CN113210607B - Auxiliary material, composite shaped charge liner containing auxiliary material and preparation method of composite shaped charge liner - Google Patents

Auxiliary material, composite shaped charge liner containing auxiliary material and preparation method of composite shaped charge liner Download PDF

Info

Publication number
CN113210607B
CN113210607B CN202110281234.8A CN202110281234A CN113210607B CN 113210607 B CN113210607 B CN 113210607B CN 202110281234 A CN202110281234 A CN 202110281234A CN 113210607 B CN113210607 B CN 113210607B
Authority
CN
China
Prior art keywords
powder
shaped charge
liner
auxiliary material
charge liner
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.)
Active
Application number
CN202110281234.8A
Other languages
Chinese (zh)
Other versions
CN113210607A (en
Inventor
刘杰
刘洋
李巍
吕卓昆
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.)
Dragon Totem Technology Hefei Co ltd
Original Assignee
Nanjing Vocational University of Industry Technology NUIT
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 Nanjing Vocational University of Industry Technology NUIT filed Critical Nanjing Vocational University of Industry Technology NUIT
Priority to CN202110281234.8A priority Critical patent/CN113210607B/en
Publication of CN113210607A publication Critical patent/CN113210607A/en
Application granted granted Critical
Publication of CN113210607B publication Critical patent/CN113210607B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/10—Sintering only
    • B22F3/105—Sintering only by using electric current other than for infrared radiant energy, laser radiation or plasma ; by ultrasonic bonding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F9/00—Making metallic powder or suspensions thereof
    • B22F9/02—Making metallic powder or suspensions thereof using physical processes
    • B22F9/04—Making metallic powder or suspensions thereof using physical processes starting from solid material, e.g. by crushing, grinding or milling
    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
    • C09D175/00—Coating compositions based on polyureas or polyurethanes; Coating compositions based on derivatives of such polymers
    • C09D175/04—Polyurethanes
    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
    • C09D5/00—Coating compositions, e.g. paints, varnishes or lacquers, characterised by their physical nature or the effects produced; Filling pastes
    • C09D5/03—Powdery paints
    • C09D5/033—Powdery paints characterised by the additives
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C27/00—Alloys based on rhenium or a refractory metal not mentioned in groups C22C14/00 or C22C16/00
    • C22C27/04—Alloys based on tungsten or molybdenum
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C30/00—Alloys containing less than 50% by weight of each constituent
    • C22C30/02—Alloys containing less than 50% by weight of each constituent containing copper
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
    • C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
    • C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
    • C23C24/106—Coating with metal alloys or metal elements only
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B3/00—Blasting cartridges, i.e. case and explosive
    • F42B3/28—Cartridge cases characterised by the material used, e.g. coatings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • B22F2003/248—Thermal after-treatment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F9/00—Making metallic powder or suspensions thereof
    • B22F9/02—Making metallic powder or suspensions thereof using physical processes
    • B22F9/04—Making metallic powder or suspensions thereof using physical processes starting from solid material, e.g. by crushing, grinding or milling
    • B22F2009/043—Making metallic powder or suspensions thereof using physical processes starting from solid material, e.g. by crushing, grinding or milling by ball milling

Abstract

The invention discloses an auxiliary material, a composite shaped charge liner containing the auxiliary material and a preparation method of the composite shaped charge liner, and belongs to the technical field of shaped charge liners. The method specifically comprises the following steps: weighing copper powder, tungsten powder, aluminum powder and nickel powder raw materials according to a proportion, and obtaining tungsten-copper mixed powder in a ball mill and an inert gas atmosphere; step two, mixing the thermoplastic agent and the adsorbent to obtain the mixture with the density of
Figure DEST_PATH_IMAGE002
、
Figure DEST_PATH_IMAGE004
、
Figure DEST_PATH_IMAGE006
The auxiliary material of (1); step three, forming a shaped charge liner semi-finished product on the solid mould; step four, respectively obtaining the densities of,
Figure 270504DEST_PATH_IMAGE004
、
Figure 594169DEST_PATH_IMAGE006
The auxiliary materials are respectively sprayed on the outer surfaces of the flat top, the frustum and the curved surface in the semi-finished product of the shaped charge liner to form cladding layers, and a shaped charge liner precursor is obtained; and step five, placing the shaped charge liner precursor obtained in the step four in a resistance furnace for recrystallization annealing treatment, and cooling the furnace. The liner prepared by the invention has strong power to break nails.

