• Volume 46,Issue 4,2016 Table of Contents
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    • >综述
    • Manufacturing Technology and Its Application of Aerospace Advanced Polymer Matrix Composites

      2016, 46(4).

      Abstract (3045) HTML (255) PDF 846.30 K (3413) Comment (0) Favorites

      Abstract:

      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


    • Progress on Boron Nitride Interface Coating Achieved by CVD

      2016, 46(4).

      Abstract (2854) HTML (209) PDF 2.73 M (2678) Comment (0) Favorites

      Abstract:

      The characteristics of BN and CVD are reviewed. Then the deposition process and the effect of deposi ̄
      tion temperatureꎬ source gases compositionꎬ heat treatment during the preparation by CVD are summarized. The stabili ̄
      zation of process conditions and the reaction mechanism will be the trend for the development of BN coatings. The meth ̄
      od to obtain uniform ꎬ controllable thickness and ordered BN interface coatings will be forced in the future study.

    • Preparation of Graphene and Its Application in Ceramic Matrix Composites

      2016, 46(4).

      Abstract (2064) HTML (253) PDF 1.13 M (2439) Comment (0) Favorites

      Abstract:

      Graphene with its excellent mechanicalꎬ opticalꎬ electricalꎬ thermal properties and unique two ̄di ̄
      mensional structure has become a research hotspot in the field of materials. In this paperꎬ the characteristics of gra ̄
      pheneꎬ different methods for graphene preparation and its applications in ceramic matrix composites were mainly intro ̄
      duced. The preparation methods including mechanical stripping methodꎬ chemical reduction methodꎬ chemical vapor
      deposition method and crystal epitaxial growth method.The application of graphene in the ceramic composite materials
      can significantly improve its physical properties.

    • >计算材料学
    • Finite Element Analysis of Mechanical Property of SMP Composite Shell Structure

      2016, 46(4).

      Abstract (1829) HTML (234) PDF 2.95 M (1966) Comment (0) Favorites

      Abstract:

      Based on provided three ̄dimensional SMP constitutive equationꎬ the mechanical properties of bending
      and expanding on SMP hinge structure have been modeled and simulatedꎬ with emphasize on shape memory behavior
      of the structure. The enhancement effect of the metal diaphragm on SMP hinge is further analyzed. The constitutive e ̄
      quations and finite element method can effectively describe the shape memory behavior of SMP hinge under the three ̄
      dimensional complex stress state.Simulated reverse bending moment is larger than the forward hinge bending moment
      and the moment ̄rotation curve has obvious nonlinear features.Metal film can effectively improve the stiffness and shape
      recovery force of the hinge structure.

    • >新材料新工艺
    • Radiation/ Ablation Flexible Thermal Protection Materials

      2016, 46(4).

      Abstract (1805) HTML (275) PDF 2.73 M (1829) Comment (0) Favorites

      Abstract:

      Thermal protect performance of flexible materials was improved by devising the method of thermal pro ̄
      tection. A radiation/ ablation alternate flexible thermal protection materials (FTPM) was designedꎬ which was composed
      of multi layer of composites of heat-resistant and evaluated by oxyacetylene ablation test. In order to eliminate the poor
      adhesion between the radiation layer and ablation layerꎬ the adhesion properties was evaluated by T peel test and SEM
      after modified by surface treatment. The results showed that new FTPM possesses much more excellent ablative perform ̄
      ance than conventional ablatorsꎬ because FTPM has more layers in good condition and lower temperature after ablation
      test. Adhesion properties were improved effectively by surface treatment and obtained the best with 5wt%.

    • Properties of C/ E Composites for Cryogenic Application

      2016, 46(4).

