CN116080182A - Preparation method of high-energy-absorption layered sandwich protection structure - Google Patents
Preparation method of high-energy-absorption layered sandwich protection structure Download PDFInfo
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- CN116080182A CN116080182A CN202211111200.5A CN202211111200A CN116080182A CN 116080182 A CN116080182 A CN 116080182A CN 202211111200 A CN202211111200 A CN 202211111200A CN 116080182 A CN116080182 A CN 116080182A
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
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Abstract
A preparation method of a high energy-absorbing layered sandwich protective structure relates to a preparation method of an energy-absorbing protective structure. In order to solve the problem that the energy absorption effect of the existing impact-resistant protective structure is poor. The method comprises the following steps: weighing the hollow sphere and the balance of aluminum ingot; screening and drying the hollow spheres, then placing the hollow spheres in a steel mold, compacting and preheating to obtain a preheated preform; immersing the preheated preform in aluminizing liquid on a press to obtain a hollow sphere porous aluminum matrix composite core plate; and stacking the face plate, the core plate and the back plate, bonding the face plate, the core plate and the back plate by using an epoxy resin adhesive, and finally drying. The invention adopts the porous composite material with higher strength and higher energy absorption capacity as the core layer structure instead of the traditional foam metal in the protective structure, thereby remarkably improving the whole energy absorption capacity of the sandwich protective structure and having good antiknock performance.
Description
Technical Field
The invention relates to a preparation method of an energy-absorbing protective structure.
Background
Military armor and the like are mainly affected by vibration impact energy, so that impact protection is required. The sandwich structure is designed to realize the energy absorption effect in the fields of automobiles, aerospace, civil building structures, military armor and the like. The hard/soft/hard sandwich structure with porous material, rubber or plastic and other soft material as the core layer, metal with high strength and hardness, ceramic or fiber polymer as the surface and back plate can make the surface plate and back plate continuously bend by regulating the wave impedance of the layers of material, so as to attenuate impact energy, and the matching problem of the wave impedance of the core layer material and the surface and back plate is a necessary condition for realizing excellent energy absorption performance. However, the core layer of the traditional sandwich protection structure mainly comprises foam metal, but the foam metal has three limitations:
1. the strength of the foam metal is low;
2. the foam metal has low rigidity;
3. the foam metal has low impact load, so the existing impact-resistant protective structure has poor energy absorption effect.
Disclosure of Invention
The invention provides a preparation method of a high-energy-absorption layered sandwich protective structure, which aims to solve the problem that the existing impact-resistant protective structure is poor in energy-absorption effect and cannot meet the increasing demands on the impact-resistant protective structure.
The preparation method of the high energy absorption layered sandwich protective structure comprises the following steps:
1. weighing material
Weighing 30-60% of hollow spheres and the balance of aluminum ingots according to the volume fraction;
the hollow sphere is one or a combination of more of an alumina hollow sphere, a fly ash hollow sphere, a glass microsphere hollow sphere, a SiC hollow sphere and a hollow steel ball;
2. preparation of core plate
Screening and drying the hollow spheres, then placing the hollow spheres in a steel die and compacting, and preheating the hollow microsphere belt die to obtain a preheated preform; impregnating the preheated preform with aluminum liquid on a press, and performing hot demolding after impregnating to obtain a hollow sphere porous aluminum-based composite core plate;
the preheating process comprises the following steps: preserving heat for 4 hours at 600 ℃ in a protective atmosphere to perform preheating treatment;
the pressure of the pressure infiltration is 2-5 MPa, and the time is 5-15 min;
3. preparation of high-energy-absorption layered sandwich protective structure
Mixing epoxy resin, a curing agent and a proper amount of SiC powder to obtain an epoxy resin adhesive; stacking the panel, the core plate and the back plate, bonding the panels with epoxy resin adhesive, and finally drying to finish the process;
the epoxy resin is bisphenol A glycidyl ether epoxy resin;
the curing agent is m-xylylenediamine;
the mass ratio of the epoxy resin to the curing agent to the silicon carbide is (60-50): 2:1.
The invention has the beneficial effects that:
1. the invention adopts the porous composite material with higher strength and higher energy absorption capacity to replace the traditional foam metal as the core layer structure in the protective structure, thereby remarkably improving the whole energy absorption capacity of the sandwich protective structure.