Description

Auxiliary material, composite shaped charge liner containing auxiliary material and preparation method of composite shaped charge liner
Technical Field
The invention belongs to the technical field of shaped charge liners, and particularly relates to an auxiliary material, a composite shaped charge liner containing the auxiliary material and a preparation method of the composite shaped charge liner.
Background
Prior art shaped charges have a metal outer case or charge housing. The highly explosive material is disposed within the metal housing. The liner retains the explosive material within the outer jacket prior to detonation. The priming post provides a detonating link between the detonating cord and the explosive substance. When the shaped charge coat is detonated, the liner forms a jet portion of the liner. The jet portion is propelled away from the housing and in a direction toward the target.
At present, liner materials are mainly divided into metal materials, multiphase composite materials and non-metal materials. The research of metal materials mainly comprises a pure metal liner and an alloy liner, and considering that the pure metal liner has many problems, the alloy liner compounds metals or alloys with different properties according to the design requirements of the liner, thereby making good use of the advantages and avoiding the disadvantages. It is common to add a small amount of Zn (zinc) and Ni (nickel) in W-Cu (tungsten-copper) alloy to improve the compactness, strength and plasticity of the alloy, but the tungsten-copper composite liner is very sensitive to explosive height (namely the placement height) of explosive charge, and the depth of a broken nail is rapidly reduced under the condition of large explosive height, and the most ideal explosive height is 3 times of caliber size. This is also a common feature of the presence of a composite liner: the depth of broken nail can be improved by about 30% compared with a pure copper liner under the condition of small explosive height, but the performance is rapidly deteriorated under the condition of large explosive height, and ductile jet flow cannot be obtained. Furthermore, due to the alloy and the poor flowability of the metal powder, and the random factors in the filling and pressing process are many, the quality (density) distribution of the mold cover is difficult to control, so that the performance is unstable and the penetration fluctuation is large, which is a point to be improved.
Disclosure of Invention
The invention provides a composite shaped charge liner and a preparation method thereof, aiming at solving the technical problems in the background technology.
The invention adopts the following technical scheme: a preparation method of a composite shaped charge liner specifically comprises the following steps:
weighing copper powder, tungsten powder, aluminum powder and nickel powder raw materials according to a proportion, and obtaining tungsten-copper mixed powder in a ball mill and an inert gas atmosphere;
step two, mixing the thermoplastic agent and the adsorbent to obtain the mixture with the density of rho 1 、ρ 2 、ρ 3 The auxiliary materials of (1);
step three, establishing an entity mould of the shaped charge liner, feeding the tungsten-copper mixed powder obtained in the step one into the irradiation range of a laser beam for melting through a powder feeder and a coaxial nozzle by adopting a synchronous powder feeding method, and spraying the tungsten-copper mixed powder on the entity mould to form a semi-finished product of the shaped charge liner;
step four, adopting a synchronous powder feeding method to respectively obtain the densities rho in the step two 1 、ρ 2 、ρ 3 The auxiliary materials are fed into the irradiation range of laser beams through a powder feeder and a coaxial nozzle to be melted and respectively sprayed on the outer surfaces of a flat top, a frustum and a curved surface in the semi-finished product of the shaped charge liner to form cladding layers, and a shaped charge liner precursor is obtained;
and step five, placing the liner precursor obtained in the step four in a resistance furnace for recrystallization annealing treatment, and cooling the furnace.
In a further embodiment, the particle size of the copper powder is 1.2 to 1.8 μm, and the particle size of the tungsten powder is 2.2 to 2.8 μm.
In a further embodiment, the annealing temperature is 300 ℃ and the time is 3 hours.
In a further embodiment, the parameters of the laser beam in step three and step four are: the single-speed laser power is 2.5kW, the diameter of a focusing light spot is 4mm, and the movement speed of the numerical control workbench is 350mm/s.
In further embodiments, the liner is constructed as described in the following examples, including flat top, truncated cone, curved surface, and cladding layer, and more particularly, the following composite liner.
A composite liner is prepared by the preparation method.
In a further embodiment, the composite liner comprises:
flat top;
the top of the frustum is connected with the flat top in a sealing manner;
the curved surface is connected with the bottom of the frustum; wherein, the connection part of the frustum and the curved surface is in smooth transition;
wherein the flat top, the frustum and the curved surface are formed by pressing composite metal powder;
further comprising: the cladding layer is coated on the outer surfaces of the flat top, the frustum and the curved surface in sequence from top to bottom, and the cladding layer is formed by pressing nonmetal powder.
In a further embodiment, the density of the cladding layer at the outer surface of the flat top is defined as ρ 1 The density of the cladding layer at the outer surface of the frustum is rho 2 The density of the cladding layer at the outer surface of the curved surface is rho 3 And ρ 1 ＜ρ 2 ＜ρ 3 。
In a further embodiment, the curved surface comprises:
Figure BDA0002978498350000021
the first straight line segments and the phi second straight line segments are connected end to end between the adjacent first straight line segments and the second straight line segments, and the first straight line segments and the second straight line segments are connected end to endThe two straight line segments are in smooth transition.
In a further embodiment, the length of the first straight line segment is defined as iota i ，
Figure BDA0002978498350000031
