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  • 1  Development of Fibers as Radar Wave Absorbers
    2003, 33(6).
    [Abstract](2819) [HTML](202) [PDF 203.39 K](9155)
    2  Temperature Dependence of Specific Heat Capacity of Solid Materials
    徐辉 邓建兵 沈江立
    2011, 41(5).
    [Abstract](2246) [HTML](337) [PDF 1.23 M](7777)
    Based on the analysis of specific heat capacity of different solid materials, the relationship between
    specific heat capacity of solid materials and temperature is studied and the model is built. As the example of Mo,Al2O3,graphite,W,Si3N4 and SiC, the model on specific heat capacity with temperature has been verified. The results indicate that the relative deviation between calculated and standard data is not exceeding 2%.
    3  Pyrolysis Mechanism of PICA Phenolics
    LIU Yunzhao SHI Jianjun WANG Yun FENG Zhihai YANG Yunhua
    2016, 46(6):68-73, 78.
    [Abstract](4619) [HTML](255) [PDF 4.29 M](6819)
    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.
    4  Mechanical Properties of Pure Aluminum Alloys at Cryogenic Temperatures
    [Abstract](4563) [HTML](818) [PDF 281.05 K](6812)
    5  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](5358) [HTML](4777) [PDF 769.25 K](6592)
    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.
    6  Application of Impedance Matching Techniques in TheStructure Design of Radome
    2015, 45(4):16-18.
    [Abstract](2024) [HTML](227) [PDF 914.53 K](6067)
    In the hypersonic flight conditions,the radome will have to face the contradiction between the mechanical,
    thermal and electrionics in electrical structure design. In order to solve this contradiction,this paper apply
    the impedance matching techniques,introduce the permittivity matching layer between the mechanical layer and the
    heat insulation layer. Using this techinque,the electrical property have been significantly improved based on satisfying
    the mechanical property and the thermal property. The application of this techniques can provide a feasible technical
    way for traditional area of electrical structure design, and can effectively solve the bottleneck problem of designing
    high temperature radome and other high performance radome.
    7  Analyses on Current Developments of Accelerated Aging Test Standards of Non-Metallic Materials
    LIANG Xiaofan LIANG Hongtao ZHANG Xinlan ZOU Shiwen
    2017, 47(3):6-9. DOI: 10.12044/j.issn.1007-2330.2017.03.002
    [Abstract](3586) [HTML](4238) [PDF 794.69 K](6004)
    The aging of non-metallic materials and products was one of the determining factors of the weapons' lifetime.The existing accelerated aging test standards of non-metallic materials are introduced in this article,and the similarities and differences between these test standards are analyzed.The conceptions of the development trends of accelerated aging tests are also proposed.
    8  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](4763) [HTML](3304) [PDF 1.33 M](5916)
    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.
    9  Measuring and Analyzing of Drilling Temperature for Carbon Fiber Reinforced Composites
    [Abstract](2353) [HTML](272) [PDF 193.51 K](5895)
    10  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](3940) [HTML](4420) [PDF 2.61 M](5803)
    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.
    11  Research Progress of Ti Products Fabricated by Hot Isostatic Pressing(HIP)
    ZHANG Xuhu XU Guihua SUN Yanbo
    2016, 46(6):6-10.
    [Abstract](3659) [HTML](203) [PDF 4.35 M](5695)
    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.
    12  Developments of Coating Materials in the Thermal Protection System of Spacecrafts
    WANG Kaishi KUANG Songlian
    2016, 46(6):1-5.
    [Abstract](4505) [HTML](229) [PDF 2.74 M](5590)
    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.
    13  Research Status of Thermal Protection System and Thermal Protection Materials for Aerospace Vehicles
    XING Yajuan SUN Bo GAO Kun WANG Zhenhe YANG Yi
    2018, 48(4):9-15. DOI: 10.12044/j.issn.1007-2330.2018.04.002
    [Abstract](3456) [HTML](6364) [PDF 818.20 K](5225)
    With the development of space technology, the aircraft flight speed is much higher and the service environment is even worse. The effective thermal protection system is one of the key systems to ensure the safety of aircraft flight. In this paper, the application status of passive thermal protection system, active thermal protection system and semi-passive thermal protection system on the aerospace vehicles are reviewed. And the application and development of five kinds of thermal protection material in the aerospace field, including metal matrix composites, carbon based materials, ceramic matrix composites, resin matrix composites and aerogel materials are mainly introduced. Finally the future developments of the thermal protection for aerospace vehicles are prospected.
    14  Status and Development of Foreign Study on New Stealthy Materials
    [Abstract](2337) [HTML](148) [PDF 109.45 K](5138)
    简单回顾了从二次世界大战至今几十年间,国外隐身材料的发展历程 ;系统综述了国外在陶瓷材料、导电高分子材料、晶须材料、纳米材料、手征材料等新型隐身材料研究方面所取得的进展;从耐高温隐身材料、智能隐身材料、等离子体隐身三个方面入手, 重点介绍了国外近年来在隐身材料领域的最新进展;并且指出了隐身技术未来的发展方向.
    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](3392) [HTML](2267) [PDF 1.42 M](4748)
    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  Status and Development of Study on Infrared Stealthy Materials
    2001, 31(4).
    [Abstract](2102) [HTML](242) [PDF 116.69 K](4742)
    17  Heat-Conduction Theories of Powder-Filled Polymer Composites
    2008, 38(2).
    [Abstract](1560) [HTML](173) [PDF 546.12 K](4635)
    18  Progress in Joining of Alumina Ceramics to Metal
    李卓然%Fan Jianxin%冯吉才
    2008, 38(4).
    [Abstract](1791) [HTML](158) [PDF 483.71 K](4422)
    19  A Review of Vibrating Assisted Drilling on CFRP
    JIAO Feng QI Jialiang WANG Xiaobo WANG Xiaoliang
    2017, 47(3):1-5. DOI: 10.12044/j.issn.1007-2330.2017.03.001
    [Abstract](2758) [HTML](2192) [PDF 1.20 M](4259)
    This paper reviews the property of the CFRP firstly,then summaries the defect of drilling fiber laminated material and the available solutions.In the second part,the characteristics of vibrating assisted machining(VAM)and vibrating assisted drilling(VAD)mechanism of decreasing defect during processing are introduced.In the last part,the paper reviews the development of vibrating assisted drilling CFRP.
    20  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](4282) [HTML](2481) [PDF 3.64 M](4225)
    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.

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