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  • 1  Research Progress and Application Requirements of Lightweight Structure Materials for Aerospace Applications
    WANG Qun WANG Jingchao LI Xiongkui MENG Dehao GAO Yihang
    2017, 47(1):1-4. DOI: 10.12044/j.issn.1007-2330.2017.01.001
    [Abstract](4032) [HTML](2185) [PDF 769.25 K](3785)
    The main lightweight structure materials including lightweight alloy and composite materials for aerospace applications were introduced in the article. The development direction of the lightweight structure materials are analysed briefly combining the application requirements of aerospace.
    2  Mechanical Properties of Pure Aluminum Alloys at Cryogenic Temperatures
    [Abstract](3721) [HTML](818) [PDF 281.05 K](4028)
    3  Preparation and Properties of an Out-of-Autoclave T800/607 C/E Composite
    ZHOU Yu FAN Mengjin SHANG Chengyuan LING Hui SUN Hongjie
    2017, 47(3):57-60. DOI: 10.12044/j.issn.1007-2330.2017.03.013
    [Abstract](3682) [HTML](1094) [PDF 1.33 M](3443)
    The cure kinetics of the epoxy resin 607 for an out-of-autoclave(OoA) composite was investigated by differential scanning calorimetry(DSC),and the cure kinetic formula of the resin was established. The prepreg with dry fiber regions remaining and the OoA composites were prepared. The quality and properties of the T800/607 composite were studied. The results indicated that the T800/607 prepreg owed a tack life at room temperature over 30 days and the void content of the OoA composite is far below 1%. The short beam shear strength and flexural strength of the OoA composite are 96.7 and 1480 MPa,respectively, which can be compared with the autoclave cured ones.
    4  Pyrolysis Mechanism of PICA Phenolics
    LIU Yunzhao SHI Jianjun WANG Yun FENG Zhihai YANG Yunhua
    2016, 46(6):68-73, 78.
    [Abstract](3549) [HTML](255) [PDF 4.29 M](4312)
    The pyrolytic process and volatiles of PICA porous phenolics at different stages were investigated by TG-FTIR and PyGC-MS.The results demonstrated that PICA porous phenolics presented two evident weight loss processes.The desorption of small molecules of PICA porous phenolics took place during the first process and H2O,CO2,HOCH2CH2OH are the main volatiles.The molecular chain of porous phenolics broke up and phenols,benzene series,fused ring aromatics evolved during the second process and it is the main stage of thermal degradation. After high-temperature pyrolysis loose and porous char with a certain strength is formed by the combination of porous phenolics matrix with high porosity carbon fiber reinforcement.
    5  Developments of Coating Materials in the Thermal Protection System of Spacecrafts
    WANG Kaishi KUANG Songlian
    2016, 46(6):1-5.
    [Abstract](3530) [HTML](229) [PDF 2.74 M](2953)
    The aerodynamic heating environment for spacecrafts currently under development typically possesses the following characteristics:high enthalpy, high heat flux and long heating time. This in turn has lead to the shift of active research work of heat shield materials, e.g., phenolic-resin based composites, towards enhancing properties such as higher ablation resistance, good heat insulation and even lower densities. To overcome the limitation of materials’ intrinsic properties and to improve their performances, both ablative(resin based) and non-ablative(ceramic based) types of heat shield materials can be further optimized by applying functional coating materials on top of the ablation surface. This review has focused on the recent research effort on the coating material for different thermal protection systems and categorized them into two major types:ablative and non-ablative. Having obtained a comprehensive understanding about their pros and cons, a possible solution is proposed at the end of this article for resin-based ablative composites:coatings consist of silicon-based preceramic polymers that can be cured around the same temperature as phenolic resin but ceramized in-situ during flight.
    6  Research Progress of Ti Products Fabricated by Hot Isostatic Pressing(HIP)
    ZHANG Xuhu XU Guihua SUN Yanbo
    2016, 46(6):6-10.