      Abstract (1634) HTML (277) PDF 1.28 M (2167) Comment (0) Favorites

      Abstract:

      For the application demand of composites under liquid N2 temperatureꎬ several carbon fabric/ epoxy
      composites have been prepared by RTM process.The flexural propertiesꎬ compression strengthꎬ interlamniar shear
      strengthꎬ and impact strength at 80℃ꎬRT and -196℃ have been tested.GⅠC and GⅡC at RT have also been tested.
      Compared with room temperatureꎬ the flexural strengthꎬ compression strength and impact strength of M40 ̄level braid ̄
      ing fabric/ R608-1 composites under -196℃ obviously increasedꎬ while the effect of cryogenic temperature on the
      modulus of composites was small. The effects of resin toughness on the strength and modulus of composites were smallꎬ
      while the effects of carbon fiber on the strength and modulus of composites were large. In any caseꎬ toughness of resin
      matrix and variety of carbon fabric could not change the trend of mechanical properties vs temperature. Besidesꎬ both
      toughness of resin matrix and variety of carbon fabric could affect the interlaminar fracture toughness of composites.
      And high ̄toughness resin matrix could improve the interlaminar fracture toughness more obviously. The GⅠC and GⅡC
      of M40 ̄level braiding fabric/ R608-2 composites was as high as 868 J/ m2 and 2 750 J/ m2ꎬrespectively. Howeverꎬ the
      Tg of composites with high ̄toughness resin matrix was relatively low.

    • Comparative Study on Properties of Three T700 Grade CarbonFibers and Their Epoxy Matrix Composites

      2016, 46(4).

      Abstract (3288) HTML (277) PDF 3.60 M (4090) Comment (0) Favorites

      Abstract:

      The tensile propertiesꎬ surface morphologyꎬ laminate mechanical properties and AGS cylinder axial
      compression stability of MT700 carbon fiber have been studied graduallyꎬ compared with T700-A and T700-B carbon
      fibers. The tensile strength of MT700 has catch up with T700-A and T700-B. The homogeneous groove on fiber sur ̄
      face could effectively improve its interfacial property and tensile ̄compress compatibility. Thereforeꎬ the compressive
      strengthꎬ interlaminar shear strength and flexural strength for MT700/603 are superior to T700-A/603 and T700-B/
      603. The maximum failure load and axial compression modulus of MT700/603 AGS cylinder are as high as 870 kN
      and 108.2 GPaꎬ respectivelyꎬ which have increased by 11.5% and 33.1% compared to T700-B/603. The results
      demonstrated that MT700 carbon fiber is suitable for preparing load ̄carrying component in aerospace structural com ̄
      posites.

    • Properties of A Mixed Fabrics Reinforced Composite

      2016, 46(4).

      Abstract (2002) HTML (263) PDF 2.39 M (2143) Comment (0) Favorites

      Abstract:

      A new type of mixed fabrics reinforced composite was madeꎬ using carbon and glass plain cloth/ epoxy
      prepregs. The tensileꎬbendingꎬshear mechanical properties and conductive property are tested.The results show that
      the mixed fabric enhanced composite has lower tensile and bending strength than the composite which was reinforced
      by the pure glass fabricꎬ but the modules are higherꎬ in -50 to 200℃. The shear test shows that both composites have
      the same interlaminal shear strength. Besidesꎬ adding the carbon fiber results is decrease in the composite density and
      but increase in propertyꎬ and broaden the application of the glass fabric enhanced composites.

    • Effect of Polyetherimide on Toughening T700/ Epoxy Composite Materials

      2016, 46(4).

      Abstract (1996) HTML (271) PDF 2.46 M (2012) Comment (0) Favorites

      Abstract:

      In this paperꎬ the toughening of the T700/ epoxy composite was studied by using the polyetherimide
      (PEI) as additive. Test results show that the toughness of epoxy resin composite was significantly improvedꎬ but the me ̄
      chanical properties and glass transition temperature were slightly decreased. Under the premise of satisfying the strengthꎬ
      the toughness of the composite was the best when the content of PEI was 20wt%ꎬ which was reaching 593.6 J/ m

    • Preparation and Performance of Highly ̄Flexible Prepreg With Low Surface Density

      2016, 46(4).

      Abstract (1747) HTML (223) PDF 1.79 M (2359) Comment (0) Favorites

      Abstract:

      The effects of viscosity of high toughness epoxy resin on prepreg process technique were investigatedꎬ
      and the effects of process parameters during film preparation and impregnation on prepreg quality were discussed. The
      highly ̄flexible prepreg with low surface density was successfully fabricated through hot ̄melt method.The physical prop ̄
      erties of high ̄flexible prepreg with low surface density were evaluatedꎬ which has a thickness of (25±5) μm and has
      stable quality and good manufacturability. Testing results showed that the mechanical properties of the composites
      made from the ultra ̄thin prepreg are enhanced especially for the interlaminar fracture toughnessꎬ interlaminar shear
      strength and flexural properties. Morphology observation indicated excellent interfacial properties of composites pre ̄
      pared from high ̄flexible prepreg with low surface density. 

