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2017 Vol. 60, No. 4
Published: 2017-02-15
FEATURE
FIGURE
FORUM
NEW VIEWPOINT
RESEARCH
C0NTENTS
COVER STORY
 
       C0NTENTS
6 C0NTENTS
2017 Vol. 60 (4): 6-10 [Abstract] ( 88 ) HTMLNew PDF (6500 KB)  ( 270 )
       FEATURE
16 Study on Mould Surface Revising of Composites Part Based on the Surface Node
HAN Zhiren1,2, YANG Pan2, TONG Gang3, XIANG Song3
DOI: 10.16080/j.issn1671-833x.2017.04.016
Aiming at the problems in the aerospace industry for a long time that curing process causes the size error
of composite part prepared in autoclave, assembly with stress and fatigue life is reduced. It realizes the match between
the two surfaces by the location coordinates of fiducial points, and presents a arithmetic of deformation modification and
a feasible means of correction by the study on the factors and mechanism of composites curing deformation. In the design
process of the forming die, a compensation for the surface of the forming die has been carried out, which reduces the trial
and amendment work of the die. It can realize the effective control of composites curing deformation and achieve the goal
of composites precision manufacturing.
2017 Vol. 60 (4): 16-19 [Abstract] ( 171 ) HTMLNew PDF (1435 KB)  ( 475 )
       FIGURE
20 Surface Layer Modification Technology, Internal Medicine of Mechanical Manufacturing
高玉魁 GAO Yukui
同济大学航空航天与力学学院
教授
Professor, School of Aerospace Engineering
and Applied Mechanics, Tongji
University
2017 Vol. 60 (4): 20-22 [Abstract] ( 141 ) HTMLNew PDF (2942 KB)  ( 452 )
       COVER STORY
24 Large Aircraft Assembly Plan and Simulation Technology for Module-Based Configuration Production
HOU Zhuobing, MENG Jinghui, HU Chengdan
DOI: 10.16080/j.issn1671-833x.2017.04.024
Large aircraft assembly has such typical characters as multi-discipline, high precision, complex coordinate
supplier chain, heavy workload, etc. It takes the definitive role during the aircraft deliver cycle, quality and cost control.
Currently, most domestic aircraft manufacturers have adopted model-based definition and assembly simulation technologies,
but the business is still keeping the traditional design and manufacturing separated mode. The advanced digital assembly
engineering application system is not built. This article analyses the digital assembly adoption status in avia-tion
industry, proposes the integrated architecture of combing advanced business management, digital manufacturing engineering
design and assembly simulation & validation. Then key technologies are demonstrated. Based on the architecture,
constructs the engineering application integration environment of assembly plan and simulation combined with advanced
management approaches. Final the application benefits of one large aircraft program are described.
2017 Vol. 60 (4): 24-30 [Abstract] ( 188 ) HTMLNew PDF (2305 KB)  ( 1041 )
       FORUM
34 Friction and Influence in FEM Simulation of Local Loading Process for Titanium  Alloy Rib-Web Component
ZHANG Dawei
Isothermal local loading process provides an efficient approach to manufacture large-sized titanium-alloy ribweb
component with saving force and high performance. However, the forming process is complex, and the material parameter,
geometric parameter and processing parameter have a stronger coupling action in the forming processing, so the accurate
prediction about the process is difficult. The finite element simulation provides a powerful approach for analyzing and optimizing
this complex forming process. The friction model and friction condition are one of the key boundary conditions in numerical
simulation, which play an important role in accuracy and reliability of predicted results. In this paper, the influences of the
friction models such as Coulomb friction model, shear friction model, Coulomb-shear friction model and Coulomb-sticking
friction model, and the magnitude of friction on the simulation results for local loading process of rib-web component have
been analyzed. The results in the present study indicate that: The shear friction model is suitable for the modeling and simulation
of local loading process; Accurate friction condition can decrease predicted error of forming loadby more than 15%; Active
controlling the friction in local zone will improve the cavity filling and reduce the forming defect.
