure using the determined resin injection method. The simulation results show good agreement
with that of the tests.
2017 Vol. 60 (16): 53-57 [Abstract] ( 262 ) HTMLNew PDF (4770 KB)  ( 431 )
58 Forming Process of Glass Fiber/Aluminum-Lithium Laminates Leading Edge Structure
HUA Xiaoge1, LI Huaguan1，2, LU Yi1, CHEN Yujie1, SUN Denghui2, TAO Jie1
DOI: 10.16080/j.issn1671-833x.2017.16.058
Aiming at the large curvature leading edge component, the self-forming characteristic of glass fiber/aluminum-
lithium super hybrid laminates (NFMLs) was studied. The results demonstrated that self-forming technology was
feasible to manufacture the large curvature NFMLs component such as the leading edge parts. The investigated component
exhibited no obvious interlaminar defect, presenting good fittability and thickness uniformity. Meanwhile, the forming process
hardly resulted in the generation of large residual stress, which provided a reference for the application of super hybrid
composites in the aircraft wing skin structure.
2017 Vol. 60 (16): 58-63 [Abstract] ( 299 ) HTMLNew PDF (3009 KB)  ( 533 )
64 Study on the Cure-Induced Deformation and Application of Compensation Technology of U Shaped Composite Structure in Autoclave Process
LIU Wangzi, WANG Xinwen, GUAN Haixin, LI Meng, XU Piao, CHEN Zhengsheng
DOI: 10.16080/j.issn1671-833x.2017.16.064
The U shaped structure of composite material was studied. Simulation technology was used for the
temperature distribution of typical U shape part in autoclave toolings, and the temperature distribution of the tool and part
in different periods. Under the influence of the heat transmission and distortion of tool, internal heat transmission, curing
degree, ultimately distortion and residual stress of composite part were simulated. According to the results of the simulation,
we optimize the structure of tool as well as the curing parameter, establish the compensating scheme for tool, thereby
improving issues of part, including the solidification and thermal deformation. Based on analysis results, the compensating
scheme had been established and validated. Result shows that the deformation between compensation and the theory shape
is 1.37mm. The feasibility of compensation is verified. Profile compensation can be used for improving the manufacturing
precision of composite component.
2017 Vol. 60 (16): 64-69 [Abstract] ( 338 ) HTMLNew PDF (3198 KB)  ( 536 )
70 Study on Manufacture of J Type Stiffened Panel Composite Material
LIU Wen, GU Wu, CUI Bo, HE Kai, LIU Zhijie, SHAN Yucai
DOI: 10.16080/j.issn1671-833x.2017.16.070
This article studied the main problem of J type stiffened panels faced in the practical application, situation of
application for some important technology, for example, the precise fill cor-material of R area, outer mold forming process of
fillet, perpendicular positioning of frame-bolt type, assemble of co-cementing vacuum bag, have been introduced, and a deep
analysis has also been done for the technique related. The experiment results show that, the cor-material can be made precisely
with the precise calculation and the application for dedicated molds, by which, the quality of stiffened panels can be improved.
With the application of outer mold and frame-type location device, the surface quality, dimensional accuracy, positional accuracy
of J type stiffened panels will all be improved. Surface problem will induce with the use of vulcanized rubber for resist
strips and suitable soft mode. With the optimizing of auxiliary material laying method, risk of bridging and bag broken will reduce.
By the use of all these technique introduced below, we successfully made the stiffened panels that can be used, this part
can also be made bulkily.
2017 Vol. 60 (16): 70-74 [Abstract] ( 191 ) HTMLNew PDF (2164 KB)  ( 498 )
       NEW VIEWPOINT
76 Application of Automatic Fiber Placement Technology in A350 Manufacturing
ZHENG Guangqiang, YAO Feng, ZHOU Xiaoqin
DOI: 10.16080/j.issn1671-833x.2017.16.076
Taking Airbus A350 composite manufacturing technology as background, this paper analyzed the manufacturing
features of aircraft fuselage structure and the application of automatic fiber placement (AFP). The principles,
characteristics and advantage of AFP are introduced; AFP machine, slit tape, process and application are also covered in
this paper. The key issues in engineering application of composite structure AFP technology are put forward. It can provide
reference to the application of Chinese domestic AFP technology in composite structure forming.