    • Performance of Polycarbosilane With Different Molecular Weigh andIts Effect on Densification of C/ C-SiC Composites

      2016, 46(4).

      Abstract (2687) HTML (317) PDF 1.78 M (2701) Comment (0) Favorites

      Abstract:

      C/ C-SiC composites were prepared by CVD ꎬimpregnation and pyrolysis method using polycarbosilane
      (PCS) with four number average molecular weight as impregnant.The molecular weightꎬ softening pointꎬ molecular struc ̄
      ture and thermogravimetic performance of PCS were determinedꎬ and the distribution of pores were analyzed by means of
      mercury intrusion method .The results showed that the softening point and rate of conversion at 800℃ of PCS increased with
      increasing molecular weight of PCS. The pyrolysis process of PCS with four molecular weight grade were identicalꎬ and
      branch degree did not have significant difference. The integral densification efficiency of PCS with molecular weight 1 178
      and 1 333 was higher than that of PCS with molecular weight 1 550. The cumulative pore content of sample densified by PCS
      with molecular weight 1 178 was maximum after seven densification cyclesꎬ and that of sample densified by PCS with molec ̄
      ular weight 1 550 was minimum.When PCS with molecular weight 1 178 and 1 333 was used in previous five ̄cycles and mo ̄
      lecular weight 1 550 was used in other cyclesꎬ the material could be densified more efficiently.

    • Preparation and Properties of Continuous Carbon FiberReinforced Polyetheretherketone Prepreg

      2016, 46(4).

      Abstract (2210) HTML (244) PDF 3.06 M (2880) Comment (0) Favorites

      Abstract:

      Continuous carbon fiber reinforced polyetheretherketone (CF/ PEEK) prepreg was produced by slurry
      method. Processing temperatures and velocity were investigated.Thermal expansion properties and tensile properties
      were also experimented. SEM was used to observe the interface morphology of CF/ PEEK prepreg. The results indica ̄
      ted that the temperature distribution in pre ̄heating and melt ̄saturating districts are controlled by 110 to 130℃ and
      220 to 370℃.The prepreg velocity is 2 m/ min in order to get good CF/ PEEK prepreg. The thermal expansion property
      of CF/ PEEK prepreg is 0.5×10-6 / K in the temperature from -150 to +150℃ꎬthe maximum tensile strength is up to
      1.81 GPaꎬ and decreasing with fiber volume increasing.Scanning electron micrograph (SEM) confirms that the inter ̄
      face is good between carbon fiber and PEEK. The research tells us that the processing parameters are viable and the
      properties of CF/ PEEK prepreg are goodꎬ and can be used in engineering.

    • Processing Method of Polyimide Matrix Composites for 420℃ Application

      2016, 46(4).

      Abstract (1915) HTML (276) PDF 2.49 M (2298) Comment (0) Favorites

      Abstract:

      The chemical reaction characterization and rheological property of novel polyimide for 420℃ applica ̄
      tion were analyzed. The influence of processing parameters on the properties of composites were also investigated.The
      inner quality of composite was evaluated by ultrasonic C-scanꎬ microscopic analysis. Meanwhile the relationship be ̄
      tween void contents and ultrasonic absorption ratio was discussed to determine the ultrasonic inspect parameter. Re ̄
      sults showed that the resin and void contents could be effectively controlled by applying the pressure step by step. The
      ultrasonic inspect could be carried out by probe of 5 MHz and gain of 15 dB to evaluate the quality of composite with
      thickness of 2 to 3 mm. The polyimide composite prepared in this work exhibits excellent high ̄temperature mechanical
      properties at 420℃ꎮ

    • Effect of Carbon Nanotubes Modification on Interlaminal Properties ofC/ E Composite

      2016, 46(4).