Define the length of the second straight line segment as ζ i And ζ is i ＝1.38ι i (ii) a i is a current first straight line segment and a current second straight line segment;
defining the thickness of the frustum as D1, the thickness of the curved surface as D2, the thickness of the cladding layer as D3,
and, D1: D2: D3=1 (0.7-0.8): 0.2-0.3).
In a further embodiment, the cladding layer is made of an auxiliary material formed by mixing a thermoplastic agent and an adsorbent. The molecular structural formulas of the adsorbent and the thermoplastic agent are respectively as follows.
For making a liner as described above for forming a cladding layer.
In a further embodiment, the composite material is formed by mixing thermoplastic agent and adsorbent;
wherein the molecular structural formula of the thermoplastic agent is as follows:
Figure BDA0002978498350000032
wherein R is 1 is-CH 2 -CH 3 ，R 2 is-CH 2 -CH 2 -CH 3 R is
Figure BDA0002978498350000033
Wherein n is an integer of 8 to 12.
In a further embodiment, the molecular structural formula of the adsorbent is as follows:
Figure BDA0002978498350000034
wherein m is an integer of 8 to 10.
The invention has the beneficial effects that:
the external surface of the existing liner is coated with thermoplastic agent and adsorbent. When the shaped charge is detonated and generates high temperature during use, high-speed jet flow is formed at the flat top of the shaped charge cover to move forwards, and because the cladding layer is coated on the outer surface and is in direct contact with the high temperature, strong reaction is generated between the soft section and the hard section in the thermoplastic agent and the metal powder to form energetic jet flow under the action of the high temperature, the viscosity of the thermoplastic agent is enhanced, and the nail-breaking power of the jet flow is increased. Meanwhile, the adsorbent has stronger chelating force, so that the metal particles around the adsorbent can be coated at the moment of explosion, the metal particles move forwards along with the heat-following agent, and the impact force of the metal particles is further increased.
The liner comprises a flat top, a frustum and a curved surface, and is used for forming high-speed jet flow at the moment of explosion, and the wavy structure on the curved surface is used for increasing the coating area of a cladding layer, increasing the heating area of the liner and accelerating the formation of jet flow.
Drawings
Fig. 1 is a structural view of a solid mold used in example 1.
Fig. 2 is a structural view of a solid mold used in example 3.
FIG. 3 is a comparative diagram of test example 1.
FIG. 4 is a comparative graph of test example 2.
FIG. 5 is a comparative diagram of detection example 3.
Each of the labels in fig. 1 is: the device comprises a flat top 1, a frustum 2, a first straight line section 3 and a second straight line section 4.
Detailed Description
The invention is further described below with reference to the figures and examples. It should be noted that the same technical contents between different subjects are omitted for the sake of brevity of the lines. The above abbreviations may be known to those skilled in the art after reading the text as a whole based on the context.
First, liner materials are mainly classified into metallic materials, multiphase composite materials and non-metallic materials. The research on metal materials mainly comprises a pure metal liner and an alloy liner, and the alloy liner combines metals or alloys with different properties according to the design requirements of the liner by considering that the pure metal liner has many problems. It is common to add a small amount of Zn (zinc) and Ni (nickel) in W-Cu (tungsten-copper) alloy to improve the compactness, strength and plasticity of the alloy, however, the tungsten-copper composite liner is very sensitive to explosive height (i.e. the height of placement) of explosive charge, and the depth of the broken nail is rapidly reduced under the explosive height, and the most ideal explosive height is 3 times of caliber size. This is also a common feature of the composite liner that the nail penetration depth can be increased by about 30% under small explosive conditions compared to pure copper liners, but the performance deteriorates rapidly under large explosive conditions, and ductile jet flow cannot be achieved. Furthermore, because the powder is an alloy and the flowability of the metal powder is poor, and random factors are many in the process of loading and pressing, the mass quantity (i.e. density) distribution of the mold cover is difficult to control, so that the performance is unstable and the penetration depth fluctuates greatly, which is a place to be improved.
Therefore, the invention develops a preparation method of the composite shaped charge liner, which comprises the following steps: weighing copper powder, tungsten powder, aluminum powder and nickel powder raw materials according to a proportion, and obtaining tungsten-copper mixed powder in a ball mill and an inert gas atmosphere;
step two, mixing the thermoplastic agent and the adsorbent to obtain the mixture with the density of rho 1 、ρ 2 、ρ 3 The auxiliary materials of (1);
step three, establishing an entity mould of the shaped charge liner, adopting a synchronous powder feeding method, feeding the tungsten-copper mixed powder obtained in the step one into the irradiation range of a laser beam through a powder feeder and a coaxial nozzle for melting, and spraying the tungsten-copper mixed powder on the entity mould to form a semi-finished product of the shaped charge liner;
step four, adopting a synchronous powder feeding method to obtain densities rho respectively in the step two 1 、ρ 2 、ρ 3 The auxiliary materials are fed into the irradiation range of laser beams through a powder feeder and a coaxial nozzle to be melted and respectively sprayed on the outer surfaces of a flat top, a frustum and a curved surface in the semi-finished product of the shaped charge liner to form cladding layers, and the precursor of the shaped charge liner is obtainedA body;
and step five, placing the shaped charge liner precursor obtained in the step four in a resistance furnace for recrystallization annealing treatment, and cooling the furnace.
