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1Research Progress and Application Perspectives of 4D Printing
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2Progress on Self-Healing and Structure-Wave Absorbing Integration of Silicon Carbide Ceramic Matrix Composites
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3Novel Ceramic Materials for Thermal Barrier Coatings
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4Research Progress of Laser Shock Treatment in the Field of Material Forming
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5Recent progress of 4D printing technology
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6Application and Research Status of Alternative Materials for 3D-printing Technology
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7Application Potential of 4D Printing Technology in Development of Aircraft
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8Research Progress on Preforms of C/C Composites
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9Research Progress of Metal-Intermetallic Laminated Composites
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10Research Process in Plasma Spray Physical Vapor Deposited Thermal Barrier Coatings
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11Effect of Mo content on Microstructure and Mechanical Properties of IN718 Alloy
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12Research Progress in Preparation and Crystallization Technologies of Amorphous ITO Film
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13Additive Manufacture of Metamaterials: a Review
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14Recent Process and Application of Electrochromism
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15Effect of sintering temperature on microstructure and mechanical behavior of alumina-based ceramic shell by SLS
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16Effect of Rare Earth Y on Microstructure and Properties of Sn-58Bi Solder Alloy
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1First-principle Calculations of Mechanical Properties of Al2Cu, Al2CuMg and MgZn2 Intermetallics in High Strength Aluminum Alloys
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2Effect of Filler Systems on Properties of Fluororubber Vulcanized by Peroxide
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3Research Process in Plasma Spray Physical Vapor Deposited Thermal Barrier Coatings
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4Effect of Rare Earth Y on Microstructure and Properties of Sn-58Bi Solder Alloy
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52018-02-Catalog
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6Research Progress and Application Perspectives of 4D Printing
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7Research Progress in Preparation and Crystallization Technologies of Amorphous ITO Film
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82018-04-Catalog
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9Research Progress in Cemented Carbide with Co-Ni-Al Composite Binder Phase
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10Application and Research Status of Alternative Materials for 3D-printing Technology
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11Progress in Amorphous Transparent Conducting Oxide Thin Films
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12Current Study and Novel Ideas on Magnesium Matrix Composites
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13Failure and Protection of Thermal Barrier Coating under CMAS Attack
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14Research and Application Progress of Silicone Rubber Materials in Aviation
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15High Temperature Titanium Alloys：Status and Perspective
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16Progress on Self-Healing and Structure-Wave Absorbing Integration of Silicon Carbide Ceramic Matrix Composites
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Available online
, doi: 10.11868/j.issn.1005-5053.2019.000043
Abstract:
Carbon fiber reinforced polymer (CFRP) has been widely used in the aviation, space and automobile structural parts manufacturing due to its excellent physical and mechanical properties. However, the properties of CFRP materials with inhomogeneity and anisotropy are vastly different from metals. In the process of drilling, it is easy to produce delamination, tearing, burr and other defects, which seriously affect the quality of drilling. Therefore, drilling technology of CFRP-metal stacks has become a difficult problem in aircraft assembly process. This paper summarizes the researches of drilling mechanism of CFRP in recent years. The relationship between chip formation mechanism and fiber orientation angle is generalized. Meanwhile, the relationship between axial drilling force, drilling temperature and tool shape, workpiece material, process parameters is summarized. The causes, detection, evaluation methods and restraining measures of typical machining damage during CFRP drilling processes, such as delamination, burr and tearing are analyzed. The latest advances in material, geometric structure of CFRP drilling tools, and development of simulation technology of CFRP drilling process are expounded. It is also proposed that the establishment of accurate and reliable constitutive model is the key to the research of drilling simulation technology. The development trend of CFRP drilling technology is prospected by introducing new CFRP drilling technologies, such as variable process parameters drilling, robotic automatic drilling and suction-type internal chip removal drilling.