2. The invention uses the epoxy resin adhesive prepared by bisphenol A glycidyl ether epoxy resin and m-xylylenediamine curing agent to connect the sandwich structure, the prepared epoxy resin adhesive has high strength, and the strength of the epoxy resin adhesive can be further enhanced by adding a certain amount of silicon carbide powder into the epoxy resin adhesive, thereby avoiding the damage of the sandwich structure at the connection position when being impacted.
3. The process is simple to operate, and the sandwich structures with different sizes can be prepared according to the requirements.
4. The porous composite material prepared by the invention has good antiknock performance, and the minimum mass loss in antiknock experiments is only 1.4%.
Drawings
FIG. 1 is a photograph of the front side of an antiknock test of a "sandwich" protective structure of example 1;
FIG. 2 is a photograph of the front of a "sandwich" protective structure of example 1 after an antiknock test;
FIG. 3 is a photograph of broken pieces of aluminum foam after the core aluminum foam is damaged after an antiknock test of the protective structure in the comparative example;
FIG. 4 is a photograph of another broken piece of aluminum foam after the core aluminum foam is damaged after an antiknock test of the protective structure in the comparative example;
fig. 5 is a photograph of another aluminum foam fragment after the core aluminum foam is damaged after the blast resistance test of the protective structure in the comparative example.
Detailed Description
The technical scheme of the invention is not limited to the specific embodiments listed below, and also comprises any reasonable combination of the specific embodiments.
The first embodiment is as follows: the preparation method of the high energy absorption layered sandwich protective structure in the embodiment is carried out according to the following steps of;
1. weighing material
Weighing 30-60% of hollow spheres and the balance of aluminum ingots according to the volume fraction;
the hollow sphere is one or a combination of more of an alumina hollow sphere, a fly ash hollow sphere, a glass microsphere hollow sphere, a SiC hollow sphere and a hollow steel ball;
2. preparation of core plate
Screening and drying the hollow spheres, then placing the hollow spheres in a steel die and compacting, and preheating the hollow microsphere belt die to obtain a preheated preform; impregnating the preheated preform with aluminum liquid on a press, and performing hot demolding after impregnating to obtain a hollow sphere porous aluminum-based composite core plate;
the preheating process comprises the following steps: preserving heat for 4 hours at 600 ℃ in a protective atmosphere to perform preheating treatment;
the pressure of the pressure infiltration is 2-5 MPa, and the time is 5-15 min;
3. preparation of high-energy-absorption layered sandwich protective structure
Mixing epoxy resin, a curing agent and a proper amount of SiC powder to obtain an epoxy resin adhesive; stacking the panel, the core plate and the back plate, bonding the panels with epoxy resin adhesive, and finally drying to finish the process;
the epoxy resin is bisphenol A glycidyl ether epoxy resin;
the curing agent is m-xylylenediamine;
the mass ratio of the epoxy resin to the curing agent to the silicon carbide is (60-50): 2:1.
The present embodiment has the following advantageous effects:
1. in the embodiment, the porous composite material with higher strength and higher energy absorption capacity is adopted to replace the traditional foam metal as the core layer structure in the protective structure, so that the overall energy absorption capacity of the sandwich protective structure is obviously improved.
2. According to the embodiment, the sandwich structure is connected by using the epoxy resin adhesive prepared by the bisphenol A glycidyl ether epoxy resin and the m-xylylenediamine curing agent, the prepared epoxy resin adhesive has high strength, and meanwhile, the strength of the epoxy resin adhesive can be further enhanced by adding a certain amount of silicon carbide powder into the epoxy resin adhesive, so that the sandwich structure is prevented from being damaged at the connection part when being impacted.
3. The method is simple in process operation, and the sandwich structures with different sizes can be prepared according to the requirements.
4. The porous composite material prepared by the embodiment has good antiknock performance, and the minimum mass loss in antiknock experiments is only 1.4%.