Adopt above-mentioned technical scheme: by adding the coating layer containing the thermoplastic agent and the adsorbent, on one hand, the damage force during explosion is increased through the thermoplastic agent, and on the other hand, the cohesiveness during metal powder jet flow is increased through the thermoplastic agent; secondly, the metal powder is adsorbed by the adsorbent at the moment of explosion to increase the kinetic energy of the metal powder when it is jetted.
In a further embodiment, the molecular structure of the thermoplastic is as follows:
Figure BDA0002978498350000051
wherein R is 1 is-CH 2 -CH 3 ，R 2 is-CH 2 -CH 2 -CH 3 R is
Figure BDA0002978498350000052
Wherein n is an integer of 8 to 12.
The thermoplastic agent is synthesized by arranging the hard segment formed by OCN-R-NCO and-O-R2-O-in the chemical mechanism formula and the soft satin formed by HO-R1-OH according to the proportion, so that the rigidity of the thermoplastic agent is increased. At the same time, the strong reaction between the soft segment and the hard segment in the thermoplastic agent and the metal powder is formed into energetic jet flow.
In a further embodiment, the molecular structural formula of the adsorbent is as follows:
Figure BDA0002978498350000061
wherein m is an integer of 8 to 10.
The adsorbent is used for adsorbing the metal particles, so that when jet flow is formed, viscosity is generated among the metal particles, the adsorbent and the thermoplastic agent, and the impact force of the metal particles is enhanced.
In a further embodiment, the copper powder has a particle size of 1.2 to 1.8 μm and the tungsten powder has a particle size of 2.2 to 2.8 μm.
In a further embodiment, the solid mold is configured as follows:
the method comprises the following steps: flat tops, frustums, and curved surfaces; wherein the top of the frustum is in sealing connection with the flat top; the curved surface is connected with the bottom of the frustum; the connection part of the frustum and the curved surface is in smooth transition.
A composite liner is prepared by the preparation method, and the specific processes of the method are not described in detail.
The compound liner specifically comprises:
flat top;
the top of the frustum is connected with the flat top in a sealing manner;
the curved surface is connected with the bottom of the frustum; wherein, the connection part of the frustum and the curved surface is in smooth transition;
wherein the flat top, the frustum and the curved surface are formed by pressing composite metal powder;
further comprising: the cladding layer is coated on the outer surfaces of the flat top, the frustum and the curved surface in sequence from top to bottom, and the cladding layer is formed by pressing nonmetal powder.
Adopt above-mentioned technical scheme: the flat top is downward under the action of detonation to form an annular linear first jet flow, then the frustum region is converged to form a second jet flow again, and the curved surface region is converged to form a third jet flow again immediately after the second jet flow.
In a further embodiment, the density of the cladding layer at the outer surface of the plateau is defined as ρ 1 The density of the cladding layer at the outer surface of the frustum is rho 2 The density of the cladding layer at the outer surface of the curved surface is rho 3 And ρ is 1 ＜ρ 2 ＜ρ 3 。
Adopt above-mentioned technical scheme: namely, the energy in the formed first jet flow, the second jet flow and the third jet flow is sequentially increased, the first jet flow is further propelled, more metal in the second jet flow and the third jet flow is coated, and the impact force is larger.
In a further embodiment, the curved surface comprises:
Figure BDA0002978498350000072
the device comprises a plurality of first straight line segments and phi second straight line segments, wherein the adjacent first straight line segments are connected with the second straight line segments end to end, and the first straight line segments and the second straight line segments are in smooth transition.
The wave bands formed in the technical scheme are sequentially expanded from top to bottom, and have higher elongation. While the smooth transition is to accelerate the formation of the jet.
In a further embodiment, the length of the first straight line segment is defined as iota i ，
Figure BDA0002978498350000071
Define the length of the second straight line segment as ζ i And ζ of i ＝1.38ι i (ii) a i is the current first and second straight line segments.
By adopting the technical scheme: the inner diameter of the curved surface is sequentially increased from top to bottom, and the jet speed is not influenced.
In a further embodiment, the frustum thickness is defined as D1, the curved surface thickness is defined as D2, the cladding layer thickness is defined as D3, and D1: D2: D3=1 (0.7-0.8): 0.2-0.3).
Example 1
Step one, weighing raw materials of copper powder with the particle size of 1.2 microns, tungsten powder with the particle size of 2.8 microns, aluminum powder with the particle size of 1.5 microns and nickel powder with the particle size of 1.5 microns according to a ratio, and obtaining tungsten-copper mixed powder in a ball mill and an inert gas atmosphere; wherein the mass ratio of the copper powder to the tungsten powder to the aluminum powder to the nickel powder is 1.1. The ball milling time is 15 hours, and the rotating speed is 500r/min.
Step two, mixing the thermoplastic agent and the adsorbent to obtain the mixture with the density of rho 1 、ρ 2 、ρ 3 The auxiliary materials of (1); where ρ is 1 ＜ρ 2 ＜ρ 3 Is in order to formWhen the jet flow is in a step type, the later stage has larger thrust. The molecular structural formula of the thermoplastic agent is as follows:
Figure BDA0002978498350000081
wherein R is 1 is-CH 2 -CH 3 ，R 2 is-CH 2 -CH 2 -CH 3 R is
Figure BDA0002978498350000082
In the formula, n is 10.
The hard segment composed of OCN-R-NCO and-O-R2-O-in the chemical mechanism formula and the soft satin composed of HO-R1-OH are arranged in proportion to form the thermoplastic agent, so that the rigidity of the thermoplastic agent is increased. At the same time, the strong reaction between the soft segment and the hard segment in the thermoplastic agent and the metal powder is formed into energetic jet flow.
The molecular structural formula of the adsorbent is as follows:
Figure BDA0002978498350000083
in the formula, m is 9.
The adsorbent can adsorb the metal particles, so that when the jet flow is formed, viscosity is generated among the metal particles, the adsorbent and the thermoplastic agent, and the impact force of the metal particles is enhanced.