Carbon fiber reinforced polymer (CFRP) has been widely used in the aviation, space and automobile structural parts manufacturing due to its excellent physical and mechanical properties. However, the properties of CFRP materials with inhomogeneity and anisotropy are vastly different from metals. In the process of drilling, it is easy to produce delamination, tearing, burr and other defects, which seriously affect the quality of drilling. Therefore, drilling technology of CFRP-metal stacks has become a difficult problem in aircraft assembly process. This paper summarizes the researches of drilling mechanism of CFRP in recent years. The relationship between chip formation mechanism and fiber orientation angle is generalized. Meanwhile, the relationship between axial drilling force, drilling temperature and tool shape, workpiece material, process parameters is summarized. The causes, detection, evaluation methods and restraining measures of typical machining damage during CFRP drilling processes, such as delamination, burr and tearing are analyzed. The latest advances in material, geometric structure of CFRP drilling tools, and development of simulation technology of CFRP drilling process are expounded. It is also proposed that the establishment of accurate and reliable constitutive model is the key to the research of drilling simulation technology. The development trend of CFRP drilling technology is prospected by introducing new CFRP drilling technologies, such as variable process parameters drilling, robotic automatic drilling and suction-type internal chip removal drilling.
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Available online
, doi: 10.11868/j.issn.1005-5053.2019.000042
Abstract:
Electrochromic technology has been widely used in many fields, such as building windows and car rear-view mirrors. Ion storage layers (generally anodic electrochromic materials) are significant for improving the performance of electrochromic devices and realizing the application of the technology. Its role is to store and supply the ions needed for the color change reaction, maintaining the charge balance of the entire electrochromic process. At present, the most typical anodic electrochromic material is nickel oxide(NiO). The cheap NiO film has high coloration efficiency and large range of optical transmittance, so it is widely used in the electrochromic technology. This paper overviews the research progress of anodic electrochromic materials in recent years, including material classification, working principle and characteristic requirement, and also introduces the film preparation methods. Developing simple and cost-effective film preparation process is the research focus of electrochromic technology. At the same time, this paper introduces some methods for improving the performance of anodic electrochromic materials, and prospects the development trend.
Electrochromic technology has been widely used in many fields, such as building windows and car rear-view mirrors. Ion storage layers (generally anodic electrochromic materials) are significant for improving the performance of electrochromic devices and realizing the application of the technology. Its role is to store and supply the ions needed for the color change reaction, maintaining the charge balance of the entire electrochromic process. At present, the most typical anodic electrochromic material is nickel oxide(NiO). The cheap NiO film has high coloration efficiency and large range of optical transmittance, so it is widely used in the electrochromic technology. This paper overviews the research progress of anodic electrochromic materials in recent years, including material classification, working principle and characteristic requirement, and also introduces the film preparation methods. Developing simple and cost-effective film preparation process is the research focus of electrochromic technology. At the same time, this paper introduces some methods for improving the performance of anodic electrochromic materials, and prospects the development trend.
2019, 39(5): 1 -12
doi: 10.11868/j.issn.1005-5053.2019.000139
Abstract:
Microwave-absorbing ceramic matrix composites play an important role in the development of heat-resisting stealthy materials due to their excellent high-temperature mechanical property, superior corrosion resistance and oxidation resistance. In this paper, the micro to macromultiscale design principle of microwave-absorbing ceramics is introduced. The latest research progresses of microwave-absorbing materials such as modified SiC ceramics, doped BaFe12O19 (BFO) ceramics, polymer derived ceramics (PDCs), 3D printed porous ceramics/ceramic-honeycombs, multiscale-designed continuous fiber reinforced ceramic matrix composites (CFCMC) and other new ceramic matrix composites are overviewed. The development trend of ceramic matrix composites with integrated structure absorbing is prospected, and the fiber reinforced ceramic matrix composites with multiscale structure design of micro-macro is proposed to be an important development direction in the field of high-temperature stealth materials in the future.
