Nothing Special   »   [go: up one dir, main page]

CN116080182A - Preparation method of high-energy-absorption layered sandwich protection structure - Google Patents

Preparation method of high-energy-absorption layered sandwich protection structure Download PDF

Info

Publication number
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
Authority
CN
China
Prior art keywords
protective structure
alloy
plate
mass fraction
energy absorption
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202211111200.5A
Other languages
Chinese (zh)
Inventor
张强
孙凯
卫国梁
卫增岩
耿家一
杨文澍
修子扬
陈国钦
姜龙涛
武高辉
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Harbin Institute of Technology
Original Assignee
Harbin Institute of Technology
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Harbin Institute of Technology filed Critical Harbin Institute of Technology
Priority to CN202211111200.5A priority Critical patent/CN116080182A/en
Publication of CN116080182A publication Critical patent/CN116080182A/en
Pending legal-status Critical Current

Links

Images

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/18Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by features of a layer of foamed material
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B22CASTING; POWDER METALLURGY
    • B22DCASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D18/00Pressure casting; Vacuum casting
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B22CASTING; POWDER METALLURGY
    • B22DCASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D23/00Casting processes not provided for in groups B22D1/00 - B22D21/00
    • B22D23/04Casting by dipping
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00Layered products comprising a layer of metal
    • B32B15/04Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/046Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of foam
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00Layered products comprising a layer of metal
    • B32B15/18Layered products comprising a layer of metal comprising iron or steel
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00Layered products comprising a layer of metal
    • B32B15/20Layered products comprising a layer of metal comprising aluminium or copper
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/02Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/08Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/12Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00Ancillary operations in connection with laminating processes
    • B32B38/16Drying; Softening; Cleaning
    • B32B38/164Drying
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04Interconnection of layers
    • B32B7/12Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • CCHEMISTRY; METALLURGY
    • C08ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08GMACROMOLECULAR COMPOUNDS OBTAINED OTHERWISE THAN BY REACTIONS ONLY INVOLVING UNSATURATED CARBON-TO-CARBON BONDS
    • C08G59/00Polycondensates containing more than one epoxy group per molecule; Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups
    • C08G59/18Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups ; e.g. general methods of curing
    • C08G59/40Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups ; e.g. general methods of curing characterised by the curing agents used
    • C08G59/50Amines
    • C08G59/5033Amines aromatic
    • CCHEMISTRY; METALLURGY
    • C09DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09JADHESIVES; NON-MECHANICAL ASPECTS OF ADHESIVE PROCESSES IN GENERAL; ADHESIVE PROCESSES NOT PROVIDED FOR ELSEWHERE; USE OF MATERIALS AS ADHESIVES
    • C09J11/00Features of adhesives not provided for in group C09J9/00, e.g. additives
    • C09J11/02Non-macromolecular additives
    • C09J11/04Non-macromolecular additives inorganic
    • CCHEMISTRY; METALLURGY
    • C09DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09JADHESIVES; NON-MECHANICAL ASPECTS OF ADHESIVE PROCESSES IN GENERAL; ADHESIVE PROCESSES NOT PROVIDED FOR ELSEWHERE; USE OF MATERIALS AS ADHESIVES
    • C09J163/00Adhesives based on epoxy resins; Adhesives based on derivatives of epoxy resins
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C21/00Alloys based on aluminium
    • C22C21/02Alloys based on aluminium with silicon as the next major constituent
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C21/00Alloys based on aluminium
    • C22C21/06Alloys based on aluminium with magnesium as the next major constituent
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C21/00Alloys based on aluminium
    • C22C21/10Alloys based on aluminium with zinc as the next major constituent
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C21/00Alloys based on aluminium
    • C22C21/12Alloys based on aluminium with copper as the next major constituent
    • C22C21/14Alloys based on aluminium with copper as the next major constituent with silicon
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C30/00Alloys containing less than 50% by weight of each constituent
    • C22C30/02Alloys containing less than 50% by weight of each constituent containing copper
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C30/00Alloys containing less than 50% by weight of each constituent
    • C22C30/06Alloys containing less than 50% by weight of each constituent containing zinc
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00Ancillary operations in connection with laminating processes
    • B32B38/16Drying; Softening; Cleaning
    • B32B38/164Drying
    • B32B2038/168Removing solvent
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2250/00Layers arrangement
    • B32B2250/40Symmetrical or sandwich layers, e.g. ABA, ABCBA, ABCCBA
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2266/00Composition of foam
    • B32B2266/04Inorganic
    • B32B2266/045Metal
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00Properties of the layers or laminate
    • B32B2307/50Properties of the layers or laminate having particular mechanical properties
    • B32B2307/56Damping, energy absorption
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2571/00Protective equipment
    • B32B2571/02Protective equipment defensive, e.g. armour plates or anti-ballistic clothing
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02WCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO WASTEWATER TREATMENT OR WASTE MANAGEMENT
    • Y02W30/00Technologies for solid waste management
    • Y02W30/50Reuse, recycling or recovery technologies
    • Y02W30/91Use of waste materials as fillers for mortars or concrete