Step three, establishing an entity mould of the shaped charge liner, adopting a synchronous powder feeding method, feeding the tungsten-copper mixed powder obtained in the step one into the irradiation range of a laser beam through a powder feeder and a coaxial nozzle for melting, and spraying the tungsten-copper mixed powder on the entity mould to form a semi-finished product of the shaped charge liner;
step four, adopting a synchronous powder feeding method to obtain densities rho respectively in the step two 1 、ρ 2 、ρ 3 The auxiliary materials are fed into the irradiation range of laser beams through a powder feeder and a coaxial nozzle to be melted and respectively sprayed on the outer surfaces of a flat top, a frustum and a curved surface in the semi-finished product of the shaped charge liner to form cladding layers, and a shaped charge liner precursor is obtained;
and step five, placing the shaped charge liner precursor obtained in the step four in a resistance furnace for recrystallization annealing treatment, and cooling the furnace at the annealing temperature of 300 ℃ for 3 hours.
The parameters of the laser beam in the third step and the fourth step are as follows: the single-speed laser power is 2.5kW, the diameter of a focusing light spot is 4mm, and the movement speed of the numerical control workbench is 350mm/s.
Wherein, the structure of entity mould is as follows:
the method comprises the following steps: flat tops, frustums, and curved surfaces; wherein the top of the frustum is in sealing connection with the flat top; the curved surface is connected with the bottom of the frustum; the connection part of the frustum and the curved surface is in smooth transition. The structure of the composite liner constructed by using the above-described solid mold is specifically shown in fig. 1.
Example 2
Step one, weighing raw materials of copper powder with the particle size of 1.2 microns, tungsten powder with the particle size of 2.8 microns, aluminum powder with the particle size of 1.5 microns and nickel powder with the particle size of 1.5 microns according to a proportion, and obtaining tungsten-copper mixed powder in a ball mill and an inert gas atmosphere; wherein the mass ratio of the copper powder, the tungsten powder, the aluminum powder and the nickel powder is 1.1. The ball milling time is 15 hours, and the rotating speed is 500r/min.
Step two, establishing an entity mould of the shaped charge liner, adopting a synchronous powder feeding method, feeding the tungsten-copper mixed powder obtained in the step one into the irradiation range of a laser beam through a powder feeder and a coaxial nozzle for melting, and spraying the tungsten-copper mixed powder on the entity mould to form a semi-finished product of the shaped charge liner;
and step three, placing the semi-finished liner in the resistance furnace for recrystallization annealing treatment, wherein the annealing temperature is 300 ℃ and the annealing time is 3 hours.
Wherein, the structure of entity mould is as follows:
the method comprises the following steps: flat tops, frustums, and curved surfaces; wherein the top of the frustum is in sealing connection with the flat top; the curved surface is connected with the bottom of the frustum; the connection part of the frustum and the curved surface is in smooth transition. The structure of the composite liner constructed by using the above-described solid mold is specifically shown in fig. 1.
Example 3
Step one, weighing raw materials of copper powder with the particle size of 1.2 microns, tungsten powder with the particle size of 2.8 microns, aluminum powder with the particle size of 1.5 microns and nickel powder with the particle size of 1.5 microns according to a proportion, and obtaining tungsten-copper mixed powder in a ball mill and an inert gas atmosphere; wherein the mass ratio of the copper powder, the tungsten powder, the aluminum powder and the nickel powder is 1.1. The ball milling time is 15 hours, and the rotating speed is 500r/min.
Step two, mixing the thermoplastic agent and the adsorbent to obtain the mixture with the density of rho 1 、ρ 2 、ρ 3 The auxiliary materials of (1); where ρ is 1 ＜ρ 2 ＜ρ 3 The aim is to form a step-shaped jet flow with larger thrust at the later stage. The molecular structural formula of the thermoplastic agent is as follows:
Figure BDA0002978498350000101
wherein R is 1 is-CH 2 -CH 3 ，R 2 is-CH 2 -CH 2 -CH 3 R is
Figure BDA0002978498350000102
In the formula, n is 10.
The rigid section composed of OCN-R-NCO and-O-R2-O-in the chemical mechanism formula and the soft section composed of HO-R1-OH are arranged in proportion to form the thermoplastic agent, so that the rigidity of the thermoplastic agent is increased. At the same time, strong reaction is generated between the soft segment and the hard segment in the thermoplastic agent and the metal powder to form energetic jet flow.
The molecular structural formula of the adsorbent is as follows:
Figure BDA0002978498350000103
in the formula, m is 9.
The adsorbent can adsorb the metal particles, so that when jet flow is formed, viscosity is generated among the metal particles, the adsorbent and the thermoplastic agent, and the impact force of the metal particles is enhanced.
Step three, establishing an entity mould of the shaped charge liner, adopting a synchronous powder feeding method, feeding the tungsten-copper mixed powder obtained in the step one into the irradiation range of a laser beam through a powder feeder and a coaxial nozzle for melting, and spraying the tungsten-copper mixed powder on the entity mould to form a semi-finished product of the shaped charge liner;
step four, adopting a synchronous powder feeding method to obtain densities rho respectively in the step two 1 、ρ 2 、ρ 3 The auxiliary materials are fed into the irradiation range of laser beams through a powder feeder and a coaxial nozzle to be melted and respectively sprayed on the outer surfaces of a flat top, a frustum and a curved surface in the semi-finished product of the shaped charge liner to form cladding layers, and a shaped charge liner precursor is obtained;
and step five, placing the liner precursor obtained in the step four in a resistance furnace for recrystallization annealing treatment, and cooling the furnace at the annealing temperature of 300 ℃ for 3 hours.