Microwave-absorbing ceramic matrix composites play an important role in the development of heat-resisting stealthy materials due to their excellent high-temperature mechanical property, superior corrosion resistance and oxidation resistance. In this paper, the micro to macromultiscale design principle of microwave-absorbing ceramics is introduced. The latest research progresses of microwave-absorbing materials such as modified SiC ceramics, doped BaFe12O19 (BFO) ceramics, polymer derived ceramics (PDCs), 3D printed porous ceramics/ceramic-honeycombs, multiscale-designed continuous fiber reinforced ceramic matrix composites (CFCMC) and other new ceramic matrix composites are overviewed. The development trend of ceramic matrix composites with integrated structure absorbing is prospected, and the fiber reinforced ceramic matrix composites with multiscale structure design of micro-macro is proposed to be an important development direction in the field of high-temperature stealth materials in the future.
2019, 39(5): 13 -23
doi: 10.11868/j.issn.1005-5053.2019.000101
Abstract:
SiCf/SiC composites are consisted of SiC fibers, SiC matrix and interphase. The interphase can transfer stresses from matrix to SiC fibers and deflects microcracks, at the same time, it protects SiC fibers from chemical erosion during the preparation and use of materials, which plays a very important role in regulating the properties of SiCf/SiC composites. In this paper, the effects of precursor gas ratio, carrier gas, deposition pressure, temperature on the deposition rate and microstructure of interphase during the chemical vapor infiltration (CVI) process are summarized. It will be the key and difficult point in the research of SiCf/SiC composite interphase to select appropriate process conditions and prepare BN and its composite multilayer with ideal structure.
SiCf/SiC composites are consisted of SiC fibers, SiC matrix and interphase. The interphase can transfer stresses from matrix to SiC fibers and deflects microcracks, at the same time, it protects SiC fibers from chemical erosion during the preparation and use of materials, which plays a very important role in regulating the properties of SiCf/SiC composites. In this paper, the effects of precursor gas ratio, carrier gas, deposition pressure, temperature on the deposition rate and microstructure of interphase during the chemical vapor infiltration (CVI) process are summarized. It will be the key and difficult point in the research of SiCf/SiC composite interphase to select appropriate process conditions and prepare BN and its composite multilayer with ideal structure.
2019, 39(5): 24 -33
doi: 10.11868/j.issn.1005-5053.2019.000035
Abstract:
High-performance thermoplastic composites, due to their high toughness, excellent impact damage resistance and better fatigue resistance, are especially suitable for constructing special helicopter structures such as the landing gear, tail section, rotor hub and transmission drive shaft, which requires high damage-resistant, ballistic-tolerant, anti-fatigue properties. The application of high-performance thermoplastic composites in foreign helicopters is expanding from the application of key laminate structures to honeycomb sandwich structures, and a large number of low-cost and auto-mated manufacturing techniques such as in-situ automated fiber placement (AFP) and low-cost verification techniques such as virtual testing is being used. Limited by the low level maturity of domestic thermoplastic composites technology, high cost and long cycle of the traditional building block verification methods for the new composite system, the application of thermoplastic composites in domestic helicopter is still in initial stage, the performance stability and consistency of thermoplastic composites, supplementary low cost automatic manufacturing process, low density and high temperature core material and high-confidence efficient virtual qualification technology are needed to focus on the future.
High-performance thermoplastic composites, due to their high toughness, excellent impact damage resistance and better fatigue resistance, are especially suitable for constructing special helicopter structures such as the landing gear, tail section, rotor hub and transmission drive shaft, which requires high damage-resistant, ballistic-tolerant, anti-fatigue properties. The application of high-performance thermoplastic composites in foreign helicopters is expanding from the application of key laminate structures to honeycomb sandwich structures, and a large number of low-cost and auto-mated manufacturing techniques such as in-situ automated fiber placement (AFP) and low-cost verification techniques such as virtual testing is being used. Limited by the low level maturity of domestic thermoplastic composites technology, high cost and long cycle of the traditional building block verification methods for the new composite system, the application of thermoplastic composites in domestic helicopter is still in initial stage, the performance stability and consistency of thermoplastic composites, supplementary low cost automatic manufacturing process, low density and high temperature core material and high-confidence efficient virtual qualification technology are needed to focus on the future.
