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2021 Vol. 64, No. 11
Published: 2021-06-01
FEATURE
FORUM
C0NTENTS
COVER STORY
APPROACHING SCIENCE
SPECIAL TOPIC
 
       FEATURE
14 Research and Application Progress of Key Technologies for Composites Cryogenic Tanks
WU Zhanjun,CHEN Duo,LI Shichao,CUI Yunguang,LI Juanzi,YUAN Yuhuan2, WANG Hongyu,LIU Xin
DOI: 10.16080/j.issn1671-833x.2021.11.014
Using polymer matrix composites to make cryogenic propellant tank of launch vehicle can significantly improve the launch capability of launch vehicle and reduce the launch cost. Not only must polymer matrix composites used in these applications be very structurally efficient, they must also contain extremely volatile cryogenic propellants. These requirements put forward high requirements for materials selection, tank structure design and manufacturing process. In this paper, the current research status of polymer for cryogenic use and the application of advanced composites manufacturing technology in composites cryogenic tank are summarized. Moreover, future research direction has been proposed to promote the practical engineering application of composites cryogenic tanks.
2021 Vol. 64 (11): 14-23 [Abstract] ( 227 ) HTMLNew PDF (59071 KB)  ( 147 )
       COVER STORY
24 Application and Development for Composite Primary Structure in Large Aircraft
MA Zhiyang, GAO Limin, XU Jifeng
DOI: 10.16080/j.issn1671-833x.2021.11.024
Application of composite primary structure has become a trend in large aircraft. This paper introduces the using of composite primary structure in large aircraft for the main commercial aircraft manufacturer, such as Boeing Co., Airbus Co., and COMAC, etc. Recently, the manufacturing technology of composite primary structure has been changed from the prepreg of manual placement and automated tape laying to automated fiber placement. The advanced liquid forming process of composite, as a kind of out-of-autoclave process, has been paid more and more attentions because of its huge potential that included complex-shaped and integral manufacture, lower cost of equipment, lower energy consumption and cost-cutting of manufacture.
2021 Vol. 64 (11): 24-30 [Abstract] ( 267 ) HTMLNew PDF (3304 KB)  ( 996 )
       FORUM
34 Load-Bearing Performance and Structure Optimization for Kagome Grid Satellite Cylinder Made by Filament Winding
SUN Shouzheng,SUN Tianfeng,CHEN Weiqiang, FAN Dongxing,HAN Zhenyu,FU Hongya
DOI: 10.16080/j.issn1671-833x.2021.11.034
Cylinder is the main bearing component of a satellite, which plays a major role in the load-bearing performance of the whole structure. Due to lightweight and high strength, Kagome grid satellite cylinder made by filament winding is commonly used in satellite cylinder. However, the structural parameters are coupled with each other in the design of the grid structure, and the effect of the parameters on the load-bearing performance of the cylinder is unclear. In this paper, the structure optimization of the Kagome grid satellite cylinder is studied. The finite element method is used to analyze the load-bearing performance of the cylinder under the working conditions for the satellite. Furthermore, the relative independence design conception regarding spiral rib and ring rib is put forward. Combining the parametric modeling strategy, the effect of each structural parameter on the load-bearing performance is obtained. With the loadbearing performance and mass as the main optimization objectives, the structural parameters of the cylinder are optimized using the multi-objective genetic algorithm. Also, the strength and buckling performance of the optimal structure are analyzed. The results show that the mass of the optimal structural is reduced by 21.2%, and the mechanical properties meet the specific working conditions of the satellite. Finally, the self-developed desktop winding machine is used to wind the cylinder.
2021 Vol. 64 (11): 34-40/49 [Abstract] ( 125 ) HTMLNew PDF (8700 KB)  ( 65 )
41 Advance in Automated Fiber Placement Technology on Continuous Fiber Reinforced Thermoplastic Resin Matrix Composites
WANG Kai, LIU Hansong, ZHAO Yan
DOI: 10.16080/j.issn1671-833x.2021.11.041
Continuous fiber reinforced thermoplastic resin matrix composites have unique advantages such as excellent mechanical properties, wide operating temperature range, possible for secondary processing, etc., which have made great development in aviation and other fields. In order to further improve the production and processing efficiency of this kind of material, the automatic processing technology represented by the automated fiber placement technology has become the current research hotspot. Based on the introduction of the concept of automated fiber placement technology and the relevant material systems of continuous fiber reinforced thermoplastic resin matrix composites, this paper summarized the research and application status of automated fiber placement technology at home and abroad, and focused on the current research hotspots and research progress of automated fiber placement technology.