The parameters of the laser beam in the third step and the fourth step are as follows: the single-speed laser power is 2.5kW, the diameter of a focusing light spot is 4mm, and the movement speed of the numerical control workbench is 350mm/s.
The solid mold has a cone structure, and the outer surface of the cone is a smooth plane, as shown in fig. 2.
Detection example 1
The liners prepared in examples 1 to 3 were subjected to the test analysis of the destruction property: fig. 3 is a graph showing the destruction of the respective liners at the same explosive height, and the liner prepared in example 1 showed the greatest destruction as shown in fig. 3. The initial stage of jet formation in example 1 due to the presence of the thermoplastic and the adsorbent has a radial velocity greater than that of the metal jet.
Example 4
The present embodiment is different from embodiment 1 in that: step two, mixing the thermoplastic agent and the adsorbent to obtain the mixture with the density of rho 1 、ρ 2 、ρ 3 The auxiliary material of (1); wherein ρ is satisfied 1 ＞ρ 2 ＞ρ 3 . The other steps were the same as in example 1.
Example 5
The present embodiment is different from embodiment 1 in that: step two, mixing the thermoplastic agent and the adsorbent to obtain the mixture with the density of rho 1 、ρ 2 、ρ 3 The auxiliary material of (1); wherein ρ is not satisfied 1 ＜ρ 2 ＞ρ 3 . The other steps were the same as in example 1.
Detection example 2
The liners prepared in examples 1, 4 to 5 were tested for their destruction performance: fig. 4 is a graph showing the destruction of the separately prepared liners into the aluminum target at the same burst height, as shown in fig. 4, which is the greatest in the case of liner prepared in example 1. In example 1, the thermoplastic agent and the adsorbent have a radial velocity greater than that of the metal jet at the initial stage of jet formation, and the damage is increased in consideration of the stepped shape of the liner combined with the density increase of the cladding layer, thereby avoiding the attenuation of the radial velocity to different degrees.
Example 6
A composite liner made according to example 1, comprising: the flat top 1 is connected with a frustum 2 in a sealing mode, and the bottom of the frustum 2 is connected with a curved surface in a sealing mode. And the connection part of the frustum and the curved surface is in smooth transition. In order to enable the mold cover to have high density, high strength, strong plasticity and strong nail-breaking force, the flat top, the frustum and the curved surface are pressed by composite metal powder, and auxiliary materials are coated on the outer surfaces of the flat top, the frustum and the curved surface and are prepared through the second step and the fourth step in the embodiment 1.
The auxiliary materials comprise: the thermoplastic agent and the adsorbent, wherein the molecular structural formula of the thermoplastic agent is as follows:
Figure BDA0002978498350000121
wherein R is 1 is-CH 2 -CH 3 ，R 2 is-CH 2 -CH 2 -CH 3 R is
Figure BDA0002978498350000122
Wherein n is an integer of 10.
The molecular structural formula of the adsorbent is as follows:
Figure BDA0002978498350000123
wherein m is an integer of 9.
Wherein the curved surface comprises: the four straight line segments comprise four first straight line segments 3 and four second straight line segments 4, adjacent first straight line segments are connected with the second straight line segments end to end, and smooth transition is formed between the first straight line segments and the second straight line segments.
Defining the length of the first straight line segment as iota i ，
Figure BDA0002978498350000124
Define the length of the second straight line segment as ζ i And ζ is i ＝1.38ι i (ii) a i is the current first and second straight line segments.
In this example, iota 1 =5mm, then iota 2 ＝7.5mm，ι 3 ＝8.75mm，ι 4 ＝10mm。
ζ 1 ＝6.9mm，ζ 2 ＝10.35mm，ζ 3 ＝12.1mm，ζ 4 ＝13.8mm。
Defining the thickness of the frustum as D1, the thickness of the curved surface as D2, and the thickness of the cladding layer as D3, in this embodiment, D1=3mm, then D2=2.1mm, and D3=0.6mm.
Example 7
The present embodiment is different from embodiment 6 in that: d1=3mm, then D2=2.4mm, and D3=0.9mm.
The rest were the same as in example 6.
Example 8
This embodiment is different from embodiment 6 in that: d1=3mm, then D2=1.8mm, and D3=0.2mm.
The rest were the same as in example 6.
Example 9
This embodiment is different from embodiment 6 in that: d1=3mm, then D2=2.7mm, D3=1.2mm.
The rest of the procedure was the same as in example 6.
Detection example 3
The liners prepared in examples 6 to 9 were tested for their destruction performance: fig. 5 is a graph showing the destruction of the liner penetrating the aluminum target at the same explosive height, as shown in fig. 5, with the liners of examples 6 and 7 having the greatest destruction. From fig. 5, the thickness of the liner has a great influence on penetration depth, namely when the thickness satisfies D1: D2: D3=1 (0.7-0.8): (0.2-0.3), the reaming capability of the jet is strongest, otherwise, the perforation capability is reduced.
The external surface of the existing liner is coated with thermoplastic agent and adsorbent. When the shaped charge is detonated and generates high temperature during use, high-speed jet flow is formed at the flat top of the shaped charge cover to move forwards, and because the cladding layer is coated on the outer surface and is in direct contact with the high temperature, strong reaction is generated between the soft section and the hard section in the thermoplastic agent and the metal powder to form energetic jet flow under the action of the high temperature, the viscosity of the thermoplastic agent is enhanced, and the nail-breaking power of the jet flow is increased. Meanwhile, the adsorbent has stronger chelating force, so that the metal particles around the adsorbent can be coated at the moment of explosion, the metal particles move forwards along with the heat-following agent, and the impact force of the metal particles is further increased.
The liner is composed of a frustum and a curved surface, and is used for forming high-speed jet flow at the moment of explosion, and the wave structure positioned on the curved surface is used for increasing the coating area of a cladding layer, increasing the heating area of the liner and accelerating the formation of jet flow.