    [Abstract](3282) [HTML](203) [PDF 4.35 M](3403)
    Due to its amazing properties, Ti alloys are widely used in aerospace and aerial industry. HIP powder metallurgy process, which is suspected to a proposal approach to solve Ti alloys’ fabrication problem, is investigated throughout the world. In this paper, it’s character, orgination and development is introduced. Meanwhile, the investigation, approvemnet and practical application of the process of Aerospace Research Institute of Materials & Processing Technology is also introduced.
    7  Current Applications of Isostatic Pressing Technology in Materials Processing Field
    JIANG Zhuoyu ZHANG Peng BAO Jianwen WANG Kejian
    2017, 47(1):13-19. DOI: 10.12044/j.issn.1007-2330.2017.01.003
    [Abstract](3258) [HTML](1873) [PDF 2.61 M](3215)
    The status of applications such as HIP technology in the fields of metals, metal matrix composites, inorganic non-metallic materials and polymer materials is discussed, and the simulation technology of the isostatic pressing is reviewed. At the same time, the development trend of composite molding process of the isostatic pressing technology and 3D printing technology is analyzed, and the future of isostatic pressing techniques is prospected.
    8  External and Internal Hydro-Proof Test and Simulation Investigation on Needling C/C Composite Cylinder
    HAN Xuequn LIU Qin LI Geng ZHENG Wei
    2017, 47(1):37-41. DOI: 10.12044/j.issn.1007-2330.2017.01.007
    [Abstract](3184) [HTML](704) [PDF 3.64 M](2293)
    The external and internal hydro-proof test investigation of the cylinder structures are developed in the present paper. The needling C/C composite cylinder sample preparation and the fixture are designed according to the testing condition. The stress distribution information of the structures is obtained during the test process. The 3D hydro-proof FEM simulation model is established to compare with the experiment results. The simulation results are in good agreement with the test results,which indicates the validity and accuracy of the FEM simulation model. The test and simulation conclusions can provide some important guidance for the nozzle carbon/carbon composite with cone structure design, material constitutive model parameter modification and structure safety tolerance prediction.
    9  Mechanical Properties of Electron Bean Welded Joints on 2219 T852 Transition Ring and T87 Shell Section
    HU Zhenggen HUANG Cheng CHANG Zhilong LIU Debo WANG Mingzheng
    2017, 47(1):72-76. DOI: 10.12044/j.issn.1007-2330.2017.01.015
    [Abstract](3180) [HTML](742) [PDF 2.11 M](2118)
    Based on the electron bean circular weld on 2219 T852 transition ring and T87 shell section used for tank, the normal and low mechanical properties of the electron beam welded joints in the segment level were tested, and the staggered amount,fracture types and microstructure of the welded joints were analyzed. The following conclusions can be drawn.The normal and low strength effect coefficient of the segment level electron beam welded joints on 2219 T852 transition ring and T87 shell section are 0.63, and relative to the normal temperature, the low temperature mechanical properties of welded joints have been improved. The staggered amount is inversely proportional to the mechanical properties of welded joints,and it has the most significant effect to elongation, and low temperature should help to ease the weakening effect of staggered to the mechanical properties of welded joints. Because of the uneven tissue and the discontinuous structure of the electron beam welded joints,especially T852 side heat affected zone with coarse grains,the T852 side heat affected zone and the roots of welded joints are the weak area of the electron beam weld, and welded joint is easy to fracture in the area.
    10  Ultrasonic C-scan Analyses and Nugget Diameter Measuring of Spot Welded Joints
    SUN Xinyu ZENG Kai ZHANG Long
    2017, 47(1):77-80. DOI: 10.12044/j.issn.1007-2330.2017.01.016
    [Abstract](3176) [HTML](903) [PDF 1.27 M](2559)
    The quality of spot welded joints was evaluated by the scanning acoustic microscope (SAM). The change characteristics of gray level of C-scan image were analyzed. The feasibility of evaluating the quality of spot welded joints and measuring the nugget diameter by using the change of the gray level was provided. And we analyzed the spot welded joints of 1.0 mm stainless steel under different welding parameters. The calculated values of nugget diameter are compared with the measured values by macrophotograph of samples. The results show that this method is available for measuring nugget diameter of the spot welded joints, and can avoid the influence of artificial factors and reduce production costs. The accuracy of testing result was verified by contrasting the metallographs of actual spot welded joints cross section.