      Abstract (1510) HTML (279) PDF 7.39 M (1354) Comment (0) Favorites

      Abstract:

      The effects of interlaminal properties of composite with resin and carbon fiber woven modified with
      carbon nanutubes grown on carbon fiber are investigated. The interlaminal shear strength and flexural strength of car ̄
      bon ̄epoxy composite with four kinds of carbon nanutubes grown and without carbon nanutubes are compared. The
      effects of interlaminal properties of canbon nanotubes on carbon ̄epoxy composite with the method of the canbon nano ̄
      tubes film combinated with carbon fiber are also studied. It is showed that the interlaminal properties of carbon ̄epoxy
      composite with four kinds of carbon nanutubes grown is worse than that without carbon nanutubes because the inner
      defects increase for overlong canbon nanotubes and the resin can not immerse in the carbon nanutubes because canbon
      nanotubes are overlong( >10 μm) and form “cage” due to arranging disorderly on the end leading to carbon nano ̄
      tubes playing no reinforcing effect. The canbon nanotubes filmꎬhowever well combined with carbon fiber and resinꎬ
      leading to the interlaminal shear properties improving 12%.

    • Processing of Fully ̄Wrapped Carbon FiberResin ̄Based Composite Square Tubes

      2016, 46(4).

      Abstract (1869) HTML (275) PDF 1.10 M (2068) Comment (0) Favorites

      Abstract:

      Filament winding is traditionally applied together with prepreg layer to prepared the square tube of the
      carbon fiber reinforced composite. To improve the manufacturabilityꎬ fully ̄wrapped process based on the small angle
      filament winding was studied in this paper. This work introduced the winding process and the design of the auxiliary
      frock. The mechanical properties of the prepared tubes by two above methods were measured. The results showed that
      both the mechanical properties and the Cv value of fully ̄wrapped composite are better than the traditional method. Es ̄
      peciallyꎬ for the fully ̄wrapped composites with 4°ꎬ the tensile strength and modulus are 899.74 MPa and 235.22
      GPaꎬ respectivelyꎻ the flexural strength and modulus are 823.57 MPa and 220.22 GPaꎬ respectivelyꎻ and the Cv val ̄
      ue is 2.8%. The 4° filament winding is the best choice to replace 0° overlay.

    • Precision Machining Mechanism of T800 Carbon Fiber Reinforced Polymer

      2016, 46(4).

      Abstract (2040) HTML (271) PDF 3.37 M (1815) Comment (0) Favorites

      Abstract:

      In this paperꎬ orthogonal cutting was used to investigate material cutting and surface forming process
      of CFRP composite materials under small cutting parameters. An intensive discussion was given about several key
      problems when machining CFRP for high precisionꎬ such as fiber orientationꎬ cutting parameter range and cutting
      edge radius. Experimental results indicate that CFRP behaves with notable anisotropy and cutting direction affects cut ̄
      ting process greatly. 0° and 135°cutting directions result low cutting force levelꎬ and 0° and 90° cutting directions
      generate improved surface quality. As to precise cutting of CFRPꎬ to reduce cutting force and improve surface qualityꎬ
      the 0° fiber orientation is advisedꎬ cutting speed is supposed to exceed 200 m/ minꎬ cutting edge radius should be
      sharpꎬ and cutting depth should exceed cutting edge radius.

    • Development of Large Temperature Difference Foam Sandwich Co ̄Bulkhead ofCryogenic Tank for New ̄Generation Launch Vehicle

      2016, 46(4).

      Abstract (2073) HTML (228) PDF 3.53 M (2195) Comment (0) Favorites

      Abstract:

      As an ideal layout scheme for launch vehicleꎬ co ̄bulkhead tank can improve the slenderness ratio of
      launch vehicleꎬ reduce structure weight and increase structure efficiency and carrying capacity of launch vehicle. This
      paper systematically studied the structure designꎬ key manufacturing technology and structural property of the alumi ̄
      num alloy panel/ polymethacrylimide (PMI) foam ̄sandwiched cryogenic tank co ̄bulkheadꎬ which successfully passed
      the air ̄tight testꎬ the low ̄temperature pressure test and the thermal insulation test. The single ̄bottom inner pressure
      was 0.54 MPaꎬ and the low ̄temperature pressure in coal oil tank and liquid oxygen tank were 0.40 MPa and 0.47
      MPa respectively. The co ̄bulkhead was not wrinkling or collapse after the testsꎬ and the temperature of the coal oil
      was higher than 17℃.The sandwiched co ̄bulkhead meets the using requirements of large temperature differenceꎬ light
      weight and no vacuum pumping for thermal insulation before launchingꎬ laying technological foundation for successful
      development of the new ̄generation launch vehicles. 