2017 Vol. 60 (4): 34-41 [Abstract] ( 146 ) HTMLNew PDF (2244 KB)  ( 719 )
42 Influence of Welding Sequence on the Distortion of TA15 Titanium Alloy Panel
DONG Wenchao, LU Shanping
DOI: 10.16080/j.issn1671-833x.2017.04.042
A welding finite element model for TA15 titanium alloy panel structure is developed. The influence of
welding sequence on the panel distortion is investigated by using thermo-elastic-plastic finite element method. The double
ellipsoid heat source models which are suitable for the site TIG penetration welding process are established through comparing
the weld cross-section and the residual stress of calculation and experiment. Furthermore, the distortion behaviors of
the panel structure in different welding sequences are simulated. The results show that the distortion of the middle part of
thin plate is severewhen the welding starts from one side, and the maximum distortion is 3.9mm. The distortion of the thin
plates is improved effectively by using the symmetrical welding sequence.
2017 Vol. 60 (4): 42-46 [Abstract] ( 200 ) HTMLNew PDF (2225 KB)  ( 401 )
47 Review on Simulation Technology for the Manufacturing Process of Composites
YUAN Zhenyi1, WANG Yongjun1, CAI Yujin1, GUO Jungang2, SU Xia2, SUN Bo2
DOI: 10.16080/j.issn1671-833x.2017.04.047
Using the simulation technology for the manufacturing process of composites, many defects such as delamination,
void, uneven temperature field distribution and curing deformation can be predicted effectively in the design
stage to optimize the component structure, adjust the process parameters and the tool surface. Some common softwares
used in designing and manufacturing field of composites materials are briefly introduced and some problems in the simulation
about temperature field distribution and curing deformation are reviewed and discussed.
2017 Vol. 60 (4): 47-53 [Abstract] ( 267 ) HTMLNew PDF (1428 KB)  ( 1341 )
54 Simulation of Aircraft Components Assembly Line
QU Qi1, JIA Xiaoliang1, ZHENG Zhiyuan2, LIU Guilin2
DOI: 10.16080/j.issn1671-833x.2017.04.054
Aircraft assembly is the key process for modern aircraft manufacturing. Using simulation methods in assembly
line planning can pre-evaluate the production capacity and equipment utilization, optimize and solve the assembly
line bottlenecks. In this paper, the assembly line of fuselage components of aircraft is studied. The assembly line model of
fuselage components of aircraft is established by means of assembly line simulation method. The problems of capacity ,
bottleneck and blance rate of assembly line are simulated and optimized.
2017 Vol. 60 (4): 54-59 [Abstract] ( 413 ) HTMLNew PDF (1792 KB)  ( 1221 )
       NEW VIEWPOINT
60 Interaction Design Technology of Knowledge-Based Aircraft Manufacturing Coordination Route
Lü Zhengwei, TAN Changbo, AN Luling, WANG Zhiguo
DOI: 10.16080/j.issn1671-833x.2017.04.060
Aircraft manufacturing coordination route is an important process file, which connects the interchangeable
coordination scheme designing with tolerance distribution. The digital design of aircraft manufacturing coordination route
has important significance for computer aided tolerance design and the implementation of aircraft digital process. First, we
classify the design knowledge of aircraft manufacturing coordination route and build the knowledge representation model
and use the knowledge by reasoning technology. Then, we create figures library of manufacturing coordination units and
design manufacturing coordination route interactively using intelligence capturing technology. Finally, the information
model of aircraft manufacturing coordination route is designed and coordination process files for the standardization of the
tolerance allocation are generated automatically, which provide support for the computer aided tolerance design.
2017 Vol. 60 (4): 60-66 [Abstract] ( 355 ) HTMLNew PDF (1900 KB)  ( 1039 )
       RESEARCH
68 Research on the Knowledge System of Aviation Parts Manufacturing Based on Group Technology to High Efficient Process Design
LI Nairui1, CHEN Xinghu2, GUAN Yujie1, ZHANG Kanghua1, YANG Wucheng3, LIANG Yong1
Aiming at the transformation requirements of aviation enterprises on new and intellectualized production
mode in the future, and the production status of ‘multi variety and small batch’, the design of the manufacturing knowledge
system, that based on Group Technology is studied. The development frame is proposed, including types, character definitions,
character codes, logical relations of characters of parts, and standardization of basic process, applied logic of system,
the operational frame of system. The development of the system would not only provide the standardized datum and
knowledge of basic process for the transformation of production mode in the future, but also boost the efficiency of process
design of aviation parts.
