A light-weight high-strength composite material propellant and a preparation method thereof

Abstract

The application discloses a light high-strength composite material propelling base and a preparation method thereof, and belongs to the technical field of propelling base preparation.The structure of the propelling base adopts an integrated forming process, the split structure comprises a sandwich structure in which radial modules and axial modules are arranged in a staggered mode, the radial modules and the axial modules are combined by being die-pressed by pre-impregnated materials with different layer angles, thicknesses and sizes and a sandwich foaming plate, the radial modules can make the tooth part obtain high mechanical strength, the axial modules at different positions can obtain circumferential supporting action to prevent the propelling base from being delaminated, the strength of the propelling base is ensured, and the stability of the product is ensured as well.In the preparation process, the product is split and layering is designed, foaming materials are adopted on the premise that the structural strength meets the use requirement, the weight reduction effect is remarkable, and the pressure generated by the foaming materials can also increase the density of the product.

Description

Technical Field

[0001] This invention belongs to the field of sabot preparation technology, specifically relating to a lightweight, high-strength composite material sabot and its preparation method. Background Technology

[0002] During the firing of sub-caliber high-velocity armor-piercing projectiles, multiple factors influence the lethality and armor-piercing capability of these kinetic energy projectiles, including the projectile's impact kinetic energy, reducing its negative mass, the material and manufacturing process of the core, effective range, and probability of hit. Based on previous technologies, there is limited potential to be explored by improving projectile materials and dimensions, using high chamber pressure, and increasing propellant mass; these methods are also difficult to implement. A more realistic approach is to focus on structural design and sabot materials.

[0003] As a negative mass, the sabot is an important component that can simultaneously improve the power, accuracy, and range of sub-caliber armor-piercing projectiles, thereby enabling them to achieve higher initial velocity and possess a certain degree of lethality and armor-piercing power. It is currently an important way to improve armor-piercing power.

[0004] First- and second-generation sabots from abroad were made of alloy steel and aluminum alloy, respectively, but the quality of these metal sabots had reached its limit. With the rapid innovation of new materials and technologies, composite materials have become the preferred material for sabot manufacturing due to their advantages such as low density, high mechanical strength, and convenient molding processes. Foreign countries have successively developed multiple generations of sabot products and applied composite material sabots extensively. However, existing composite material sabots currently have poor strength, reliability, and stability, and their application range is very limited. Summary of the Invention

[0005] In order to overcome the shortcomings of the prior art, the present invention aims to provide a lightweight, high-strength composite material sabot and its preparation method, so as to solve the technical problems of poor strength, reliability and stability of existing sabots.

[0006] To achieve the above objectives, the present invention employs the following technical solution:

[0007] This invention discloses a lightweight, high-strength composite material ejector, comprising a sandwich structure in which radial and axial modules are interspersed, and the outer surface of the sandwich structure is provided with a skin;

[0008] The radial module consists of several radial single-block modules interspersed with radial inserts and radial sandwich foam boards; the axial module consists of several axial single-block modules interspersed with axial inserts and axial sandwich foam boards.

[0009] This invention also discloses a method for preparing the above-mentioned lightweight high-strength composite material sabot, comprising the following steps:

[0010] S1: First, based on the structure, dimensions, and operating conditions of the sabot product, determine the quantity, dimensions, and placement of radial modules, radial sandwich foam boards, radial inserts, axial modules, axial inserts, and axial sandwich foam boards at different locations; and the dimensions and quantity of the skin at different locations.

[0011] S2: Using prepreg A as the raw material for making radial single-piece modules, calculate the number of layers required based on the thickness of the radial single-piece module and the thickness of a single layer of prepreg A. Then, lay the layers according to the set layup angle until the required number of layers are reached to form a radial single-piece module. Subsequently, use prepreg A to wrap a foam board of a predetermined size to obtain the number and size of radial sandwich foam boards set in S1. Use prepreg A to make radial inserts of the number and size set in S1. Then, place the radial inserts and radial sandwich foam boards in the positions set in S1 for the radial single-piece modules to form a radial module. Repeat the above steps until the number of radial modules set in S1 is obtained. Lay the radial modules in the order set in S1.

