CN113071158A - Composite armor protection structure and preparation method thereof - Google Patents

Composite armor protection structure and preparation method thereof Download PDF

Info

Publication number
CN113071158A
CN113071158A CN202110387759.XA CN202110387759A CN113071158A CN 113071158 A CN113071158 A CN 113071158A CN 202110387759 A CN202110387759 A CN 202110387759A CN 113071158 A CN113071158 A CN 113071158A
Authority
CN
China
Prior art keywords
layer
metal
ceramic
lattice
gradient
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
CN202110387759.XA
Other languages
Chinese (zh)
Inventor
张艳苓
赵冰
韩玉杰
曲海涛
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.)
AVIC Beijing Aeronautical Manufacturing Technology Research Institute
AVIC Manufacturing Technology Institute
Original Assignee
AVIC Beijing Aeronautical Manufacturing Technology Research Institute
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 AVIC Beijing Aeronautical Manufacturing Technology Research Institute filed Critical AVIC Beijing Aeronautical Manufacturing Technology Research Institute
Priority to CN202110387759.XA priority Critical patent/CN113071158A/en
Publication of CN113071158A publication Critical patent/CN113071158A/en
Pending legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/005—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising one layer of ceramic material, e.g. porcelain, ceramic tile
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B18/00—Layered products essentially comprising ceramics, e.g. refractory products
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered 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
    • B32B3/02—Layered 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
    • B32B3/08—Layered 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/06—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B9/041—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material of metal
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H5/00—Armour; Armour plates
    • F41H5/02—Plate construction
    • F41H5/04—Plate construction composed of more than one layer
    • F41H5/0414—Layered armour containing ceramic material
    • F41H5/0421—Ceramic layers in combination with metal layers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H5/00—Armour; Armour plates
    • F41H5/02—Plate construction
    • F41H5/04—Plate construction composed of more than one layer
    • F41H5/0471—Layered armour containing fibre- or fabric-reinforced layers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/558—Impact strength, toughness
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2571/00—Protective equipment
    • B32B2571/02—Protective equipment defensive, e.g. armour plates, anti-ballistic clothing

Landscapes

  • Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

The invention relates to a composite armor protective structure, which comprises a metal ceramic gradient layer and a metal lattice layer, wherein the metal ceramic gradient layer is an elastic surface, the metal ceramic gradient layer comprises a ceramic layer, a metal layer and a ceramic/metal mixed gradient transition layer which are mutually connected, and the ceramic/metal mixed gradient transition layer is positioned between the ceramic layer and the metal layer; the metal layer is connected with the metal lattice layer. The invention relates to a preparation method of the composite armor protection structure. The composite armor protection structure and the preparation method thereof aim to solve the problems of low bonding strength of layer interfaces and poor structural integrity caused by the difficulty in compounding the ceramic and the toughness layer of the existing composite armor material.

