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2021 Vol. 64, No. 8
Published: 2021-04-15
FEATURE
FORUM
RESEARCH
C0NTENTS
COVER STORY
APPROACHING SCIENCE
 
       FEATURE
14 Data Integration of Flight Control System Test in Final Assembly Phase Based on REST Architecture
HAN Bing,YANG Feng,WANG Ping,SHEN Jia,SUN Yi,WANG Libin,FANG Qiang,WEI Yanding
DOI: 10.16080/j.issn1671-833x.2021.08.014
In order to solve the problem that multi-source heterogeneous (MSH) data is difficult to integrate during the flight control system test process in final assembly stage, a MSH data integration service based on representational state transfer (REST) architecture is designed and implemented. First, the source and influence of MSH data in the flight control digital test in final assembly stage are analyzed, and based on this, the equipment integration experiment platform for the flight control system test in final assembly stage is constructed. Based on the REST architecture, the integration service of MSH data has been designed, so that different devices have a unified data interface, the problems of complex operation and data heterogeneity of the flight control test equipment are solved, and MSH data integration is realized. Finally, taking air data test set, single-axis rate turntable and radio altimeter exciters as examples, the effectiveness of the MSH data integration method in the digital test of the flight control in final assembly stage based on REST architecture is verified.
2021 Vol. 64 (8): 14-21 [Abstract] ( 159 ) HTMLNew PDF (1523 KB)  ( 279 )
       COVER STORY
22 Research Status and Prospect of Welding Repair Technology for Aero-Engine Blades
ZHUO Yimin, CHEN Yuanhang, YANG Chunli
DOI: 10.16080/j.issn1671-833x.2021.08.022
Aero-engine blades are subjected to complex and harsh environment in the long term. Due the extremely hostile temperature and pressure, blades are prone to various types of defects. Since the replacement of blades is exceedingly expensive, the research on repair and reconstruction of blade has enormous economic benefits. Aero-engine blades mainly contain nickel-based superalloy gas turbine blades and titanium-based compressor blades. Because of the difference in service environment and material, the defects of two types of blades are different, the repair method and the performance to be achieved after the repair are different. In this paper, the repair methods and key technologies adopted at the current stage for the common damage defects of the two types blades are analyzed, which aims at providing a fundamental guideline for high quality repair and remanufacturing of aero-engine blades.
2021 Vol. 64 (8): 22-28 [Abstract] ( 411 ) HTMLNew PDF (4762 KB)  ( 885 )
       FORUM
32 A Data-Driven Method for Machining Feature Recognition for Aircraft Structural Parts
LU Kai,LI Yingguang,LIU Xu,DENG Tianchi
DOI: 10.16080/j.issn1671-833x.2021.08.032
Machining feature recognition is an essential way to realize the integration of CAD/CAM, and is significant to improve the quality and efficiency of CNC machining of the aircraft structural parts, which contains plenty of complex interacting features with complex structure. Existing machining feature recognition methods require predefinition of feature interacting patterns before recognizing interacting features, which is difficult to meet the recognition requirements of complex interacting features of the aircraft structural parts. Therefore, a data-driven method for machining feature recognition for aircraft structural parts is proposed, which transforms the problem of machining feature recognition into a graph learning problem, and adaptively learns feature recognition rules from historical process data by constructing a graph neural network model. The proposed method breaks the limits of the pre-defined feature interacting patterns. With typical aircraft structural parts as test parts, the correct recognition rates of isolated features, interacting features and total machining features reach 98.11%, 94.62% and 96.18%, respectively, which verifies the effectiveness of the proposed method.
2021 Vol. 64 (8): 32-40/57 [Abstract] ( 131 ) HTMLNew PDF (4184 KB)  ( 290 )
41  Logic Modeling and PLC Program Design based on DEVS for Flexible Manufacturing System
WANG Bing, JIANG Haifan, DING Guofu
DOI: 10.16080/j.issn1671-833x.2021.08.041
Aiming at problems of complicated logic, long commissioning cycle and high commissioning cost in the design process of flexible manufacturing system control scheme, a virtual commissioning method based on experimentable digital twin was proposed. This method established the twin model of physical system in a layered manner, and established a three-layer logic model of equipment layer, unit layer, and system layer based on the extended form of discrete event system specification. The logic model was repeatedly verified and modified through simulation. The mapping rule from logic model to PLC program was established to realize the rapid design of PLC program. Finally, taking a FMS as an example, the process of logic modeling and PLC program design were demonstrated in detail. The feasibility and effectiveness of the proposed method were verified.
2021 Vol. 64 (8): 41-49 [Abstract] ( 123 ) HTMLNew PDF (5186 KB)  ( 393 )
50 Lean Production Line Planning for Airbus A220 Aircraft Door
LIU Min, WANG Dawei, YANG Yanrui, YANG Wubing
DOI: 10.16080/j.issn1671-833x.2021.08.050
In order to improve the assembly efficiency of Airbus A220 aircraft door production line and reduce the labor and man-hours, firstly, the assembly time data of door production line was measured by time measurement method based on lean thinking in this paper, and the number of tooling needed to improve the production capacity is determined; Secondly, the Spaghetti diagram was used to analyze the logistics trend of operators in the assembly process, and the possible waste phenomenon is analyzed. Based on the waste phenomenon and the characteristics of door assembly process flow, the door production line is arranged according to the principle of product clustering. At the same time, the layout form of the whole station serial and the local bottleneck station parallel are determined referring to the IE (industrial engineering) method, then the door lean production line is established. Finally, 3D rendering was conducted for the overall layout by 3ds Max software.
2021 Vol. 64 (8): 50-57 [Abstract] ( 213 ) HTMLNew PDF (5644 KB)  ( 787 )
58 Research on Key Technologies of Digital Twin-Oriented Intelligent Production Line Monitoring System
SUN Yuanliang, MA Wenmao, ZHANG Chao, SONG Yongjie, CUI Jing
DOI: 10.16080/j.issn1671-833x.2021.08.058
Traditional manufacturing management is often beset by the serious “Black Box” problem, that is the inability to grasp various types of information on-site in a timely manner, which causes the actual status of the site lagging behind the expected plan and further reduces efficiency and quality. To solve this problem, the key technologies of digital twin monitoring system were studied. A three-dimensional model of the production line was established in the virtual space, and the association mapping between the data and the model was established via the collection of realtime on-site data. And then, a virtual leadership cockpit was created presenting various status and performance boards to solve the transparency of the production site and to improve production efficiency and quality.
2021 Vol. 64 (8): 58-65 [Abstract] ( 198 ) HTMLNew PDF (1693 KB)  ( 877 )
       APPROACHING SCIENCE
66 Establish First-Class Disciplines in Textile Science and Engineering Breakthrough the Key Technology of Advanced Textile Structural Composites
2021 Vol. 64 (8): 66-67 [Abstract] ( 213 ) HTMLNew PDF (1524 KB)  ( 88 )
       RESEARCH
68 Surface Reconstruction and Deviation Analysis of Aircraft Body Based on Digital Twin
WANG Wei, MEN Yu
DOI: 10.16080/j.issn1671-833x.2021.08.068
A method of surface reconstruction and deviation analysis of aircraft body based on digital twin was proposed. Firstly, the real data was processed, including data collection, point cloud data grids and coordinate alignment, point cloud data division based on the characteristics. Then, twin model reconstruction method was designed combined with NURBS method, and model test was carried out by the proposed method. An application example to test the method is feasible and verifies that the method has a certain application value.
2021 Vol. 64 (8): 68-71/101 [Abstract] ( 120 ) HTMLNew PDF (4060 KB)  ( 412 )
72 Discussion on Layout Planning Method of Laser Radar Measurement Field in Aircraft Assembly
ZHOU Xinfang, XU Bin
DOI: 10.16080/j.issn1671-833x.2021.08.072
Laser radar can accurately measure the spatial contour of objects, which plays an important role in aircraft manufacturing. Due to the requirements of laser path accessibility, optical path distance, optical path incident angle and other parameters, the location of lidar must meet certain conditions. In this paper, firstly, the geometric constraint requirements of laser radar layout planning are established, and the realization method of collision interference is analyzed. Then, based on the spatial conic surface and curve, the representation method and planning method of the placement area of lidar are researched. Finally, in order to meet the engineering feasibility, the points of the layout specification of laser radar are deduced based on the grid method. The layout planning method implemented in this paper has a certain guiding significance for the location planning of laser radar measurement equipment.