2019, 39(5): 34 -44
doi: 10.11868/j.issn.1005-5053.2019.000097
Abstract:
At present, lightweight armour has been fitted in foreign military helicopters for gunships and transport. By contrast, the armor configuration of domestic helicopters is still a big gap compared with Europe and America in the level type, quantity and single aircraft area. With more requirements of new generation military helicopters' projected-retarded survivability are raised, the development of new armor materials has also made great progress at home and abroad. In this paper, the development of composite bulletproof armor for armed helicopters is reviewed, future development needs are summarized, projected-retarded mechanism, selection principle of material and the way of energy absorption in the process of weapons is analyzed, and application prospect in military helicopters of new materials such as functionally graded materials, micro-laminated material, graphene modified ceramic is looked forward. Due to the independent development needs of helicopters in China, it is urgent to develop new advanced lightweight protective materials with excellent performance. Only by developing new armor materials can improve the survivability of our helicopters, meet the requirements of our weapons, and achieve the synchronous development with the world’s advanced helicopter level.
At present, lightweight armour has been fitted in foreign military helicopters for gunships and transport. By contrast, the armor configuration of domestic helicopters is still a big gap compared with Europe and America in the level type, quantity and single aircraft area. With more requirements of new generation military helicopters' projected-retarded survivability are raised, the development of new armor materials has also made great progress at home and abroad. In this paper, the development of composite bulletproof armor for armed helicopters is reviewed, future development needs are summarized, projected-retarded mechanism, selection principle of material and the way of energy absorption in the process of weapons is analyzed, and application prospect in military helicopters of new materials such as functionally graded materials, micro-laminated material, graphene modified ceramic is looked forward. Due to the independent development needs of helicopters in China, it is urgent to develop new advanced lightweight protective materials with excellent performance. Only by developing new armor materials can improve the survivability of our helicopters, meet the requirements of our weapons, and achieve the synchronous development with the world’s advanced helicopter level.
2019, 39(5): 45 -60
doi: 10.11868/j.issn.1005-5053.2018.000074
Abstract:
In order to meet the needs of high-altitude, long-endurance, high mobility, functional and economic requirement for the future unmanned aerial vehicle(UAV), advanced composite materials have been increasingly applied in UAVs at home and abroad, and even many all-composite UAVs are manufactured. However, there are still some gaps in the proportion and technical level of composite materials used in UAVs in China compared with foreign countries. The cost of composite parts is one of the main factors restricting its application. This paper introduces the development process of UAV at home and abroad, and summarizes the application of composite materials on UAVs. Some key technologies and development trends of UAV composite materials are proposed. Some questions and suggestions are raised on the application of domestic composite materials on drones. For accelerating the application of composite materials in UAV industry in China, it is necessary to design the composite structure based on the process feasibility and stability with introducing foreign automation technology to reduce composite structure cost, actively develop various liquid forming technology, bag vacuum only-out of autoclave(BVO-OoA) materials and technology, and improve the traditional moulding technology research.
In order to meet the needs of high-altitude, long-endurance, high mobility, functional and economic requirement for the future unmanned aerial vehicle(UAV), advanced composite materials have been increasingly applied in UAVs at home and abroad, and even many all-composite UAVs are manufactured. However, there are still some gaps in the proportion and technical level of composite materials used in UAVs in China compared with foreign countries. The cost of composite parts is one of the main factors restricting its application. This paper introduces the development process of UAV at home and abroad, and summarizes the application of composite materials on UAVs. Some key technologies and development trends of UAV composite materials are proposed. Some questions and suggestions are raised on the application of domestic composite materials on drones. For accelerating the application of composite materials in UAV industry in China, it is necessary to design the composite structure based on the process feasibility and stability with introducing foreign automation technology to reduce composite structure cost, actively develop various liquid forming technology, bag vacuum only-out of autoclave(BVO-OoA) materials and technology, and improve the traditional moulding technology research.
2019, 39(5): 61 -81
doi: 10.11868/j.issn.1005-5053.2018.000130
Abstract:
High-entropy alloy is a new type of alloy, its excellent physical and chemical properties have attracted extensive attention of the researchers. However, the density of traditional HEAs is high, which greatly limits their engineering applications. In order to reduce the density of HEAs, the low-density elements such as Al, Ti, Mg, Li, and C are used to prepare HEAs, then, a series of LHEAs at equal molar or non-equalmolar concentrations is successfully prepared, showing great application potential in the fields of aerospace, energy and transportation. This paper reviews the research progress of LHEAs. The design guidelines and processing techniques of HEAs are analyzed. The phase structures and properties of LHEAs are introduced according to their system characteristics. The future research direction of LHEAs is prospected.