Claims (3)

1. The preparation method of the composite shaped charge liner is characterized by comprising the following steps:
weighing copper powder, tungsten powder, aluminum powder and nickel powder raw materials according to a proportion, and obtaining tungsten-copper mixed powder in a ball mill under the protection of inert gas;
step two, mixing the thermoplastic agent and the adsorbent to obtain the mixture with the density of
Figure 492764DEST_PATH_IMAGE001
、
Figure 347587DEST_PATH_IMAGE002
、
Figure 268270DEST_PATH_IMAGE003
The auxiliary materials of (1);
step three, establishing an entity mould of the shaped charge liner, adopting a synchronous powder feeding method, feeding the tungsten-copper mixed powder obtained in the step one into the irradiation range of a laser beam through a powder feeder and a coaxial nozzle for melting, and spraying the tungsten-copper mixed powder on the entity mould to form a semi-finished product of the shaped charge liner; the liner comprises: the device comprises a flat top, a frustum with the top connected with the flat top in a sealing way, and a curved surface connected to the bottom of the frustum; wherein the connection part of the frustum and the curved surface is in smooth transition;
step four, adopting a synchronous powder feeding method to obtain the density of
Figure 601162DEST_PATH_IMAGE001
、
Figure 618797DEST_PATH_IMAGE002
、
Figure 844854DEST_PATH_IMAGE003
The auxiliary material is fed into the irradiation range of the laser beam through a powder feeder and a coaxial nozzle for melting, and the density of the auxiliary material is
Figure 252833DEST_PATH_IMAGE001
The auxiliary material is sprayed on the outer surface of the flat top and has the density of
Figure 858258DEST_PATH_IMAGE002
The auxiliary material is sprayed on the outer surface of the frustum and the density is
Figure 199240DEST_PATH_IMAGE003
The auxiliary material is sprayed on the outer surface of the curved surface; obtaining a shaped charge liner precursor;
fifthly, placing the liner precursor obtained in the fourth step in a resistance furnace for recrystallization annealing treatment, and cooling the furnace;
wherein the molecular structural formula of the thermoplastic agent is as follows:
Figure 333550DEST_PATH_IMAGE004
wherein R is 1 is-CH 2 -CH 3 ，R 2 is-CH 2 -CH 2 -CH 3 R is
Figure 294071DEST_PATH_IMAGE005
Wherein n is an integer of 8 to 12;
the molecular structural formula of the adsorbent is as follows:
Figure 968766DEST_PATH_IMAGE006
in the formula, m is an integer of 8 to 10.
2. The method of claim 1, wherein the first and second liner segments are bonded together,
Figure 101938DEST_PATH_IMAGE007
。
3. a composite liner prepared by the method of any one of claims 1-2.
CN202110281234.8A 2021-03-16 2021-03-16 Auxiliary material, composite shaped charge liner containing auxiliary material and preparation method of composite shaped charge liner Active CN113210607B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202110281234.8A CN113210607B (en) 2021-03-16 2021-03-16 Auxiliary material, composite shaped charge liner containing auxiliary material and preparation method of composite shaped charge liner