The second embodiment is as follows: the first difference between this embodiment and the specific embodiment is that: the aluminum ingot in the first step is one or the combination of a plurality of Al-Si alloy, al-Si-Cu alloy, al-Cu-Mg alloy, al-Zn-Cu alloy, al-Zn-Mg-Cu alloy and Al-Si-Cu-Mg alloy; the mass fraction of Si in the Al-Si alloy is 2% -25%; the mass fraction of Si in the Al-Si-Cu alloy is 0.5-25%, and the mass fraction of Cu is 0.5-53%; the mass fraction of Cu in the Al-Cu-Mg alloy is 0.5-53%, and the mass fraction of Mg is 0.5-38%; the mass fraction of Zn in the Al-Zn-Cu alloy is 0.5-55%, and the mass fraction of Cu is 0.5-53%; the mass fraction of Zn in the Al-Zn-Mg-Cu alloy is 0.5-55%, the mass fraction of Mg is 0.5-38%, and the mass fraction of Cu is 0.5-53%; the mass fraction of Si in the Al-Si-Cu-Mg alloy is 0.5-25%, the mass fraction of Cu is 0.5-53%, and the mass fraction of Mg
And a third specific embodiment: this embodiment differs from the first or second embodiment in that: the median particle diameter of the hollow sphere in the step one is 18 mu m-3 mm.
The specific embodiment IV is as follows: this embodiment differs from one of the first to third embodiments in that: the die in the second step is cylindrical, and the diameter is 90-430 mm.
Fifth embodiment: this embodiment differs from one to four embodiments in that: and step two, the protective atmosphere is helium, nitrogen or argon.
Specific embodiment six: this embodiment differs from one of the first to fifth embodiments in that: the screening method in the second step is a floating method, and broken hollow spheres can be removed.
Seventh embodiment: this embodiment differs from one of the first to sixth embodiments in that: and step three, the drying temperature is 80-150 ℃, and the heat preservation time is 2-8 h.
Eighth embodiment: this embodiment differs from one of the first to seventh embodiments in that: the particle size of the silicon carbide in the third step is 2-5 mu m; the silicon carbide has the function of improving the strength of the adhesive.
Detailed description nine: this embodiment differs from one to eight of the embodiments in that: the face plate and the back plate in the third step are 2024Al plate, Q235 steel plate, fiber cloth, 5005H34 aluminum alloy plate, 3003 aluminum alloy plate, Q460 steel plate, T700 carbon fiber plate, HRB335 grade steel plate or 304# stainless steel.
Detailed description ten: this embodiment differs from one of the embodiments one to nine in that: the thickness of the panel and the backboard is 0.9-1.1 mm; the thickness of the core plate is 2-7 mm.
Example 1:
the preparation method of the high-energy-absorption layered sandwich protective structure is carried out according to the following steps:
1. weighing material
Weighing 60% of hollow spheres and 40% of aluminum ingots according to the volume fraction;
the aluminum ingot is an Al-Si alloy; the mass fraction of Si in the Al-Si alloy is 10%;
the hollow spheres are glass microsphere hollow spheres;
the median particle diameter of the hollow sphere is 40 mu m;
2. preparation of core plate
Screening the hollow spheres by a floating method, drying, placing the hollow spheres in a steel mould, naturally vibrating the hollow spheres by using gravity, and carrying out heat preservation on the hollow spheres with the mould for 4 hours at 600 ℃ under the protective atmosphere to obtain a preheated preform; impregnating the preheated preform with aluminum liquid on a press, and performing hot demolding after impregnating to obtain a hollow sphere porous aluminum-based composite core plate;
the die is cylindrical, and the diameter of the die is 90mm;
the pressure impregnation pressure is 5MPa, and the time is 5min;
the protective atmosphere is helium;
3. preparation of high-energy-absorption layered sandwich protective structure
Mixing epoxy resin, a curing agent and a proper amount of SiC powder to obtain an epoxy resin adhesive; bonding the face plate, the core plate and the back plate by using an epoxy resin adhesive, pressing, putting the face plate, the core plate and the back plate into a drying box for drying, taking out the face plate, and grinding the epoxy resin adhesive on the surface of the face plate to obtain the high-energy-absorption layered sandwich protective structure.
The mass ratio of the epoxy resin to the curing agent to the silicon carbide is 50:2:1;
the epoxy resin is bisphenol A glycidyl ether epoxy resin;
the curing agent is m-xylylenediamine;
the grain diameter of the silicon carbide is 2 mu m;
the panel and the backboard are Q235 steel plates;
the thickness of the panel is 1mm, the thickness of the backboard is 1mm, and the thickness of the core board is 5mm;
the drying temperature is 120 ℃, and the heat preservation time is 4 hours.