High-entropy alloy is a new type of alloy, its excellent physical and chemical properties have attracted extensive attention of the researchers. However, the density of traditional HEAs is high, which greatly limits their engineering applications. In order to reduce the density of HEAs, the low-density elements such as Al, Ti, Mg, Li, and C are used to prepare HEAs, then, a series of LHEAs at equal molar or non-equalmolar concentrations is successfully prepared, showing great application potential in the fields of aerospace, energy and transportation. This paper reviews the research progress of LHEAs. The design guidelines and processing techniques of HEAs are analyzed. The phase structures and properties of LHEAs are introduced according to their system characteristics. The future research direction of LHEAs is prospected.
2019, 39(5): 82 -93
doi: 10.11868/j.issn.1005-5053.2019.000023
Abstract:
High strength and low density are the basic requirements for the materials used in the aeronautical field, the engine materials need high temperatures resistance more severely. High entropy alloys (HEAs) containing refractory metal elements with high melting point show excellent material properties at high temperature. At present, more than 120 kinds of refractory high entropy alloys (RHEAs) have been synthesized, and their physical and mechanical properties, such as density, tensile properties, compression properties, elastic modulus and antioxidant properties have been tested experimentally. In this paper, the performance parameters of refractory high entropy alloys and traditional typical aviation materials are summarized, and the density and yield strength limits of refractory high entropy alloys at high temperature are compared, most refractory high entropy alloys show high mechanical strength and microstructure stability.
High strength and low density are the basic requirements for the materials used in the aeronautical field, the engine materials need high temperatures resistance more severely. High entropy alloys (HEAs) containing refractory metal elements with high melting point show excellent material properties at high temperature. At present, more than 120 kinds of refractory high entropy alloys (RHEAs) have been synthesized, and their physical and mechanical properties, such as density, tensile properties, compression properties, elastic modulus and antioxidant properties have been tested experimentally. In this paper, the performance parameters of refractory high entropy alloys and traditional typical aviation materials are summarized, and the density and yield strength limits of refractory high entropy alloys at high temperature are compared, most refractory high entropy alloys show high mechanical strength and microstructure stability.
2019, 39(5): 94 -102
doi: 10.11868/j.issn.1005-5053.2019.000142
Abstract:
The effect of YSZ+NiCrAl-B.e composite coating on the ignition resistance of TC11 titanium alloy was studied by using the method of friction in oxygen-enriched atmosphere. Combining friction and wear analysis and unsteady heat conduction calculation, the fireproof mechanism of the composite coating was discussed. The results show that the YSZ+NiCrAl-B.e composite coating significantly improves the ignition resistance of the titanium alloy, and its critical ignition oxygen concentration is about 2.3 times than that of the bare titanium alloy. The friction property of the friction pair composed of the titanium alloy and the composite coating is higher than that of the friction pair composed of titanium and titanium alloy; And the effect of NiCrAl-B.e layer on the ignition resistance of the titanium alloy is not obvious. In the process of friction ignition, the YSZ layer can significantly reduce the temperature rise of the titanium alloy substrate though preventing the rapid heat transfer, delaying the ignition of the titanium alloy. In this sense, the YSZ layer is the flame retardant layer in the coating system, and heat barrier is the main fireproof mechanism.