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202110281234.8A CN113210607B (en) 2021-03-16 2021-03-16 Auxiliary material, composite shaped charge liner containing auxiliary material and preparation method of composite shaped charge liner

Publications (2)

Publication Number Publication Date
CN113210607A CN113210607A (en) 2021-08-06
CN113210607B true CN113210607B (en) 2022-12-02

Family

ID=77083704

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202110281234.8A Active CN113210607B (en) 2021-03-16 2021-03-16 Auxiliary material, composite shaped charge liner containing auxiliary material and preparation method of composite shaped charge liner

Country Status (1)

Country Link
CN (1) CN113210607B (en)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4766813A (en) * 1986-12-29 1988-08-30 Olin Corporation Metal shaped charge liner with isotropic coating
CN104457433A (en) * 2014-10-24 2015-03-25 中国船舶重工集团公司第七〇五研究所 Combined cartridge-shaped cover
CN104911585A (en) * 2015-06-29 2015-09-16 北京理工大学 Preparation method of composite liner
CN105014072A (en) * 2015-07-16 2015-11-04 南京理工大学 Preparation method for W-Cu shaped charge liner
CN107236949A (en) * 2016-12-26 2017-10-10 北京理工大学 A kind of near-net-shape preparation method of Al bases active metal cavity liner containing energy
CN111075405A (en) * 2020-01-15 2020-04-28 北方斯伦贝谢油田技术（西安）有限公司 Energetic shaped charge liner and energetic material for double-effect perforating bullet

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7360488B2 (en) * 2004-04-30 2008-04-22 Aerojet - General Corporation Single phase tungsten alloy
US8166882B2 (en) * 2009-06-23 2012-05-01 Schlumberger Technology Corporation Shaped charge liner with varying thickness

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4766813A (en) * 1986-12-29 1988-08-30 Olin Corporation Metal shaped charge liner with isotropic coating
CN104457433A (en) * 2014-10-24 2015-03-25 中国船舶重工集团公司第七〇五研究所 Combined cartridge-shaped cover
CN104911585A (en) * 2015-06-29 2015-09-16 北京理工大学 Preparation method of composite liner
CN105014072A (en) * 2015-07-16 2015-11-04 南京理工大学 Preparation method for W-Cu shaped charge liner
CN107236949A (en) * 2016-12-26 2017-10-10 北京理工大学 A kind of near-net-shape preparation method of Al bases active metal cavity liner containing energy
CN111075405A (en) * 2020-01-15 2020-04-28 北方斯伦贝谢油田技术（西安）有限公司 Energetic shaped charge liner and energetic material for double-effect perforating bullet

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
复合药型罩EFP的形成及数值模拟;袁建飞等;《火***学报》;20100228(第01期);第83-86、90页 *
复合药型罩的研究进展;李国宾;《兵器材料科学与工程》;19950130(第01期);第63-68页 *
激光熔覆制备TC4基复合药型罩材料的力学性能;闫春洋等;《航空材料学报》;20171231(第03期);第68-72页 *

Also Published As

Publication number Publication date
CN113210607A (en) 2021-08-06

Similar Documents

Publication Publication Date Title
US7921778B2 (en) Single phase tungsten alloy for shaped charge liner
US20050235862A1 (en) Warhead with integral, direct-manufactured features
US7658148B2 (en) Reactive shaped charges comprising thermal sprayed reactive components
US7886668B2 (en) Metal matrix composite energetic structures
US20070240603A1 (en) Porous Coated Member and Manufacturing Method Thereof Using Cold Spray
US7955451B2 (en) Energetic thin-film based reactive fragmentation weapons
JPS62138699A (en) Molded explosive and liner thereof
US20030015265A1 (en) Energy dense explosives
US8616130B2 (en) Liners for warheads and warheads having improved liners
CN113210607B (en) Auxiliary material, composite shaped charge liner containing auxiliary material and preparation method of composite shaped charge liner
US4638738A (en) Fin stabilized subcaliber shell of large length to diameter ratio
CN113073215A (en) Preparation method and application of high-entropy alloy for passive heavy bulletproof armor
CN114147233B (en) Missile warhead shell and additive manufacturing method thereof
Tepper Nanosize powders produced by electro-explosion of wire and their potential applications
US8486541B2 (en) Co-sintered multi-system tungsten alloy composite
US9573858B1 (en) Energetic materials using amorphous metals and metal alloys
US10240906B2 (en) Penetrator incorporating a core enclosed in a ductile sheath and manufacturing process for such a penetrator
US8573128B2 (en) Multi component reactive metal penetrators, and their method of manufacture
Zou et al. Effect of magnesium-rich phase on oxidation properties of atomized aluminum–magnesium powders
US20240085160A1 (en) Cold spray additive manufacturing of fragmentation bombs and warheads
Nable et al. Novel energetic composite materials
Lee et al. Reactivity enhancement and fabrication of Al-MoO3 thermite coating using ball milling for kinetic spraying
CN113503775B (en) Shaped charge structure capable of forming active and metal dual-projectile follow-up
CN115055686B (en) Tungsten particle reinforced high-entropy alloy warhead and additive manufacturing method thereof
KR102613642B1 (en) Microstructural design of reactive material structures to maximize the blast effect in explosive detonating environment

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
GR01 Patent grant
GR01 Patent grant
TR01 Transfer of patent right
TR01 Transfer of patent right

Effective date of registration: 20240319

Address after: 230000 floor 1, building 2, phase I, e-commerce Park, Jinggang Road, Shushan Economic Development Zone, Hefei City, Anhui Province

Patentee after: Dragon totem Technology (Hefei) Co.,Ltd.

Country or region after: Zhong Guo

Address before: No. 532-2, Zhongshan East Road, Qinhuai District, Nanjing City, Jiangsu Province, 210005

Patentee before: Nanjing Vocational University of Industry Technology

Country or region before: Zhong Guo