Description

Composite armor protection structure and preparation method thereof
Technical Field
The invention relates to the technical field of armor protection materials, in particular to a composite armor protection structure and a preparation method thereof.
Background
The ceramic/back plate composite armor is the light composite armor which has the simplest structure and is researched most at present, and is formed by bonding a ceramic panel and a metal or composite material back plate. The panel is usually made of Al2O3SiC and B4C ceramics, etc.; the back plate is made of metal or composite material with good toughness, such as steel, aluminum alloy and Kevlar composite material. With Al2O3Glass fiber composite material, B4A new generation of lightweight bulletproof materials represented by C/aramid, and in recent years, B has been developed4C and ultra-high molecular weight polyethylene fiber composite armor materials have become the main armor materials used in modern helicopters, such as the most advanced AH-64 ("Apache") gunships in the world, which are used, and a large amount of B is used around cabins and ejection seats4C/aramid fiber and Al2O3The glass fiber light composite material armor plate greatly improves the armor protection level and the bullet-resistant survival capability of the helicopter.
However, the composite armor material is difficult to compound with the ceramic and the toughness layer, and is usually bonded by adopting a bonding agent, so that the bonding strength of the layer interface is low, the structural integrity is poor, the armor protection effect is influenced, and the composite armor material is difficult to be used for ultra-high-speed collision protection.
Accordingly, the inventors provide a composite armor protective structure and method of making the same.
Disclosure of Invention
(1) Technical problem to be solved
The embodiment of the invention provides a composite armor protection structure and a preparation method thereof. The composite armor material solves the technical problems of low bonding strength of layer interfaces and poor structural integrity caused by the difficulty in compounding the ceramic and the toughness layer in the conventional composite armor material.
(2) Technical scheme
A first aspect of an embodiment of the present invention provides a composite armor protective structure, including a cermet gradient layer and a metal lattice layer, where the cermet gradient layer is a bullet-facing surface, the cermet gradient layer includes a ceramic layer, a metal layer, and a ceramic/metal hybrid gradient transition layer, which are connected to each other, and the ceramic/metal hybrid gradient transition layer is located between the ceramic layer and the metal layer; the metal layer is connected with the metal lattice layer.
Further, the ceramic layer is Al2O3Ceramic layer, SiC ceramic layer and B4C, one of ceramic layers.
Further, the metal layer is a Ti layer.
Furthermore, the metal lattice layer comprises a first metal panel, a second metal panel and middle lattice ribs, and the middle lattice ribs are located between the first metal panel and the second metal panel.
Furthermore, the first metal panel and the second metal panel are both titanium alloy panels, and the middle lattice ribs are titanium alloy ribs.
Furthermore, the middle lattice ribs are of a one-layer lattice structure or a multi-layer lattice structure.
Further, the metal layer and the metal lattice layer are in diffusion connection.
A second aspect of an embodiment of the present invention provides a method of making a composite armor protective structure as described above, the method comprising the steps of:
preparing a metal ceramic gradient layer;
preparing a metal lattice layer;
carrying out diffusion connection on the metal ceramic gradient layer and the metal lattice layer;
and performing superplastic forming on the metal ceramic gradient layer and the metal dot matrix layer after the diffusion connection is completed to obtain the composite armor protection structure.
Further, the preparation of the cermet gradient layer specifically comprises the following steps:
optimizing the number of layers of the metal ceramic gradient layer, the thickness of each layer and the gradient distribution index of the gradient layer by utilizing finite element simulation;
mixing powder and layering according to the optimized parameters;
and carrying out vacuum hot-pressing sintering.
Further, the preparation of the metal lattice layer specifically comprises the following steps:
fixing the middle lattice ribs at preset positions by spot welding;
sealing the first metal panel and the second metal panel by argon arc welding to form a vacuum pocket;
and welding a pipeline on a non-diffusion area at the edge of the vacuum bag, and detecting the tightness of the vacuum bag by vacuumizing.
(3) Advantageous effects
In summary, the composite armor protection structure comprises the metal ceramic gradient layer and the metal lattice layer, the bullet-facing surface of the composite armor protection structure is made of the metal/ceramic mixed gradient material, one side of the material is made of pure ceramic, the other side of the material is made of pure metal, the ceramic/metal mixed gradient transition is adopted in the middle of the composite armor protection structure, the pure metal side of the metal ceramic gradient material is connected with the titanium alloy lattice sandwich structure panel, and metallurgical bonding of an interface is achieved. The composite armor material solves the technical problems of low bonding strength of layer interfaces and poor structural integrity caused by the difficulty in compounding the ceramic and the toughness layer in the conventional composite armor material. The armor protection structure material has strong designability and good structural integrity, and the lattice structure has a certain energy absorption effect, so that the impact resistance of the armor material can be further improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic illustration of a composite armor protective structure provided by an embodiment of the present invention;