2021 Vol. 64 (11): 41-49 [Abstract] ( 155 ) HTMLNew PDF (4768 KB)  ( 863 )
50 Comparative Study Between CF/PEKK Thermoplastic Composite by Hot-Press Molding and CF/PEEK Composite Using Automated Fiber Placement Process
LIU Ya’nan, LIU Chenxiao, ZHU Minghao, LI Laixin, FENG Rongxin
DOI: 10.16080/j.issn1671-833x.2021.11.050
In this paper, adopting CF/PEKK and CF/PEEK thermoplastic composites as research objects, a preliminary comparative study were conducted between the two systems using corresponding process of low-cost hot-press molding and automated fiber placement (AFP) process. The basic characteristics, obtained composites quality and properties of two thermoplastic composites were explored and analyzed. Firstly, hot press molding process of CF/PEKK system with a prepreg width of 305mm was optimized, which showed that its short beam strength is more affected by molding pressure rather than cooling rate. A satisfactory CF/PEKK composite was fabricated using a process with molding pressure of 2.0MPa, heating temperature of 370℃, and cooling rate of –15℃/min, generating a short beam strength up to (135.65±4.72)MPa, with fiber volume fraction of 61.8%. Meanwhile, a novel two step in-situ AFP combined with hot press molding process was preliminary explored using 6.35mm width CF/PEEK narrow thermoplastic prepreg. It is found that obtained CF/PEEK laminates using same process parameters revealed satisfactory surface and internal quality and similar failure mode to that of CF/PEKK system, while showed lower short beam strength and different micro-scale failure behavior. The research results can provide basic data and technical reference for the material and process selection of thermoplastic composite used in future aviation structures.
2021 Vol. 64 (11): 50-57/68 [Abstract] ( 125 ) HTMLNew PDF (30660 KB)  ( 507 )
58 Research on Process Design of Layered Self-Resistance Electric Heating for Thick Composite
ZHANG Bo， LU Yong,LIU Shuting,LIU Qiangqiang,HAO Xiaozhong
DOI: 10.16080/j.issn1671-833x.2021.11.058
Aiming at the thermal overshoot and thermal shell-core effect during the curing of thick composite, a layered self-resistance electric heating (L–SRE) process design method is proposed to alleviate the thermal overshoot, reduce the through-thickness temperature difference, and shorten the curing time. In this paper, a multi-physical coupling finite element model (FEM) of L–SRE process is established to predict the degree of curing and the through-thickness temperature distribution under specific layering process parameters. Based on the FEM, a radial basis neural network surrogate model (RBF) is established. The genetic algorithm (GA) is used to optimize the peak temperature of thermal overshoot, the maximum through-thickness temperature difference, and the curing time during the whole process to obtain optimal parameters. Finally, the optimized multi-layer independent temperature control process parameters are obtained. Based on a multi-channel self-resistance electric heating (SRE) platform, L–SRE curing experiments are carried out. The experimental results show that the peak temperature of thermal overshoot using the new process is reduced to 132.8℃ below the glass transition temperature. Compared with the oven, the overshoot temperature is reduced by 19.7 ℃ , which is a 60.6% reduction; Compared with the integrated SRE and the recommended process of L-SRE, the overshoot temperature are reduced by 54.0% and 34.7% respectively. The curing time is reduced by nearly 33min, which is a 19.6% shorter. The optimized L–SRE process parameters can effectively reduce the thermal overshoot and improve the temperature uniformity through thickness.
2021 Vol. 64 (11): 58-68 [Abstract] ( 81 ) HTMLNew PDF (11781 KB)  ( 77 )
69 Study on Interlaminar Tensile Properties of Large Thickness Stitched Composites
YANG Hongyu, WU Ning, HAN Meiyue, ZHU Chao， CHEN Li
DOI: 10.16080/j.issn1671-833x.2021.11.069
In order to investigate the influence of the stitching process parameters on the interlaminar properties of large-thickness stitched composites, this paper prepared stitched composite specimens using a modified locking stitching technique combined with a vacuum-assisted resin infusion (VARI) molding process. The effects of the stitching spacing and prefabricated delamination position on the interlaminar tensile properties were tested using a universal material testing machine. The specimens were characterized by scanning electron microscopy (SEM) to determine the cross-sectional morphology after failure. The results showed that the interlaminar tensile properties of the specimens were best when the stitching spacing was 5mm×5mm and the prefabricated delamination position was at the depth of 17.5mm. The interlaminar fracture mode of the stitched composites was mainly presented as: fracture of the stitches after extraction from the matrix, direct fracture of the stitches within the matrix, and direct fracture of the stitches between the layers.