FIG. 1 is a macroscopic photograph of the side of the high energy absorption layered sandwich structure of example 1 before an antiknock test, and FIG. 2 is a macroscopic photograph of the front side of the core plate after the antiknock test; as is evident from fig. 1, the three-layer structure, i.e., the "sandwich" structure, is tightly bonded and has no voids in the connection layer. The structure is subjected to an antiknock experiment, as shown in fig. 2, the target with the sandwich protective structure is slightly damaged in the experiment, the panel is broken down by the explosive, the complete broken-down panel fragments are collected, the middle layer of the composite material is in a pit, the middle layer of the composite material is not broken down, and the backboard is slightly bulged. The detected mass loss was only 1.4%.
Example 2:
the preparation method of the high-energy-absorption layered sandwich protective structure is carried out according to the following steps:
1. weighing material
Weighing 60% of hollow spheres and 40% of aluminum ingots according to the volume fraction; weighing epoxy resin, curing agent and proper amount of SiC powder; preparing a face plate and a back plate with proper sizes;
the aluminum ingot is made of Al-Si alloy, and the mass fraction of Si in the Al-Si alloy is 2%;
the hollow spheres are fly ash hollow spheres;
the median particle diameter of the hollow sphere is 200 mu m;
2. preparation of core plate
Screening the hollow spheres by a floating method, drying, placing the hollow spheres in a steel mould, naturally vibrating the hollow spheres by using gravity, and carrying out heat preservation on the hollow spheres with the mould for 4 hours at 600 ℃ under the protective atmosphere to obtain a preheated preform; impregnating the preheated preform with aluminum liquid on a press, and performing hot demolding after impregnating to obtain a hollow sphere porous aluminum-based composite core plate;
the die is cylindrical, and the diameter of the die is 130mm;
the pressure impregnation pressure is 2MPa, and the time is 10min;
the protective atmosphere is argon;
3. preparation of high-energy-absorption layered sandwich protective structure
Mixing epoxy resin, a curing agent and a proper amount of SiC powder to obtain an epoxy resin adhesive; bonding the face plate, the core plate and the back plate by using an epoxy resin adhesive, pressing, putting the face plate, the core plate and the back plate into a drying box for drying, taking out the face plate, and grinding the epoxy resin adhesive on the surface of the face plate to obtain the high-energy-absorption layered sandwich protective structure.
The mass ratio of the epoxy resin to the curing agent to the silicon carbide is 60:2:1;
the epoxy resin is bisphenol A glycidyl ether epoxy resin;
the curing agent is m-xylylenediamine;
the grain diameter of the silicon carbide is 5 mu m;
the face plate and the back plate are 2024Al plates;
the thickness of the panel is 1mm, the thickness of the backboard is 1mm, and the thickness of the core board is 5mm;
the drying temperature is 80 ℃, and the heat preservation time is 8 hours.
Antiknock experiments are carried out on the high-energy-absorption layered sandwich protective structure, and the mass loss is 8.6%. The protective structure target prepared by the embodiment is damaged to a certain extent in the experiment, the panel is broken down by the explosive, the middle layer of the composite material is provided with a pit, the pit is broken down, and the backboard is provided with a certain bulge.
Example 3:
the preparation method of the high-energy-absorption layered sandwich protective structure is carried out according to the following steps:
1. weighing material
Weighing 60% of hollow spheres and 40% of aluminum ingots according to the volume fraction; weighing epoxy resin, curing agent and proper amount of SiC powder; preparing a face plate and a back plate with proper sizes;
the aluminum ingot is an Al-Si-Cu alloy, wherein the mass fraction of Si in the Al-Si-Cu alloy is 0.5%, and the mass fraction of Cu is 2%;
the hollow spheres are alumina hollow spheres;
the median particle diameter of the hollow sphere is 2mm;
2. preparation of core plate
Screening the hollow spheres by a floating method, drying, placing the hollow spheres in a steel mould, naturally vibrating the hollow spheres by using gravity, and carrying out heat preservation on the hollow spheres with the mould for 4 hours at 600 ℃ under the protective atmosphere to obtain a preheated preform; impregnating the preheated preform with aluminum liquid on a press, and performing hot demolding after impregnating to obtain a hollow sphere porous aluminum-based composite core plate;
the die is cylindrical, and the diameter of the die is 90mm;
the pressure impregnation pressure is 2MPa, and the time is 15min;
the protective atmosphere is nitrogen;
3. preparation of high-energy-absorption layered sandwich protective structure
Mixing epoxy resin, a curing agent and a proper amount of SiC powder to obtain an epoxy resin adhesive; bonding the face plate, the core plate and the back plate by using an epoxy resin adhesive, pressing, putting the face plate, the core plate and the back plate into a drying box for drying, taking out the face plate, and grinding the epoxy resin adhesive on the surface of the face plate to obtain the high-energy-absorption layered sandwich protective structure.