    11  Process of C/SiC Composites Used in Space Mirror
    HUANG Luming ZHANG Changrui LIU Rongjun CAO Yingbin
    2016, 46(6):26-29, 63.
    [Abstract](3031) [HTML](256) [PDF 4.61 M](2265)
    The mirrors play a key role in the space optical system, and it has been developed to the fourth generation of C/SiC composites. C/SiCcomposites have become very important materials for light-weight mirrors because of the advantage of low density, high stiffness and strength, considerable flexibility in structural design and so on.In this paper, the characteristics of four generation of mirror were contrast, the preparation process and the structure design of C/SiC composites were summarized, the development of the C/SiC mirror at home and abroad is reviewed.
    12  Progress of Ablative Polymer Composite for Solid Rocket Motor Nozzle
    2017, 47(2):1-4,13. DOI: 10.12044/j.issn.1007-2330.2017.02.001
    [Abstract](3004) [HTML](923) [PDF 1.22 M](2586)
    The progress of materials and processings for ablative polymer composite is introduced in this paper. The materials include ablation-resistant matrix resins and reinforcement, the processings include die moldings, tape wraps, layups and resin transfer moldings (RTM).
    13  Defects Repair for Ceramic Insulation Tiles
    WANG Xiaoyan HU Zijun SUN Chencheng ZHOU Jiejie ZHANG Hongbo
    2017, 47(3):83-85. DOI: 10.12044/j.issn.1007-2330.2017.03.020
    [Abstract](2926) [HTML](1059) [PDF 2.44 M](2042)
    Ceramic insulation tiles with defects were repaired by introducing high-temperature ceramic powders, such as MgO, YSZ, Al2O3 and tile matrix powders. The microstructure, mechanical property and thermal insulation properties of tile before and after repair were systematically investigated. The results show that the powder containing tile matrix powders is the best method to repair the ceramic insulation tile. The part of the complement has good compatibility with the body, and the micro morphology is similar to remain porous network structure. After repairing, the density, thermal conductivity at room temperature and compressive strength of the samples are 0.24 g/cm3, 0.044 W/(m·K) and 0.58 MPa, respectively. After 1 200℃ and 30 min heat treatment, the complement and the tile body have good bonding,cracks,depressions and other defects free.
    14  Storage Life Evaluation Technology and Application for Missile Used Non-Metallic Materials
    BAI Tian ZHANG Huan ZOU Shiwen ZHANG Xinlan
    2017, 47(1):20-24. DOI: 10.12044/j.issn.1007-2330.2017.01.004
    [Abstract](2924) [HTML](807) [PDF 787.49 K](2719)
    The ageing of non-metallic materials was one of the most important factors which affected the storage reliability of missile. This article introduced the current research and application of storage life evaluation technology for missile used non-metallic materials at home and abroad, summarized the typical ageing models and lifetime evaluation methods for non-metallic materials, and predicted the future development of storage life evaluation technology for non-metallic materials.
    15  Tightening Characteristic of C/C Composite Material Bolt
    SUN Pengjun LEI Yongjun WU Hongwei AN Jun LI Xintao
    2017, 47(1):59-61. DOI: 10.12044/j.issn.1007-2330.2017.01.012
    [Abstract](2919) [HTML](752) [PDF 1.42 M](2714)
    In order to obtain the tightening characteristics of C/C composite material bolt, the tightening torque characteristics of C/C composite material bolt with different structures were studied in this paper. The research can include the variation trend of the torque coefficient K of the bolts in different combinations of gasket material, single nuts and double nuts, scribbling with adhesives and non-scribbling with adhesives. The ultimate torsional resistance of C/C composite material bolt was studied. The results show that the torque coefficient K of the bolts is different from that of the metal bolts. The scribbling with adhesives can obviously improve the clamping force.