2021 Vol. 64 (8): 72-77 [Abstract] ( 144 ) HTMLNew PDF (1360 KB)  ( 346 )
78 Research on Wrinkle Defects Inspection and Influence of Wrinkle Defects on Mechanical Properties
ZHANG Ting, HUANG Aihua, LI Xiangqian
DOI: 10.16080/j.issn1671-833x.2021.08.078
Wrinkles are common defects in laminated composite parts manufacturing, which usually have a large impact on parts’ performance. In this paper, effects of wrinkle angles on mechanical properties were studied by fabricating serials of CFRP specimens with different wrinkle angles. Finite element analysis of tensile and compressive failure of specimens with wrinkle defects was also carried out. Studies showed that wrinkle defects seriously affect the tensile and compressive strength of composites, the bigger wrinkle angles, the lower both tensile and compressive strength. A wrinkle with the angle 16.8° can reduce the tensile strength by 21% and the compressive strength by 36%. The test results match with the simulation results. Considering the detectability of wrinkle defects by NDT and the influence of wrinkles on mechanical performance in tests and simulation, the wrinkle tolerance for designing laminate composites is recommended to be 5°.
2021 Vol. 64 (8): 78-83 [Abstract] ( 147 ) HTMLNew PDF (6147 KB)  ( 358 )
84 Research on Multi-Step Hot Forming Process of TB8 Titanium Alloy Leading Edge Skin of Complex Shape Blade
SHI Wenxiang,ZHANG Wenliang,CHEN Minghe,XIE Lansheng,WANG Ning
DOI: 10.16080/j.issn1671-833x.2021.08.084
A certain type of hovercraft with complex curved blades has a special-shaped cross section at the leading edge skin. The torsion angle of the front and rear ends is so large that it’s difficult to form by one step. In order to achieve its accurate forming, a multi-step hot forming experiment is required. To obtain suitable experimental parameters, the material forming performance and part forming scheme were studied through high-temperature tension, stress relaxation experiments and finite element simulation. The results of experiments and finite element analysis show that the high temperature plasticity and stress relaxation of TB8 during hot forming can effectively avoid crack failure and suppress springback. Through multi-step hot forming, it is possible to achieve precise forming of 88.7° large twisted skin parts. After comparing with the deformation and springback distribution of the parts at different temperatures and stamping speed of the high-temperature ridge pre-bending, tip-bending and tail-bending, the optimized patameters are obtained that the forming temperature is 675℃ , the stamping speed is 30mm/min, and the maximum thinning of the skin parts during pre-bending is 0.92%. Based on the stress distribution of the parts in each forming step obtained by simulation, the stress relaxation time is determined according to the results of the stress relaxation experiment. The ridge pre-bending stress relaxation time is 15min, and the spring-back angle of the part is less than 3.5°. The high-temperature tip-bending and tail-bending after 10min stress relaxation, the average springback of the part is less than 0.5mm. The multi-step thermoforming has been used to produce the skin of complex-shaped blade leading edge, which can be accurately assembled with the blade.
2021 Vol. 64 (8): 84-91 [Abstract] ( 96 ) HTMLNew PDF (2345 KB)  ( 319 )
92 A Full-Discretization Method for Milling Stability Prediction Based on Third-Order Newton-Hermite Interpolation
HUANG Chao, YANG Wenan,HUANG Jiuchao,XIE Feifei,YANG Youcheng
DOI: 10.16080/j.issn1671-833x.2021.08.092
In milling processes, chatter usually results in poor surface quality, tool wear and even shorten the life of machine tool. In order to build the dynamic model of milling process using regenerative theory, a new full-discretization method based on third-order Newton-Hermite interpolation method is proposed in this study. The dynamic milling process considering regenerative chatter can be expressed as delay differential equations, then the transition matrix is constructed by using third-order Newton and Hermite interpolation of the state item and the time-delay term, respectively. Finally, the stability of the system was determined based on the Floquet theory, and the corresponding stability lobe diagrams are obtained. The numerical results obtained utilizing extensive simulation indicate that the convergence rate of the proposed method is faster than that of the first full-discretization method (1stFDM) and the third-order updated full-discretization method (3rdUFDM), and the discrete error of the proposed method is the smallest at the same of the discrete number. In addition, for single degree of freedom dynamic model, the proposed method is more efficient than the 1stFDM and the 3rdUFDM, and the computation accuracy of the proposed method is better than that of the 1stFDM and the 3rdUFDM. The experimental results show that the proposed method is effective for predicting the milling stability.
2021 Vol. 64 (8): 92-101 [Abstract] ( 103 ) HTMLNew PDF (1718 KB)  ( 303 )
  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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