The effect of YSZ+NiCrAl-B.e composite coating on the ignition resistance of TC11 titanium alloy was studied by using the method of friction in oxygen-enriched atmosphere. Combining friction and wear analysis and unsteady heat conduction calculation, the fireproof mechanism of the composite coating was discussed. The results show that the YSZ+NiCrAl-B.e composite coating significantly improves the ignition resistance of the titanium alloy, and its critical ignition oxygen concentration is about 2.3 times than that of the bare titanium alloy. The friction property of the friction pair composed of the titanium alloy and the composite coating is higher than that of the friction pair composed of titanium and titanium alloy; And the effect of NiCrAl-B.e layer on the ignition resistance of the titanium alloy is not obvious. In the process of friction ignition, the YSZ layer can significantly reduce the temperature rise of the titanium alloy substrate though preventing the rapid heat transfer, delaying the ignition of the titanium alloy. In this sense, the YSZ layer is the flame retardant layer in the coating system, and heat barrier is the main fireproof mechanism.
2019, 39(5): 103 -112
doi: 10.11868/j.issn.1005-5053.2019.000074
Abstract:
Aiming at the problems of many internal defects and low molding quality of cast titanium alloy impeller blades, By designed two casting systems, the finite element method is used to numerically simulate the gating system.. The design optimization of casting system was studied during the casting and solidification process. The effects of flow field, temperature field and shrinkage were carried out on the basis of optimal design, and the microstructure and mechanical properties of the casting were tested and analyzed. The results showed that under the condition of vacuum precipitating temperature of 400 ℃, pouring temperature of 1730 ℃, pouring time of 8 s, the bottom injection have good filling and solidification quality, and there is no defect inside the casting; The top-injection structure is filled with a disordered flow field, and there is a gas-filling phenomenon. Concurrently, there are many internal defects in the casting. Therefore, the pouring system of the bottom-injecting multi-risk structure is superior to the top-injection structure. Simultaneously,the castings microstructure is density, The yield strength, elongation and microhardness are 785.5 MPa, 25.5% and 301.67 HBW.The mechanical properties are good, the surface precision is high, meet the requirements of high quality titanium alloy castings
Aiming at the problems of many internal defects and low molding quality of cast titanium alloy impeller blades, By designed two casting systems, the finite element method is used to numerically simulate the gating system.. The design optimization of casting system was studied during the casting and solidification process. The effects of flow field, temperature field and shrinkage were carried out on the basis of optimal design, and the microstructure and mechanical properties of the casting were tested and analyzed. The results showed that under the condition of vacuum precipitating temperature of 400 ℃, pouring temperature of 1730 ℃, pouring time of 8 s, the bottom injection have good filling and solidification quality, and there is no defect inside the casting; The top-injection structure is filled with a disordered flow field, and there is a gas-filling phenomenon. Concurrently, there are many internal defects in the casting. Therefore, the pouring system of the bottom-injecting multi-risk structure is superior to the top-injection structure. Simultaneously,the castings microstructure is density, The yield strength, elongation and microhardness are 785.5 MPa, 25.5% and 301.67 HBW.The mechanical properties are good, the surface precision is high, meet the requirements of high quality titanium alloy castings
2019, 39(5): 113 -119
doi: 10.11868/j.issn.1005-5053.2019.000081
Abstract:
The mechanism of coating interface bulge on the TGO growth behavior was studied by analyzing the rule of TGO growth and the interface stress at the top coat/bond coat interface. The results show that the growth rate of TGO in the convex region of the top coat/bond coat interface is higher than that in the other regions. According to the stress analysis of ANSYS, the interface stress increases (from 185 MPa to 406 MPa) with the increase of roughness (from 10 μm to 20 μm). Additionally, the interfacial stress also increases (from 142 MPa to 574 MPa) with the thickness of TGO layer increasing (from 1.6 μm to 9.3 μm). What’s more, during high temperature oxidation, the convex region of the top coat/bond coat interface is mainly characterized by tensile stress and the depressed region is compressive stress.The tensile stress can promote the rapid growth of TGO layer, while the compressive stress exhibits the inhibition on the growth rate of TGO. In summary, reducing the roughness of bond coat can reduce the interface stress and slow the growth rate of TGO, which ensures the effective bonding strength of the coating. Thus, the stability of the TBCs at high temperature can be improved.