[0012] S3: Using prepreg B as the raw material for making axial single-piece modules, calculate the number of layers based on the thickness of the axial modules placed at different positions as set in S1 and the thickness of a single layer of prepreg B. Cut to the required shape and number of layers until the size set in S1 is reached, and obtain the axial single-piece module. Wrap the foam board of the predetermined size with prepreg B to obtain the number and size of the axial sandwich foam boards set in S1. Use prepreg B to make axial inserts of the number and size set in S1. Then place the axial inserts and axial sandwich foam boards at the positions set in S1 for the axial single-piece modules to form an axial module. Repeat the above steps until the number of axial modules set in S1 is obtained. Lay the axial modules in sequence according to the parting positions set in S1 to form the sandwich structure of the spring support blank. Place the skin on the sandwich structure and perform mold closing and pre-pressing to form the preformed part of the spring support.

[0013] Furthermore, the raw material for the skin is prepreg C; the prepreg C is continuous carbon fiber prepreg, continuous glass fiber prepreg cloth, or chopped fiber prepreg.

[0014] Furthermore, the preparation process of the skin is as follows:

[0015] Calculate the number of layers based on the thickness at different locations and the thickness of a single layer of prepreg C, and cut it to the required shape and number of layers until it reaches the size and quantity set in S1.

[0016] Furthermore, the prepreg A and prepreg B are carbon fiber prepregs or glass fiber prepregs; the fiber is carbon fiber cloth or unidirectional carbon fiber or glass fiber cloth.

[0017] Furthermore, the material of the foamed board is a foamed core material or a foamed adhesive film; the foaming ratio of the foamed board is 1 to 5 times.

[0018] Furthermore, the number of radial sandwich foam boards is one less than the number of radial modules; the number of axial sandwich foam boards is one less than the number of axial modules.

[0019] Furthermore, the number of radial inserts is one less than the number of radial modules; the number of axial inserts is one less than the number of axial modules; the size of the radial inserts and axial inserts is determined by the number and thickness of the radial and axial single-piece modules, as well as the total number of layers of the radial and axial modules.

[0020] Furthermore, the number of radial modules is determined by dividing the thickness of the preform by the thickness of the radial modules; the number of axial modules is determined by dividing the thickness of the preform by the thickness of the axial modules.

[0021] Furthermore, the number of layers of the axial modules at different positions = the thickness of the axial module ÷ the thickness of the single layer of fiber material B; if not evenly divided, then the number of layers of the axial modules at different positions = the integer obtained after division + 1;

[0022] The number of layers of the skin = thickness at different locations ÷ thickness of a single layer of prepreg C.

[0023] Compared with the prior art, the present invention has the following beneficial effects:

[0024] This invention discloses a lightweight, high-strength composite material sabot. The sabot's structure is manufactured using an integral molding process. The parting structure includes a sandwich structure with radial and axial modules interlocked. The radial and axial modules are formed by interlocking and molding prepregs with different layup angles, thicknesses, and sizes, and foamed sandwich panels. The radial modules enable the teeth to achieve high mechanical strength, while the axial modules at different locations provide circumferential support to prevent delamination of the sabot, thus ensuring both the strength and stability of the product. The composite material sabot is characterized by its light weight and high mechanical strength.

[0025] This invention also discloses a method for preparing the aforementioned lightweight high-strength composite material bullet. By designing the product type and layup, foaming materials are used to significantly reduce weight while ensuring that the structural strength meets the requirements for use. The pressure generated by the foaming material itself also increases the density of the product. The preparation process adopts an integrated molding method, which has a simple mold structure, good consistency of external dimensions, high process feasibility, and strong practicality. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the parting and blanking structure of the lightweight, high-strength composite material sabot of the present invention;

[0027] Figure 2 This is a schematic diagram of the cross-sectional structure of a single radial module of the present invention cut along the axial direction;

[0028] Figure 3 This is a schematic diagram of the cross-sectional structure of multiple radial modules of the present invention cut along the axial direction;

[0029] Figure 4 This is a schematic diagram of the sandwich foam board in this invention;

[0030] Figure 5 Schematic diagrams of different radial and axial inserts;

[0031] Figure 6 This is a schematic diagram of the cross-sectional structure of the lightweight, high-strength composite material sabot of the present invention, cut along its transverse direction.