FIG. 2 is a schematic view of another composite armor protective structure provided by an embodiment of the present invention;
fig. 3 is a schematic flow chart of a method for manufacturing a composite armor protective structure according to an embodiment of the invention.
In the figure:
1-a cermet gradient layer; 101-a ceramic layer; 102-a metal layer; 103-ceramic/metal hybrid gradient transition layer; 2-a metal lattice layer; 201-a first metal panel; 202-a second metal panel; 203-middle lattice ribs.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the invention and are not intended to limit the scope of the invention, i.e., the invention is not limited to the embodiments described, but covers any modifications, alterations, and improvements in the parts, components, and connections without departing from the spirit of the invention.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Fig. 1-2 are schematic diagrams of a composite armor protective structure according to a first aspect of an embodiment of the present invention, including a cermet gradient layer 1 and a metal lattice layer 2, where the cermet gradient layer 1 is a bullet-facing surface, the cermet gradient layer 1 includes a ceramic layer 101, a metal layer 102, and a ceramic/metal hybrid gradient transition layer 103 connected to each other, and the ceramic/metal hybrid gradient transition layer 103 is located between the ceramic layer 101 and the metal layer 102; the metal layer 102 is connected to the metal lattice layer 2.
In the above embodiment, the metal/ceramic hybrid gradient structure and the metal lattice structure can be optimally designed according to the bulletproof requirement by using the metal ceramic gradient material to replace the traditional ceramic panel and using the metal lattice sandwich structure to replace the traditional metal or composite backboard.
In some alternative embodiments, ceramic layer 101 is Al2O3Ceramic layer, SiC ceramic layer and B4C, one of ceramic layers.
In some alternative embodiments, metal layer 102 is a Ti layer.
In some optional embodiments, the metal lattice layer 2 includes a first metal panel 201, a second metal panel 202, and an intermediate lattice rib 203, and the intermediate lattice rib 203 is located between the first metal panel 201 and the second metal panel 202.
In some optional embodiments, the first metal panel 201 and the second metal panel 202 are both titanium alloy panels, and the middle lattice ribs 203 are titanium alloy ribs.
In some alternative embodiments, as shown in fig. 1-2, the intermediate lattice ribs 203 are a one-layer lattice structure or a multi-layer lattice structure.
In some alternative embodiments, the metal layer 102 and the metal lattice layer 2 are diffusion bonded. The back plate of the metal ceramic gradient layer 1 and the face plate of the metal lattice layer 2 are in metallurgical bonding through diffusion connection, and the interface bonding quality is high and the structural integrity is good.
Fig. 3 is a schematic flow chart of a method of making a composite armor protective structure according to a second aspect of an embodiment of the invention, the method comprising the steps of:
s1, preparing a metal ceramic gradient layer 1;
s2, preparing a metal lattice layer 2;
s3, diffusion connection is carried out on the metal ceramic gradient layer 1 and the metal lattice layer 2;
and S4, superplastic forming the diffusion-connected metal ceramic gradient layer 1 and the metal lattice layer 2 to obtain the composite armor protective structure.
In the above embodiment, in step S1, one end face of the cermet gradient layer 1 is made of pure ceramic, the other end face is made of pure Ti, and the ceramic side may be Al2O3、SiC、B4C, and the middle is in gradient transition by a plurality of layers of Ti/ceramic mixed. Firstly, the methodThe method aims to improve the shock resistance of the Ti/ceramic hybrid gradient material, and optimizes the number of layers of the gradient material, the thickness of each layer and the gradient distribution index of the gradient layer by utilizing finite element simulation. And mixing powder and layering according to the optimized parameters, then carrying out vacuum hot-pressing sintering, and adding sintering aids such as MgO and the like into the ceramic in order to reduce the sintering temperature of the ceramic and improve the sintering compactness, wherein the sintering temperature is 1300-1500 ℃, and the sintering pressure is 30-50 MPa.
In step S2, the metal lattice layer is composed of a first metal panel 201, a first metal panel 202 and a middle lattice rib 203, the thicknesses of the first metal panel 201 and the first metal panel 202 are 1-6 mm, the thickness of the middle lattice rib 203 is 0.6-2 mm, the rib is fixed at a designed position by spot welding, the upper and lower panels are sealed by argon arc welding to form a vacuum pocket, a pipeline is welded in a non-diffusion area at the edge of the pocket, and the pocket is vacuumized and the pocket sealing performance is detected. The metal lattice layer may be a layer of lattice structure or a multilayer lattice structure.
In step S3, the diffusion connection between the cermet gradient layer 1 and the titanium alloy lattice layer 2 and the diffusion connection between the lattice ribs and the panel are completed under the same thermal cycle, the diffusion connection temperature is 920-950 ℃, the pressure is 1.5-2.5 MPa, the pressure holding time is 1-3 hours, and the diffusion environment is vacuum diffusion.
In step S4, performing superplastic forming on the diffused prefabricated blank under the same thermal cycle to obtain a metal ceramic mixed gradient composite armor structure, wherein the forming temperature is 920-950 ℃, the pressurizing rate pressure is 1.5-2.5 MPa, and the pressure maintaining time is 1-2 hours.