    • Precision Turning Technology of High Volume SiCp / Al Composite Material

      2016, 46(4).

      Abstract (1638) HTML (217) PDF 1.99 M (2287) Comment (0) Favorites

      Abstract:

      During the cutting process of high volume SiCp / Al composite materialꎬ the attrition of the cutter will
      lower the tool’s lifeꎬ thus leads to the increasing difficulty of the cutting processꎬ makes it more hard to control the fi ̄
      nal quality of the product. This paper conducted an experiment which is used the PCD cutter to turning the material
      and analyzed the processed surface of the material and monitoring the tool wear condition with scanning electron micro ̄
      scopeꎬ surface roughness measuring instrumentꎬ roundness measuring instrument and other equipment.The experiment
      results indicated that the material of the bladeꎬ the cutting speedꎬ the cutting depth and the feed rate are the 3 major
      factors that influence the final result. When the PCD blade is at 25 to 40 m/ min cutting speedꎬ 25 to 35 μm cutting
      depthꎬ and 25 μm/ r feed rateꎬ the quality of the processing comes the best. In this wayꎬ the machining efficiency and
      the quality of the processed surface can be significantly improvedꎬ with a result of getting a fine processed surface with
      0.58 μm surface roughenessꎬ 0.91 μm cylindericity.

    • Improvement in Air Duct Processing by Whole Structural Designand Vacuum Assisted Infusion

      2016, 46(4).

      Abstract (1834) HTML (273) PDF 2.56 M (1778) Comment (0) Favorites

      Abstract:

      Air duct is a structure for adjusting the temperatureꎬ humidity and pressure inner the sealed cham ̄
      berꎬ which requires the air duct has good thermal insulating property and pressure tightness. The air duct had subsec ̄
      tion structureꎬ which made it difficult to ensure the dimension and pressure tightness. The air duct was made by auto ̄
      clave moldingꎬ which required high cost and long period. To solve the problemsꎬ the subsection structure of the air
      duct was improved to a whole structureꎬ so the air duct had better pressure tightness. Vacuum assisted resin infusion
      (VARI) was chosen instead of autoclave molding to manufacture the air duct. The results of mechanical properties of
      composite made by the two processing methods showed little differentꎬ which indicated that the mechanical properties
      can meet the requirements with VARI processingꎬ and the production cost and cycle can be reduced.

    • >测试分析
    • Detection Method on Chemical Composition of Unknown Component

      2016, 46(4).

      Abstract (1993) HTML (303) PDF 1.92 M (2280) Comment (0) Favorites

      Abstract:

      With the detection technology of IR、GC-MS、EDS、XRDand TOF-MSꎬ the identification of the un ̄
      known substance was successfully obtained.This article introduced the test process in the laboratoryꎬ qualitative and
      quantitative analysis of the results.Finally the various test methods for identification of unknown material chemical
      composition were summarized .Generally the analysis of unknown component starts from the analysis of the microscopic
      functional group by means of infrared spectroscopyꎬand then with the help of chromatographic separation and purifica ̄
      tion technologyꎬfinally qualitative and quantitative analysis can be summarized by the X-ray diffractionꎬ spectrosco ̄
      pyꎬ mass spectrometry and other techniques.

    • >工程实践
    • 3D Digital Assembly Process for Rocket Body Cabin

      2016, 46(4).

      Abstract (1915) HTML (229) PDF 4.52 M (1977) Comment (0) Favorites

      Abstract:

      According to the characteristics of the traditional method of rocket cabin assembly process planning
      and path planningꎬ this paper introduces a 3D digital assembly process for rocket cabinꎬ a scheme of the system frame
      and assembly process for 3D digital assembly. In this paper the relationship of each link in the structure and design of
      digital assembly is discussed. Through the virtual assembly platform output assembly animation and viewꎬ a perfect da ̄
      tabase system is establishedꎬ realizing 3D visualization of rocket cabin assembly productionꎬ achieving the purpose of
      improving the accuracy and efficiency of assembly and shortening the assembly time.

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