The mass ratio of the epoxy resin to the curing agent to the silicon carbide is 50:2:1;
the epoxy resin is bisphenol A glycidyl ether epoxy resin;
the curing agent is m-xylylenediamine;
the grain diameter of the silicon carbide is 3 mu m;
the panel and the backboard are Q235 steel plates;
the thickness of the panel is 1mm, the thickness of the backboard is 1mm, and the thickness of the core board is 6mm;
the drying temperature is 150 ℃, and the heat preservation time is 3 hours.
Antiknock experiments are carried out on the high-energy-absorption layered sandwich protective structure, and the mass loss is 5.7%. The protective structure target prepared in the embodiment is slightly damaged in the experiment, the panel is broken down by the explosive, the middle layer of the composite material is in a pit, but is not broken down, and the backboard is raised to a certain extent.
Comparative example: mixing epoxy resin, a curing agent and a proper amount of SiC powder to obtain an epoxy resin adhesive; bonding the face plate, the core plate and the back plate by using an epoxy resin adhesive, pressing, putting the face plate, the core plate and the back plate into a drying box for drying, taking out the face plate, and grinding the epoxy resin adhesive on the surface of the face plate to obtain the high-energy-absorption layered sandwich protective structure.
The core layer is foamed aluminum
The mass ratio of the epoxy resin to the curing agent to the silicon carbide is 50:2:1;
the epoxy resin is bisphenol A glycidyl ether epoxy resin;
the curing agent is m-xylylenediamine; the grain diameter of the silicon carbide is 3 mu m;
the panel and the backboard are Q235 steel plates;
the thickness of the panel is 1mm, the thickness of the backboard is 1mm, and the thickness of the core board is 6mm;
the drying temperature is 150 ℃, and the heat preservation time is 3 hours.
The protection structure prepared in the comparative example is subjected to an antiknock experiment, and the mass loss is 5.7%. As shown in fig. 3 to 5, since the aluminum foam structure is completely broken, the degree of damage of the aluminum foam structure is measured by measuring the mass and size of the aluminum foam fragments. The mass of the fragments was sorted from large to small, and the mass and size of a maximum of 4 fragments were measured. Wherein the mass of the chip of FIG. 3 is 41.6g, the long end size is 111mm, and the short end size is 29mm; the mass of the chip of FIG. 4 was 13.8g, the long end size was 52mm, and the short end size was 29mm; the mass of the chip of FIG. 5 was 6.0g, the long end size was 49mm, and the short end size was 9mm; in comparison with examples 1-3, the "sandwich" structure of aluminum foam as the core layer is completely destroyed and clearly unable to withstand the explosive load.
Claims (10)
1. A preparation method of a high energy absorption layered sandwich protective structure is characterized by comprising the following steps: the preparation method of the high energy absorption layered sandwich protective structure is carried out according to the following steps of;
1. weighing material
Weighing 30-60% of hollow spheres and the balance of aluminum ingots according to the volume fraction;
the hollow sphere is one or a combination of more of an alumina hollow sphere, a fly ash hollow sphere, a glass microsphere hollow sphere, a SiC hollow sphere and a hollow steel ball;
2. preparation of core plate
Screening and drying the hollow spheres, then placing the hollow spheres in a steel die and compacting, and preheating the hollow microsphere belt die to obtain a preheated preform; impregnating the preheated preform with aluminum liquid on a press, and performing hot demolding after impregnating to obtain a hollow sphere porous aluminum-based composite core plate;
the preheating process comprises the following steps: preserving heat for 4 hours at 600 ℃ in a protective atmosphere to perform preheating treatment;
the pressure of the pressure infiltration is 2-5 MPa, and the time is 5-15 min;
3. preparation of high-energy-absorption layered sandwich protective structure
Mixing epoxy resin, a curing agent and a proper amount of SiC powder to obtain an epoxy resin adhesive; stacking the panel, the core plate and the back plate, bonding the panels with epoxy resin adhesive, and finally drying to finish the process;
the epoxy resin is bisphenol A glycidyl ether epoxy resin;
the curing agent is m-xylylenediamine;
the mass ratio of the epoxy resin to the curing agent to the silicon carbide is (60-50): 2:1.