The invention provides a preparation method of a composite armor protection structure, which utilizes a metal ceramic gradient material to replace a traditional ceramic panel, utilizes a titanium alloy lattice sandwich structure to replace a traditional metal or composite material back plate, and adopts a diffusion connection method between the panel and the back plate to realize metallurgical bonding, and the preparation method has the following steps:
(1) the armor protection structure has strong designability, and the metal/ceramic hybrid gradient structure and the metal lattice structure can be optimally designed according to the bulletproof requirement;
(2) the metallurgical bonding is realized between the metal ceramic mixed gradient material back plate and the metal lattice sandwich structure panel through diffusion connection, the interface bonding quality is high, and the structural integrity is good;
(3) the diffusion connection between the metal ceramic gradient material and the metal lattice prefabricated blank and the diffusion connection/superplastic forming of the lattice structure can be completed under one thermal cycle, so that the time and the energy are saved, and the efficiency is improved.
In some optional embodiments, in step S1, the preparation of the cermet gradient layer 1 specifically includes the following steps:
s101, optimizing the number of layers of the metal ceramic gradient layer 1, the thickness of each layer and the gradient distribution index of the gradient layer by utilizing finite element simulation;
s102, mixing powder and layering according to the optimized parameters;
and S103, carrying out vacuum hot-pressing sintering.
In some optional embodiments, in step S2, the preparation of the metal lattice layer 2 specifically includes the following steps:
s201, fixing middle dot matrix ribs 203 at preset positions by spot welding;
s202, sealing the first metal panel 201 and the second metal panel 202 by argon arc welding to form a vacuum pocket;
s203, welding a pipeline on the non-diffusion area of the edge of the vacuum pocket, and detecting the sealing performance of the vacuum pocket by vacuumizing.
The invention will now be illustrated by the following specific examples
Examples
(1)Al2O3Preparation of a/Ti gradient layer
The upper layer of the metal ceramic gradient layer is Al2O3Ceramic, pure Ti as lower layer and three Al layers as middle layer2O3Mixed gradient transition of/Ti. To increase Al2O3The impact resistance of the/Ti hybrid gradient material is an optimization target, the number of layers of the gradient material, the thickness of each layer and the gradient distribution index of the gradient layer are optimized by utilizing finite element simulation, and layering is carried out according to an optimization result. Wherein the metal ceramicThe ceramic gradient material is Al with the powder granularity of 10-20 mu m2O3Powder and 5-10 μm pure titanium powder for Al2O3The ceramic realizes high-density sintering below a Ti melting point (1668 ℃), and sintering aid MgO powder is added into the ceramic, wherein the MgO powder has the granularity of 5-10 mu m and the addition amount of 2-3 wt%. The cermet gradient material starts from a pure Ti layer and passes through Al with different mass ratios2O3the/Ti mixed gradient layer gradually transits to pure Al2O3And (3) a layer. Adding sintering aid MgO to mix Al2O3The sintering temperature of the/Ti gradient material is up to 1500 ℃, the sintering pressure is 40MPa, and the density of the gradient material obtained under the condition is more than 97 percent.
(2) Preparation of titanium alloy lattice layer
The material of the titanium alloy lattice layer is Ti6Al4The prefabricated blank of the V titanium alloy and titanium alloy dot matrix layer is composed of an upper titanium alloy panel, a lower titanium alloy panel and a middle dot matrix rib, the thickness of the upper panel and the thickness of the lower panel are 3mm, the thickness of the dot matrix rib is 0.8mm, the rib is fixed at a designed position by spot welding, the upper panel and the lower panel are sealed by argon arc welding to form a vacuum pocket, a pipeline is welded in a non-diffusion area at the edge of the pocket, the vacuum is pumped, and the tightness of the pocket is detected.
(3) Diffusion bonding
The diffusion connection between the metal ceramic gradient layer and the titanium alloy lattice layer and the diffusion connection between the lattice ribs and the panel are completed under the same thermal cycle, the diffusion connection temperature is 920-950 ℃, the pressure is 2MPa, the pressure maintaining time is 1.5 hours, and the diffusion environment is vacuum diffusion.
(4) Titanium alloy lattice superplastic forming
Superplastic forming is carried out on the well-diffused prefabricated blank under the same thermal cycle to obtain a metal ceramic mixed gradient composite armor structure, the forming temperature is 930 ℃, the pressurizing rate pressure is high, the forming pressure is 1.5MPa, and the pressure maintaining time is 1 hour, so as to obtain Al2O3the/Ti gradient material and the titanium alloy lattice composite armor protection structure.
It should be clear that the embodiments in this specification are described in a progressive manner, and the same or similar parts in the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. The present invention is not limited to the specific steps and structures described above and shown in the drawings. Also, a detailed description of known process techniques is omitted herein for the sake of brevity.
The above are merely examples of the present application and are not intended to limit the present application. Various modifications and alterations to this application will become apparent to those skilled in the art without departing from the scope of this invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.