Landscapes

  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Inorganic Chemistry (AREA)
  • Health & Medical Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Medicinal Chemistry (AREA)
  • Polymers & Plastics (AREA)
  • Laminated Bodies (AREA)

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

Preparation method of high-energy-absorption layered sandwich protection structure
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.
CN202211111200.5A 2022-09-13 2022-09-13 Preparation method of high-energy-absorption layered sandwich protection structure Pending CN116080182A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202211111200.5A CN116080182A (en) 2022-09-13 2022-09-13 Preparation method of high-energy-absorption layered sandwich protection structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202211111200.5A CN116080182A (en) 2022-09-13 2022-09-13 Preparation method of high-energy-absorption layered sandwich protection structure

Publications (1)

Publication Number Publication Date
CN116080182A true CN116080182A (en) 2023-05-09

Family

ID=86208921

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202211111200.5A Pending CN116080182A (en) 2022-09-13 2022-09-13 Preparation method of high-energy-absorption layered sandwich protection structure

Country Status (1)

Country Link
CN (1) CN116080182A (en)

Citations (4)

* Cited by examiner, † Cited by third party
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

Patent Citations (4)

* Cited by examiner, † Cited by third party
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

Similar Documents

Publication Publication Date Title
CN100575861C (en) Plate armour of a kind of metal/ceramic composite and preparation method thereof
CN101650148B (en) Ceramic/composite material interlayer protecting structure
CN101216272A (en) Multiple layer armor protection system
CN109855473A (en) A kind of bulletproof composite armour plate and preparation method thereof
WO2020107674A1 (en) Multilayer bulletproof member, preparation method therefor and application thereof
CN110499434B (en) Multi-scale ceramic reinforced aluminum-based composite material containing close-packed bodies and preparation method thereof
CN113234967B (en) 30mm armor-piercing-resistant elastic gradient aluminum-based composite material and preparation method thereof
CN113587728B (en) Multi-elasticity-resistant multi-curved-surface boron carbide bulletproof flashboard and preparation method thereof
CN112066805A (en) Lightweight fiber/ceramic matrix composite bulletproof structure
CN110438362B (en) Multi-scale multi-shape ceramic phase reinforced aluminum-based elastic-resistant structure composite material and preparation method thereof
WO2023246417A1 (en) Lightweight bulletproof and anti-explosion multiphase composite armor material based on high-toughness heterogeneous interface layer
CN116080182A (en) Preparation method of high-energy-absorption layered sandwich protection structure
CN116399178B (en) Aluminum-based composite foam board and preparation method thereof, and composite bulletproof board and preparation method thereof
CN114434917B (en) Penetration-resistant material and preparation method and application thereof
CN114812276B (en) High-constraint bionic structural armor resistant to multiple bullets and preparation method thereof
CN115028454B (en) Bulletproof ceramic composite material
CN114750469B (en) Anti-elastic composite material containing negative poisson ratio ceramic structure and preparation method thereof
CN106891012A (en) A kind of preparation method of high-strength light bullet proof composite plating
CN108395251B (en) Preparation method of integral silicon carbide wood ceramic bulletproof panel
CN111978682B (en) Preparation method of diamond particle reinforced bulletproof composite material
CN111811324B (en) Light composite armor and manufacturing method thereof
CN112893847A (en) Nano-reinforced foam magnesium-ferrite stainless steel composite board and preparation method thereof
CN113442526A (en) Self-repairing bulletproof composite board and manufacturing method thereof
CN115972699A (en) Composite ceramic layered material and preparation method thereof
CN115612894B (en) Metal composite material with bionic double-penetration structure and preparation method and application thereof

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination