Most downloaded articles
2003, 33(6).
Abstract:
对目前吸波材料中用的纤维吸收剂--碳纤维、碳化硅纤维、金属纤维等的吸波特性、改性方法作了回顾,得出不同纤维的混杂和采用异型纤维是得到宽、轻、薄、强的结构吸波材料的有效方法.
对目前吸波材料中用的纤维吸收剂--碳纤维、碳化硅纤维、金属纤维等的吸波特性、改性方法作了回顾,得出不同纤维的混杂和采用异型纤维是得到宽、轻、薄、强的结构吸波材料的有效方法.
2011, 41(5).
Abstract:
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%.
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%.
2000(4).
Abstract:
阐述了铝合金在低温下的力学性能随温度的变化规律：在低温下拉伸性能提高、韧性改善、疲劳强度增加，且介质不同铝合金表现出不同的力学性能。并分析了这些力学性能变化规律的机理，同时对在极低温下某些铝合金锯齿变形的现象、特征、形成机理以及对力学性能的影响作了分析说明。
阐述了铝合金在低温下的力学性能随温度的变化规律：在低温下拉伸性能提高、韧性改善、疲劳强度增加，且介质不同铝合金表现出不同的力学性能。并分析了这些力学性能变化规律的机理，同时对在极低温下某些铝合金锯齿变形的现象、特征、形成机理以及对力学性能的影响作了分析说明。
2016, 46(6):68-73, 78.
Abstract:
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.
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.
2017, 47(1):1-4.
DOI: 10.12044/j.issn.1007-2330.2017.01.001
Abstract:
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.
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.
2017, 47(3):6-9.
DOI: 10.12044/j.issn.1007-2330.2017.03.002
Abstract:
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.
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.
2017, 47(3):57-60.
DOI: 10.12044/j.issn.1007-2330.2017.03.013
Abstract:
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.
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.
2017, 47(1):13-19.
DOI: 10.12044/j.issn.1007-2330.2017.01.003
Abstract:
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.
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.
2016, 46(6):1-5.
Abstract:
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.
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.
2015, 45(4):16-18.
Abstract:
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.
2016, 46(6):6-10.
Abstract:
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.
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.
2000(5).
Abstract:
利用热像仪对碳/环氧复合材料高速钻孔时的钻削温度及温度场分布进行了系统的试验研究。实验结果显示，钻削热主要是由刀具后刀面与已加工表面之间的摩擦产生的。转速越高，钻削温度越高；进给量越大，钻削温度越低，但钻削温度一般不超过环氧树脂的玻璃化转变温度。
利用热像仪对碳/环氧复合材料高速钻孔时的钻削温度及温度场分布进行了系统的试验研究。实验结果显示，钻削热主要是由刀具后刀面与已加工表面之间的摩擦产生的。转速越高，钻削温度越高；进给量越大，钻削温度越低，但钻削温度一般不超过环氧树脂的玻璃化转变温度。
13 Research Status of Thermal Protection System and Thermal Protection Materials for Aerospace Vehicles
2018, 48(4):9-15.
DOI: 10.12044/j.issn.1007-2330.2018.04.002
Abstract:
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.
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.
2000(3).
Abstract:
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.
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.
2017, 47(1):59-61.
DOI: 10.12044/j.issn.1007-2330.2017.01.012
Abstract:
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.
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.
2001, 31(4).
Abstract:
综述了国内外红外隐身材料的发展历程,重点介绍了构成红外隐身材料的填料、树脂的研究现状以及近年来开始重点研究的红外兼容型多频谱隐身材料,并且指出了红外隐身材料的发展方向.
综述了国内外红外隐身材料的发展历程,重点介绍了构成红外隐身材料的填料、树脂的研究现状以及近年来开始重点研究的红外兼容型多频谱隐身材料,并且指出了红外隐身材料的发展方向.
2017, 47(1):37-41.
DOI: 10.12044/j.issn.1007-2330.2017.01.007
Abstract:
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.
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.
18 Ｃｏｍｐａｒａｔｉｖｅ Ｓｔｕｄｙ ｏｎ Ｐｒｏｐｅｒｔｉｅｓ ｏｆ Ｔｈｒｅｅ Ｔ７００ Ｇｒａｄｅ ＣａｒｂｏｎＦｉｂｅｒｓ ａｎｄ Ｔｈｅｉｒ Ｅｐｏｘｙ Ｍａｔｒｉｘ Ｃｏｍｐｏｓｉｔｅｓ
2016, 46(4).
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.
2017, 47(1):72-76.
DOI: 10.12044/j.issn.1007-2330.2017.01.015
Abstract:
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.
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.
2017, 47(2):1-4,13.
DOI: 10.12044/j.issn.1007-2330.2017.02.001
Abstract:
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).
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).