2. The method for preparing the high energy absorption layered sandwich protective structure according to claim 1, which is characterized in that: the aluminum ingot in the first step is one or the combination of a plurality of Al-Si alloy, al-Si-Cu alloy, al-Cu-Mg alloy, al-Zn-Cu alloy, al-Zn-Mg-Cu alloy and Al-Si-Cu-Mg alloy; the mass fraction of Si in the Al-Si alloy is 2% -25%; the mass fraction of Si in the Al-Si-Cu alloy is 0.5-25%, and the mass fraction of Cu is 0.5-53%; the mass fraction of Cu in the Al-Cu-Mg alloy is 0.5-53%, and the mass fraction of Mg is 0.5-38%; the mass fraction of Zn in the Al-Zn-Cu alloy is 0.5-55%, and the mass fraction of Cu is 0.5-53%; the mass fraction of Zn in the Al-Zn-Mg-Cu alloy is 0.5-55%, the mass fraction of Mg is 0.5-38%, and the mass fraction of Cu is 0.5-53%; the mass fraction of Si in the Al-Si-Cu-Mg alloy is 0.5-25%, the mass fraction of Cu is 0.5-53%, and the mass fraction of Mg is 0.5-38%.
3. The method for preparing the high energy absorption layered sandwich protective structure according to claim 1, which is characterized in that: the median particle diameter of the hollow sphere in the step one is 18 mu m-3 mm.
4. The method for preparing the high energy absorption layered sandwich protective structure according to claim 1, which is characterized in that: the die in the second step is cylindrical, and the diameter is 90-430 mm.
5. The method for preparing the high energy absorption layered sandwich protective structure according to claim 1, which is characterized in that: and step two, the protective atmosphere is helium, nitrogen or argon.
6. The method for preparing the high energy absorption layered sandwich protective structure according to claim 1, which is characterized in that: the screening method in the second step is a floatation method.
7. The method for preparing the high energy absorption layered sandwich protective structure according to claim 1, which is characterized in that: and step three, the drying temperature is 80-150 ℃, and the heat preservation time is 2-8 h.
8. The method for preparing the high energy absorption layered sandwich protective structure according to claim 1, which is characterized in that: the particle size of the silicon carbide in the step three is 2-5 mu m.
9. The method for preparing the high energy absorption layered sandwich protective structure according to claim 1, which is characterized in that: the face plate and the back plate in the third step are 2024Al plate, Q235 steel plate, fiber cloth, 5005H34 aluminum alloy plate, 3003 aluminum alloy plate, Q460 steel plate, T700 carbon fiber plate, HRB335 grade steel plate or 304# stainless steel.
10. The method for preparing the high energy absorption layered sandwich protective structure according to claim 1, which is characterized in that: the thickness of the panel and the backboard is 0.9-1.1 mm; the thickness of the core plate is 2-7 mm.
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Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103589891A (en) * | 2013-11-26 | 2014-02-19 | 哈尔滨工业大学 | Preparation methods of magnesium-based porous composite material containing Al2O3 hollow spheres |
CN103921494A (en) * | 2014-04-28 | 2014-07-16 | 中国航天空气动力技术研究院 | Hollow metal ball structure sandwich panel and manufacturing method thereof |
CN104441809A (en) * | 2014-11-26 | 2015-03-25 | 宁波禾顺新材料有限公司 | Metal-fiber foamed aluminum composite layer plate and preparation method thereof |
CN109513906A (en) * | 2019-01-18 | 2019-03-26 | 宁波赛孚新材料科技有限公司 | A kind of hollow sphere metal composite foam production method |
-
2022
- 2022-09-13 CN CN202211111200.5A patent/CN116080182A/en active Pending
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103589891A (en) * | 2013-11-26 | 2014-02-19 | 哈尔滨工业大学 | Preparation methods of magnesium-based porous composite material containing Al2O3 hollow spheres |
CN103921494A (en) * | 2014-04-28 | 2014-07-16 | 中国航天空气动力技术研究院 | Hollow metal ball structure sandwich panel and manufacturing method thereof |
CN104441809A (en) * | 2014-11-26 | 2015-03-25 | 宁波禾顺新材料有限公司 | Metal-fiber foamed aluminum composite layer plate and preparation method thereof |
CN109513906A (en) * | 2019-01-18 | 2019-03-26 | 宁波赛孚新材料科技有限公司 | A kind of hollow sphere metal composite foam production method |
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