2017 Vol. 60 (4): 68-72 [Abstract] ( 121 ) HTMLNew PDF (933 KB)  ( 595 )
73 Experiment on Surface Integrity of Polishing for Titanium TB6
CUI Wei1, LI Xun1, SU Guihong2, HU Chaopeng2
DOI: 10.16080/j.issn1671-833x.2017.04.073
According to the question that TB6 titanium alloy parts depending on manual polishing, a polishing method
utilizing the wool wheel is presented. This paper studies the influence of polishing parameters on surface roughness,
surface hardness, and surface residual stress. Polishing parameters are optimized, and this paper has optimized out a set of
polishing parameters: linear velocity vs=19.63m/s, feed speed vf =300mm/min, precompression depth ap=0.5mm, processing
line width w=0.5mm, by which wool wheel polishing can effectively remove the milling pattern, enable the surface roughness
Ra=0.15μm, and ensure that the residual stress of the polished surface is residual compressive stress.
2017 Vol. 60 (4): 73-78 [Abstract] ( 161 ) HTMLNew PDF (3012 KB)  ( 513 )
79 Study on High Voltage Electron Beam Welding Frame of TC4-DT
GAO Feng, NI Jiaqiang, GUAN Feng
DOI: 10.16080/j.issn1671-833x.2017.04.079
High voltage electron beam frame process of TC4-DT material is studied. High voltage electron beam
welding technology is used to realize the hot forming process of refractory metal with complex structure and large thickness,
and the process, microstructure, mechanical properties and microstructure are analyzed systematically. The experimental
results show that the formation of the electron beam is relatively flat, the shape is narrow, the tensile and impact
strength are higher, and the tensile strength is stronger than that of the base metal, but the impact toughness is decreased.
Meanwhile, the weld joint microstructure of lamellar structure has no obvious boundaries, which ensure the continuity of
weld microstructure, and grain refinement, staggered.
2017 Vol. 60 (4): 79-82 [Abstract] ( 209 ) HTMLNew PDF (2022 KB)  ( 534 )
83 Research on Fatigue Experimental of Interference Fit Riveting of Titanium Alloy Structure
CHEN Yunquan1，CAO Zengqiang2, QIN Longgang1, CHEN Lili1, YAN Li1
DOI: 10.16080/j.issn1671-833x.2017.04.083
Interference-fit is a well-known technique for improving the fatigue life of joints, which has been widely
adopted in aerospace manufacturing industry. The excellent performance of titanium alloy has greatly improved its application
in aerospace structures. However, interference-fit riveting in our country is still limited to aluminum alloy structures,
there is few studies on the interference-fit riveting in titanium structures. Fatigue experiments were carried out on titanium
structures with different interference-fit levels in this paper. It was found that interference-fit riveting can greatly improve
the fatigue life of joints compared with conventional riveting. The increment of fatigue life by interference-fit riveting becomes
more obvious at lower level loads. Processing parameters, such as the gap between hole and pin, also have great effects
on the fatigue life.
2017 Vol. 60 (4): 83-86 [Abstract] ( 178 ) HTMLNew PDF (1604 KB)  ( 690 )
87 Effect of Dispersing Methods on the Properties of Carbon Nanotubes/Epoxy
ZHAO Yanwen1, XU Wei2, CHEN Jing1, YE Hongjun1, BAI Shucheng1, JIANG Wei1
DOI: 10.16080/j.issn1671-833x.2017.04.087
In this article, epoxy resin enhanced with carbon nanotubes(CNTs) was dispersed by ultrasonic disruption
and ultrasonic agitation. TEM was used to analyze the morphology of CNTs before and after two different dispersing presses.
Rheological property, curing behavior, thermal behavior and mechanic behavior was compared using two dispersing
method. The results show ultrasonic agitation can shorten the CNTs and improved their dispersion state in the resin, there is
barely difference of curing behavior and rheological property between ultrasonic disruption and ultrasonic agitation, but the
methods have influence on mechanic behavior and Tg.