2017 Vol. 60 (16): 76-82 [Abstract] ( 268 ) HTMLNew PDF (4187 KB)  ( 1453 )
       PREPARATION FOR COMPOSITES
84 Influences of Carbon Fiber/Epoxy Prepreg Pre-Heating and Storage Aging on Composite Mechanical Properties
CHEN Ping1,2, ZHAO Yueqing1, LI Hongfu3, ZHANG Boming1
DOI: 10.16080/j.issn1671-833x.2017.16.084
The curing behavior was firstly characterized through different scanning calorimetry (DSC) using modelfree
kinetic method (Flynn-Wall-Ozawa, FWO). The results show that FWO is suitable to describe and predict the curing
process. At the same time, combining with the characteristic of diaphragm forming, prepreg pre-treated at different time
and temperatures were used to product composite laminates. Then the interlaminar shear and bending properties were
tested. The results show that with the increase of pre-heating time at 80℃ , the shear strength gradually decreases while the
thickness of the specimens increases. The flexural modules decrease slightly compared with that of specimens without preheating.
For specimens aging at room temperature, the shear strength and flexural properties show small fluctuation with no
obvious regularity as the prolongation of aging time.
2017 Vol. 60 (16): 84-89 [Abstract] ( 285 ) HTMLNew PDF (1542 KB)  ( 615 )
90 Fabrication Technique and Application Prospect of Continuous SiC Fiber Reinforced Ceramic Matrix Composites for Aeroengine
LIU Hu1,2, YANG Jinhua1,2, JIAO Jian1,2
DOI: 10.16080/j.issn1671-833x.2017.16.090
Three manufacturing processes for continuous SiC fiber reinforced ceramic matrix composites (SiCf/SiC),
in other words, chemical vapor infiltration (CVI), precursor infiltration and pyrolysis (PIP) and melt infiltration (MI) were
reviewed in this article. Meanwhile, the performances of ceramic matrix composites and their further application in aeroengine
were discussed as well.
2017 Vol. 60 (16): 90-95 [Abstract] ( 349 ) HTMLNew PDF (2342 KB)  ( 1039 )
       PROCESSING FOR COMPOSITES
96 Research for Cutting Force and Torque in Rotary Ultrasonic Drilling of#br# Carbon Fiber Reinforced Polymers
YUAN Songmei1,2,SONG Heng1,2, LU Yilin1,2
DOI: 10.16080/j.issn1671-833x.2017.16.096

Aiming at the problems in the processing of carbon fiber reinforced polymers (CFRP), the rotary ultrasonic
drilling has been carried out on CFRP-T700 composites with the abrasive trepanning core tool. From the graphical analysis,
the cutting force has been found decreased with the increase of spindle speed whereas the corresponding torque has
been found increased with the increase of spindle speed. The decrease in cutting force and the corresponding torque values
has been found up to 56.6% and 39.1%, respectively in comparison with conventional machining. The mathematical relation
of the cutting force and the torque has been been developed. The proportionality constant, k has been found between
the cutting force and the torque has been found experimentally. The rotary ultrasonic drilling with trepanning tool is the
essential need to reduce the cutting force and torque for machining of CFRP composites. This research can be applied for
practical machining at the industry level.
2017 Vol. 60 (16): 96-102 [Abstract] ( 313 ) HTMLNew PDF (2112 KB)  ( 422 )
103 Research on Milling Force and Surface Roughness of GFRP in Slot Milling
ZHENG Kai1,2, CHEN Yan1,2, YAN Chaoren1,2, LIANG Yuhong1,2
DOI: 10.16080/j.issn1671-833x.2017.16.103
Slot milling is one of the most common mechanical operations for machining composite materials. Experiments
were carried out in order to investigate the milling force and surface roughness during GFRP milling. An orthogonal
exam was designed to explore the influence of machining parameters (spindle speed, feed rate and depth of cut) on milling
force. Matlab is used to analyze the experimental data of milling force and surface roughness. After regression analysis, the
milling force and surface roughness regression equations are established. Finally, the correctness of the milling force and surface
roughness regression equations is verified by experiments. The results show that depth of cutting has a greatest influence
on milling force, while the influence of feed rate is small; spindle speed has a greatest influence on surface roughness, while
the influence of depth of cutting is small. And the error range of the milling force and surface roughness is within 20%.
2017 Vol. 60 (16): 103-108 [Abstract] ( 215 ) HTMLNew PDF (2311 KB)  ( 369 )
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· 'Aeronautical Manufacturing technology ' is included in EI database
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· High Quality Sci-tech Journal Classification Catalogue in Aerospace Field （2023）
· A Guide to the Core Journals of China (hosted by Peking University Library)
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