2021 Vol. 64 (11): 69-75/85 [Abstract] ( 83 ) HTMLNew PDF (18495 KB)  ( 64 )
76 Online Monitoring Method for Curing Degree of Aircraft Composite Components
SHEN Yan,LU Yong,LIU Shuting,HAO Xiaozhong
DOI: 10.16080/j.issn1671-833x.2021.11.076
Curing degree determines the final quality of CFRP components, while curing degree online monitoring is significant for guiding the curing process control of aerospace-grade composite components. Aiming at the actual demand for curing aircraft composite components with high-quality and high-efficiency, a curing degree monitoring method based on the reconstruction of heat dissipation characteristics is proposed, which implements the accurate and non-destructive online monitoring of CFRP components curing degree. According to the time-domain distribution characteristics of the difference between the input energy and the overall thermal energy change, the overall heat dissipation is reconstructed in real time so that the curing degree is directly monitored online. The effectiveness of the proposed method is verified by finite element simulation and actual curing experiments. The results show that the calculation error of the curing degree is 2.3% in the numerical simulation model and 5.0% in the actual curing experiments.
2021 Vol. 64 (11): 76-85 [Abstract] ( 117 ) HTMLNew PDF (3832 KB)  ( 211 )
       APPROACHING SCIENCE
86 Serving the National Strategic Needs and Leading the Development of Fiber Disciplines
2021 Vol. 64 (11): 86-87 [Abstract] ( 77 ) HTMLNew PDF (661 KB)  ( 36 )
       SPECIAL TOPIC
88 Experimental Study on Low-Frequency Vibration Drilling of Titanium Alloy/CFRP Laminate Structure
ZHANG Hui,LI Meiping,LI Haiwei,DU Jie,GUO Feiyan
DOI: 10.16080/j.issn1671-833x.2021.11.088
During drilling of Ti/CFRP stacks in traditional ways, damages and tool wear occur frequently. In this study, the parameters of low-frequency vibration (LFV) drilling were optimized to improve the drilling quality and tool life. The parameters of LFV drilling were optimized in two steps. Firstly, a group of optimal parameters were obtained by combing of different cutting parameters in orthogonal experiments. Then a small range of drilling parameters near the optimal parameters were selected and optimized again according to extra orthogonal experiments. By using the final optimized parameters, the validity of optimal parameters was verified by comparing of the traditional drilling results and the LFV drilling results. The results showed that the tool wear was improved distinctly when drilling with LFV method. Also, it helps to decrease cutting chip size while increasing hole quality and elongating tool life.
2021 Vol. 64 (11): 88-95 [Abstract] ( 122 ) HTMLNew PDF (8130 KB)  ( 90 )
96 Experimental Study on Axial Ultrasonic Vibration-Assisted Grinding of Particle-Reinforced Titanium Matrix Composites
WU Bangfu, DING Wenfeng, CAO Yang
DOI: 10.16080/j.issn1671-833x.2021.11.096
Ultrasonic composite processing technology was introduced to solve the problems of high grinding temperature, poor surface quality, low processing efficiency and the short service life of abrasive wheel during the grinding process of particle-reinforced titanium matrix composites (PTMCs). Some comparative experiments of conventional grinding and axial ultrasonic vibration-assisted grinding of PTMCs were carried out. The influences of grinding process parameters on grinding force, surface roughness and microhardness were studied, and the influence mechanism of ultrasonic vibration was deeply analyzed. The results show that: ultrasonic vibration can significantly reduce the grinding force, the normal grinding force is reduced by 11.7%–20.1%, and the tangential grinding force is reduced by 9%–19%. With the increase of material removal rate, the surface quality of the machined surface gradually deteriorates, but the surface roughness of ultrasonic grinding is smaller than that of conventional grinding, which because the ultrasonic vibration changes the self-sharpening performance of abrasive wheel and the trajectory of abrasive grain. Furthermore, because ultrasonic vibration reduces the grinding force and grinding temperature, ultrasonic grinding not only inhibits grinding burns to a certain extent, reduces the microhardness of the machined surface, but also improves the defects of the machined surface.
2021 Vol. 64 (11): 96-102 [Abstract] ( 80 ) HTMLNew PDF (8091 KB)  ( 55 )
  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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