The mechanism of coating interface bulge on the TGO growth behavior was studied by analyzing the rule of TGO growth and the interface stress at the top coat/bond coat interface. The results show that the growth rate of TGO in the convex region of the top coat/bond coat interface is higher than that in the other regions. According to the stress analysis of ANSYS, the interface stress increases (from 185 MPa to 406 MPa) with the increase of roughness (from 10 μm to 20 μm). Additionally, the interfacial stress also increases (from 142 MPa to 574 MPa) with the thickness of TGO layer increasing (from 1.6 μm to 9.3 μm). What’s more, during high temperature oxidation, the convex region of the top coat/bond coat interface is mainly characterized by tensile stress and the depressed region is compressive stress.The tensile stress can promote the rapid growth of TGO layer, while the compressive stress exhibits the inhibition on the growth rate of TGO. In summary, reducing the roughness of bond coat can reduce the interface stress and slow the growth rate of TGO, which ensures the effective bonding strength of the coating. Thus, the stability of the TBCs at high temperature can be improved.
2019, 39(5): 120 -127
doi: 10.11868/j.issn.1005-5053.2019.000016
Abstract:
The open-cell Al foam was fabricated by space-holder method and Al foam-filled tube was obtained by filling Al foam into Al alloy tube. The influences of wall thickness, bonding method and filling margin on the mechanical and energy absorbing properties of Al foam-filled tubes were investigated by quasi static compression experiment. The mechanical and energy absorption properties of single and composite structures at different strain rates were studied by quasi-static compression and drop impact tests. The results show that in quasi-static compression tests, when the strain is 60%, the energy absorbed of Al foam-filled tube is 122 % of the numerical sum of Al foam and Al foam-filled tube. In the impact test, the impact load of the composite structure is more stable, and it has higher average impact load and stronger energy absorption capability. Therefore, compared with Al foam, Al foam-filled tube has a great improvement in energy absorption both in compression test and impact test.
The open-cell Al foam was fabricated by space-holder method and Al foam-filled tube was obtained by filling Al foam into Al alloy tube. The influences of wall thickness, bonding method and filling margin on the mechanical and energy absorbing properties of Al foam-filled tubes were investigated by quasi static compression experiment. The mechanical and energy absorption properties of single and composite structures at different strain rates were studied by quasi-static compression and drop impact tests. The results show that in quasi-static compression tests, when the strain is 60%, the energy absorbed of Al foam-filled tube is 122 % of the numerical sum of Al foam and Al foam-filled tube. In the impact test, the impact load of the composite structure is more stable, and it has higher average impact load and stronger energy absorption capability. Therefore, compared with Al foam, Al foam-filled tube has a great improvement in energy absorption both in compression test and impact test.
2018, 38(2): 70-76
doi: 10.11868/j.issn.1005-5053.2018.001005
2018, 38(2): 10-20
doi: 10.11868/j.issn.1005-5053.2018.001001
2018, 38(6): 1-10
doi: 10.11868/j.issn.1005-5053.2018.000081
2019, 39(2): 1-9
doi: 10.11868/j.issn.1005-5053.2018.000041
2016, 36(4): 89-98
doi: 10.11868/j.issn.1005-5053.2016.4.013
2018, 38(2): 59-69
doi: 10.11868/j.issn.1005-5053.2018.001002
2018, 38(2): 86-95
doi: 10.11868/j.issn.1005-5053.2017.000010
2018, 38(4): 37-46
doi: 10.11868/j.issn.1005-5053.2017.000204
2018, 38(2): 1-9
doi: 10.11868/j.issn.1005-5053.2018.001008
2018, 38(4): 64-74
doi: 10.11868/j.issn.1005-5053.2018.000025
2018, 38(5): 24-35
doi: 10.11868/j.issn.1005-5053.2018.000035
2018, 38(3): 10-19
doi: 10.11868/j.issn.1005-5053.2018.001009
2016, 36(3): 108-123
doi: 10.11868/j.issn.1005-5053.2016.3.012
2018, 38(4): 101-108
doi: 10.11868/j.issn.1005-5053.2018.000007
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Address：P.Q.BOX 81-44,Beijing 100095,China
Telephone：010-62496277 E-mail：hkclxb@biam.ac.cn
Supported by Beijing Renhe Information Technology Co. LtdTechnical support：info@rhhz.net