2017 Vol. 60 (4): 87-91 [Abstract] ( 228 ) HTMLNew PDF (3015 KB)  ( 901 )
92 Dwell Behavior of Ceramic Matrix Composites During the Projectile Penetration
GAO Jubin1,2, WANG Yangwei3, 4,WANG Fuchi3,4, SUN Jianzhuo1,2
DOI: 10.16080/j.issn1671-833x.2017.04.092
With the purpose of increasing application value and revealing the ballistic mechanism of ceramic matrix
composites, it is necessary to investigate dwell phenomenon and ballistic performance of the material in the process
of projectile penetration. In this paper, the behavior law of dwell is studied by utilizing numerical simulation method. The
dwell behavior of aforementioned materials is investigated. Stress level and damage evolution of ceramic composites during
dwell process are analyzed, and compared to common armor ceramics at the same condition. It is concluded that energy
dissipated during dwell process reaches 845J in ceramic composite, respectively increasing by 46.0%, 30.2% and 35.7%
to the energy of B4C, SiC and AD99 Al2O3. The damage evolution in ceramic during dwell process is different from that
in ceramic and full damaged composites can bear higher compression load than ceramics in the same state. As a result, the
damage energy dissipation of composites accounts for 23.9% of the total dwell energy dissipation, which is almost twice as
much as that dissipated in ceramic.
2017 Vol. 60 (4): 92-96 [Abstract] ( 293 ) HTMLNew PDF (1910 KB)  ( 957 )
97 Application of Automatic Tape Laying Technology in the Composites Wing Skin
HUANG Dangming, NIE Haiping
DOI: 10.16080/j.issn1671-833x.2017.04.097
This text is about to analyze the structure and material of the composites wing skin of a certain type airplane
and make tape laying project. Combined with the accurate controlling design, parallel and cross laying, automated
placement and laser projection, and the automatic blanking technology, it successfully applied the tape laying technology
to produce composites wing skin, which is accepted by the internal quality test, and meets the requirements of the tape gap
and surface quality, laying a solid foundation for the laying machine technology application in composites.
2017 Vol. 60 (4): 97-100 [Abstract] ( 198 ) HTMLNew PDF (1256 KB)  ( 855 )
101 Research on the Fast and High Accuracy Adaptive Method to Register Blank Points and CAD Model
LI Huan1, CHEN Zhitong1, QU Xinhe2
During the accuracy registering for scanning point set of complex aviation casting and forging blank part
and the CAD model, the vast amounts of point set, lots of model faces and no relevance between the points and CAD model
surfaces can bring amounts of calculation for the registration algorithm, and restrict the processing efficiency severely. In
order to improve the efficiency of registration, this paper proposes a fast and high accuracy adaptive method to register
blank points and CAD model. This method uses registration surface to extract the registration points, and the correspondence
between point and surface can be built by the way, and classifies registration surfaces, and then gradually increases
quantity of points and surfaces to the precise registration which uses ICP algorithm. Finally, the efficiency and reliability of
the algorithm are verified by the instance.
2017 Vol. 60 (4): 101-105 [Abstract] ( 106 ) HTMLNew PDF (1773 KB)  ( 407 )
106 Application of Net Assembly Technology on Aircraft Composites Component
WANG Xin, ZHANG Yi, ZHAO Ruixia
DOI: 10.16080/j.issn1671-833x.2017.04.106
The net assembly technology is presented in the process of composites component of aircraft. Error accumulation
is reduced and coordination accuracy is improved with digital quantity transfer in the process of product design
and manufacturing. In order to improve the assembly accuracy, the measuring device, such as laser tracker is applied, the
assembly accuracy and tolerance distribution is adopted with the stage of assembly process design. Taking an composites
component as the typical research structure of composites fuselage, the process flows and methods of net assembly technology
is defined. The method can realize one time clamping, processing and without repeated assembly of the parts, so that
the assembly quality has good stablility.
2017 Vol. 60 (4): 106-109 [Abstract] ( 230 ) HTMLNew PDF (1343 KB)  ( 778 )
  Notices
· 'Aeronautical Manufacturing technology ' is included in EI database
· China Science Citation Database (CSCD)
· Chinese S&T Journal Citation Reports (CJCR)
· World Journal Clout Index (WJCI) Report of Scientific and Technological Periodicals
· Supported in China Science and Technology Journal Excellence Action Plan
· Aeronautical Manufacturing Technology ranked No. 3 in Chinese S&T Journal Citation Reports (CJCR)
· 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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