Claims (10)

1. The composite armor protection structure is characterized by comprising a metal ceramic gradient layer (1) and a metal lattice layer (2), wherein the metal ceramic gradient layer (1) is a bullet-facing surface, the metal ceramic gradient layer (1) comprises a ceramic layer (101), a metal layer (102) and a ceramic/metal mixed gradient transition layer (103) which are connected with each other, and the ceramic/metal mixed gradient transition layer (103) is positioned between the ceramic layer (101) and the metal layer (102); the metal layer (102) is connected with the metal lattice layer (2).
2. Composite armor protective structure according to claim 1, characterized in that said ceramic layer (101) is Al2O3Ceramic layer, SiC ceramic layer and B4C, one of ceramic layers.
3. The composite armor protective structure according to claim 1, wherein said metal layer (102) is a Ti layer.
4. Composite armor protective structure according to claim 1, characterized in that said metal lattice layer (2) comprises a first metal panel (201), a second metal panel (202) and intermediate lattice ribs (203), said intermediate lattice ribs (203) being located between said first metal panel (201), said second metal panel (202).
5. Composite armor protective structure according to claim 4, wherein said first metal panel (201) and said second metal panel (202) are both titanium alloy panels and said intermediate lattice ribs (203) are titanium alloy ribs.
6. Composite armor protective structure according to claim 4 or 5, characterized in that said intermediate lattice ribs (203) are of one-layer lattice structure or of multilayer lattice structure.
7. Composite armor protective structure according to claim 1, characterized in that said metal layer (102) and said metal lattice layer (2) are diffusion bonded.
8. A method of making a composite armor protective structure according to any one of claims 1-7, comprising the steps of:
preparing a metal ceramic gradient layer (1);
preparing a metal lattice layer (2);
carrying out diffusion connection on the metal ceramic gradient layer (1) and the metal lattice layer (2);
and (3) performing superplastic forming on the metal ceramic gradient layer (1) and the metal dot matrix layer (2) after the diffusion connection is completed to obtain the composite armor protection structure.
9. Method for the production of a composite armor protective structure according to claim 8, characterized in that said production of a cermet gradient layer (1) comprises in particular the steps of:
optimizing the number of layers of the metal ceramic gradient layer (1), the thickness of each layer and the gradient distribution index of the gradient layer by utilizing finite element simulation;
mixing powder and layering according to the optimized parameters;
and carrying out vacuum hot-pressing sintering.
10. Method for the production of a composite armor protective structure according to claim 8, wherein said production of a metal lattice layer (2) comprises the following steps:
fixing the middle lattice ribs (203) at preset positions by spot welding;
sealing the first metal panel (201) and the second metal panel (202) by argon arc welding to form a vacuum pocket;
and welding a pipeline on a non-diffusion area at the edge of the vacuum bag, and detecting the tightness of the vacuum bag by vacuumizing.
CN202110387759.XA 2021-04-12 2021-04-12 Composite armor protection structure and preparation method thereof Pending CN113071158A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202110387759.XA CN113071158A (en) 2021-04-12 2021-04-12 Composite armor protection structure and preparation method thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202110387759.XA CN113071158A (en) 2021-04-12 2021-04-12 Composite armor protection structure and preparation method thereof