    16  Composite Laminates Vibration Theory and Experimental Modal Analysis Based on Hammering Method
    LI Jufeng YANG Tao DU Yu NIU Xuejuan
    2017, 47(1):25-28,36. DOI: 10.12044/j.issn.1007-2330.2017.01.005
    [Abstract](2891) [HTML](767) [PDF 2.00 M](2566)
    Based on the theory of experimental modal analysis, the modal theory and testing system of composite laminates is established. Firstly, composite laminates of 150 mm×80 mm×3.75 mm (length×width×thickness) were built-up. By using DH5922N dynamic data acquisition instrument, the frequency response function and the excitation signal sensed by acceleration sensor and force hammer are obtained. And frequency response function is analysised in the dynamic signal analysis system DHDAS. The first and second natural frequencies were 323.103 Hz and 656.180 Hz respectively, and the shift values of each measurement point corresponding to the frequency were obtained. The experimental results show that the experimental theory and the equipment used in this paper can be used to accurately extract the modal information of composite laminates.
    17  Manufacturing Technology and Its Application of Aerospace Advanced Polymer Matrix Composites
    2016, 46(4).
    [Abstract](2777) [HTML](255) [PDF 846.30 K](2338)
    The manufacturing technology of aerospace advanced polymer matrix composites in China and their
    main raw materials have made great progress during past 30 years. The advanced polymer matrix composites have been
    widely applied in aerospace industry. It is comprehensively summarized in this paper that the recent progress of the main
    raw materials(matrix resin and reinforced fibers) and the main aspects of the manufacturing technology for aerospace ad ̄
    vanced polymer matrix composites in Chinaꎬ including composite forming technique(autoclaveꎬ resin transfer molding
    processꎬ filament windingꎬautomated fiber placement techniques ) and machining processing and assembly process tech ̄
    nique. The future development trends of aerospace advanced polymer matrix composites in China are discussed. Key words AerospaceꎬPolymer matrix compositeꎬManufactureꎬMachiningꎬAssemblyꎬProcessing

    18  Filament Winding of Microwave Absorbing Composites Cylinders
    WU Jian LI Buyun CHEN Qing CHEN Liang LIU Xiumei
    2017, 47(1):55-58. DOI: 10.12044/j.issn.1007-2330.2017.01.011
    [Abstract](2767) [HTML](736) [PDF 959.21 K](2437)
    Based on modern filament winding technology, processing property and puzzles are analyzed for the microwave absorbing composites cylinders. For winding layer including absorbers, a technique is adopted, which prepreg is prepared using double rolls for the same slot and double lines sandwich core, and absorbing composites cylinders are manufactured through wet filament winding. The results show the winding rules and the processing parameters can meet cylinders manufacture. The content of absorbers dispersed in the different prepreg well-proportioned can be controlled,and the microwave absorbing performance is excellent.
    19  Fracture Reason Analysis of Wind Turbine Blade
    HAN Lu YU Xiangtian WANG Ying XIE Guojun PANG Jincheng
    2017, 47(1):67-71. DOI: 10.12044/j.issn.1007-2330.2017.01.014
    [Abstract](2765) [HTML](854) [PDF 4.51 M](2241)
    The blade in the installation of test failed in the operating process,fault location is located in the root of blade.Through observation,testing and analysis of fault component,the reason blade produced by low cycle fatigue fracture is identified due to improper control of production process.The blade root curing is incomplete in local area,which causes the strength and stiffness of very low. Fiber beam between curing not completely of resin cannot will load effective of passed to near of fiber beam, so dang by fatigue load role in structure stress concentrated regional first occurred layered cracking, and extended until eventually lost stability fracture.The direction for improvement is pointed out.

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