Publications (1)

Publication Number Publication Date
CN113071158A true CN113071158A (en) 2021-07-06

Family

ID=76617302

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202110387759.XA Pending CN113071158A (en) 2021-04-12 2021-04-12 Composite armor protection structure and preparation method thereof

Country Status (1)

Country Link
CN (1) CN113071158A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116872573A (en) * 2023-06-02 2023-10-13 华中科技大学 Heat insulation and bearing integrated material and preparation method and application thereof

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090286100A1 (en) * 2006-10-27 2009-11-19 University Of Virginia Patent Foundation Manufacture of Lattice Truss Structures from Monolithic Materials
CN101658973A (en) * 2009-09-16 2010-03-03 华北电力大学 Preparation method of composite armor plate consisting of metal-ceramic cladding layer-metal
US20110151267A1 (en) * 2006-06-30 2011-06-23 Withers James C Composite armor tile based on a continuously graded ceramic-metal composition and manufacture thereof
CN103612007A (en) * 2013-11-21 2014-03-05 中国航空工业集团公司北京航空制造工程研究所 Preparation method of high-temperature alloy three-dimensional lattice sandwich structure
US20140087202A1 (en) * 2012-09-24 2014-03-27 China Weapon Science Academy Ningbo Branch Metal Matrix Ceramic Composite and Manufacturing Method and Application Thereof
CN107152888A (en) * 2017-07-14 2017-09-12 中国科学技术大学 A kind of lightweight impact resistance protective plate
CN107976115A (en) * 2017-10-27 2018-05-01 浙江立泰复合材料股份有限公司 A kind of boron carbide-titanium alloy composite armour
CN108326315A (en) * 2016-11-18 2018-07-27 中国航空工业集团公司北京航空制造工程研究所 A kind of multi-gradient armor structure and its manufacturing method
CN109405647A (en) * 2018-11-05 2019-03-01 中国航空制造技术研究院 Brickwall multilayer tortoise plastron protective device and preparation method thereof
CN110453104A (en) * 2019-09-05 2019-11-15 中国航空制造技术研究院 A kind of titanium-based SiC-Ti mixes functionally gradient material (FGM) and preparation method thereof
CN112461050A (en) * 2020-12-12 2021-03-09 江西洪都航空工业集团有限责任公司 Bulletproof armor containing metal lattice structure

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110151267A1 (en) * 2006-06-30 2011-06-23 Withers James C Composite armor tile based on a continuously graded ceramic-metal composition and manufacture thereof
US20090286100A1 (en) * 2006-10-27 2009-11-19 University Of Virginia Patent Foundation Manufacture of Lattice Truss Structures from Monolithic Materials
CN101658973A (en) * 2009-09-16 2010-03-03 华北电力大学 Preparation method of composite armor plate consisting of metal-ceramic cladding layer-metal
US20140087202A1 (en) * 2012-09-24 2014-03-27 China Weapon Science Academy Ningbo Branch Metal Matrix Ceramic Composite and Manufacturing Method and Application Thereof
CN103612007A (en) * 2013-11-21 2014-03-05 中国航空工业集团公司北京航空制造工程研究所 Preparation method of high-temperature alloy three-dimensional lattice sandwich structure
CN108326315A (en) * 2016-11-18 2018-07-27 中国航空工业集团公司北京航空制造工程研究所 A kind of multi-gradient armor structure and its manufacturing method
CN107152888A (en) * 2017-07-14 2017-09-12 中国科学技术大学 A kind of lightweight impact resistance protective plate
CN107976115A (en) * 2017-10-27 2018-05-01 浙江立泰复合材料股份有限公司 A kind of boron carbide-titanium alloy composite armour
CN109405647A (en) * 2018-11-05 2019-03-01 中国航空制造技术研究院 Brickwall multilayer tortoise plastron protective device and preparation method thereof
CN110453104A (en) * 2019-09-05 2019-11-15 中国航空制造技术研究院 A kind of titanium-based SiC-Ti mixes functionally gradient material (FGM) and preparation method thereof
CN112461050A (en) * 2020-12-12 2021-03-09 江西洪都航空工业集团有限责任公司 Bulletproof armor containing metal lattice structure

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116872573A (en) * 2023-06-02 2023-10-13 华中科技大学 Heat insulation and bearing integrated material and preparation method and application thereof
CN116872573B (en) * 2023-06-02 2024-03-19 华中科技大学 Heat insulation and bearing integrated material and preparation method and application thereof

Similar Documents

Publication Publication Date Title
CN109405647B (en) Brick wall type multilayer tortoise shell protection device and preparation method thereof
CN108372692B (en) Multi-element composite toughening type bionic structure armor and preparation method thereof
US8528457B2 (en) Method of producing a hybrid tile metal matrix composite armor
CN100570268C (en) Fibre-reinforced metal/ceramic laminated composite material prevention plate
CN111272016B (en) Bulletproof composite armor and preparation method thereof
AU2003304083B2 (en) Armor system with monolithic ceramic shell
CN103727842B (en) Fiber/ceramic/metal composite material bulletproof plate and manufacturing method thereof
CN109855473A (en) A kind of bulletproof composite armour plate and preparation method thereof
WO2008053041A1 (en) Stiffened casing for an aircraft or spacecraft with a laminate stringer of high rigidity and corresponding laminate stringer
CN113071158A (en) Composite armor protection structure and preparation method thereof
US8464626B2 (en) Multi-layer metal matrix composite armor with edge protection
CN108437574A (en) Shock resistance case material, preparation method, the preparation method of digital product shell and digital product shell
WO2023246417A1 (en) Lightweight bulletproof and anti-explosion multiphase composite armor material based on high-toughness heterogeneous interface layer
CN108871073A (en) A kind of ceramic laminated composite armour of TC4-Al3Ti-TC4- and preparation method thereof
CN113619225A (en) Gradient bulletproof impact-resistant gradient material structure and preparation method thereof
CN110220418B (en) Microporous plate composite material, microporous plate, light bulletproof armor and manufacturing method thereof
CN113983868A (en) Gradient ceramic column reinforced aluminum-based composite armor plate and preparation method thereof
Du et al. Study on the protective performance of high-performance multi-scale (SiCh-p+ B4Cp)/5083Al ceramic array armor with excellent ballistic properties
CN114812276B (en) High-constraint bionic structural armor resistant to multiple bullets and preparation method thereof
CN205090879U (en) Shellproof anti -riot board of composite construction
US20120247312A1 (en) Structural panel insert with honeycomb core
CN208410950U (en) Shock resistance case material and digital product shell
CN201016655Y (en) Fiber reinforced metal/ceramic laminar composite guard plate
CN116518780A (en) Functional gradient armor structure for resisting armor piercing bullet with diameter of 14.5mm
CN107152888B (en) A kind of lightweight impact resistance protective plate

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
RJ01 Rejection of invention patent application after publication
RJ01 Rejection of invention patent application after publication

Application publication date: 20210706