[0032] Wherein: 1-Radial module; 2-Axial module; 3-Skin; 4-Foamed board; 5-Prepreg. Detailed Implementation

[0033] To enable those skilled in the art to understand the features and effects of the present invention, the terms and expressions used in the specification and claims are explained and defined in general below. Unless otherwise specified, all technical and scientific terms used herein have the ordinary meaning understood by those skilled in the art regarding the present invention, and in case of conflict, the definitions in this specification shall prevail.

[0034] The theories or mechanisms described and disclosed herein, whether right or wrong, should not in any way limit the scope of the invention, that is, the contents of the invention can be implemented without being limited by any particular theory or mechanism.

[0035] In this document, all features defined by numerical ranges or percentage ranges, such as numerical values, quantities, contents, and concentrations, are for the sake of brevity and convenience only. Accordingly, descriptions of numerical ranges or percentage ranges should be considered as covering and specifically disclosing all possible sub-ranges and individual numerical values ​​(including integers and fractions) within those ranges.

[0036] In this article, unless otherwise specified, “contains,” “includes,” “containing,” “has,” or similar terms cover the meanings of “composed of” and “mainly composed of,” for example, “A contains a” covers the meanings of “A contains a and others” and “A contains only a.”

[0037] For the sake of brevity, not all possible combinations of the technical features in each implementation scheme or embodiment are described herein. Therefore, as long as there is no contradiction in the combination of these technical features, the technical features in each implementation scheme or embodiment can be combined arbitrarily, and all possible combinations should be considered within the scope of this specification.

[0038] This invention discloses a lightweight, high-strength composite material sabot, wherein the sabot adopts a sandwich structure of radial module 1 + axial module 2 + skin 3, as shown below. Figure 1 As shown, the strength of the sabot teeth is mainly borne by the radial fibers in the radial module 1, while the safety and stability of the sabot are mainly borne by the axial fiber cloth in the axial module 2, which ensures both the strength of the sabot and the stability of the product.

[0039] The preparation process of the above-mentioned lightweight high-strength composite material sabot includes the following steps:

[0040] 1): First, based on the structure, dimensions and operating conditions of the sabot product, the product structure is designed for material cutting and shaping, and the following parameters are set: number of radial modules 1, thickness of radial modules 1, number and size of radial inserts, size and number of radial sandwich foam boards, placement of radial sandwich foam boards, number and size of different axial modules 2, size of axial sandwich foam boards, size and number of axial sandwich foam boards, and size and number of skin 3.

[0041] 2): Use prepreg A to make radial single-piece modules. Calculate the number of layup layers based on the thickness of the radial single-piece module and the thickness of a single layer of prepreg A. Then lay up the layers according to the set layup angle until the required number of layers is reached.

[0042] 3): Wrap the pre-prep material A around the foam board 4 of the predetermined size until it reaches the quantity set in S1, such as... Figure 4 As shown;

[0043] 4) Using prepreg A to fabricate inserts, radial inserts are obtained, such as... Figure 5 As shown, until it reaches the quantity and size set in step 1);

[0044] 5) Place the sandwich foam board and inserts from steps 3) and 4) at the positions set in step 1) to form a complete radial module 1, such as... Figure 2 As shown;

[0045] 6) Repeat steps 2) to 5) until the quantity set in step 1) is reached;

[0046] 7) Lay out the radial modules 1 obtained in step 6) in the order set in step 1), such as... Figure 3 As shown;

[0047] 8) Use prepreg B to make modules in different axial directions. Calculate the number of layers based on the thickness of the modules in different positions and the thickness of a single layer of prepreg B. Cut them to the required shape and number of layers until they reach the number of layers and dimensions set in step 1).

[0048] 9) The prepreg B is used to wrap the foam board 4 of a predetermined size to obtain an axially sandwiched foam board, the shape of which is as follows: Figure 4 As shown, until it reaches the size set in step 1);

[0049] 10) Place the axial module 2 and the axial sandwich foam board from steps 8) and 9) in the positions set in step 1) to form a complete axial module;

[0050] 11) Repeat steps 8) to 10) to obtain multiple axial modules 2 of different sizes until the number set in step 1) is reached;

[0051] 12) Place the modules with different axial directions obtained in step 11) into the corresponding parting positions in step 7) to form spring support blanks;

[0052] 13) Use prepreg C to make skin 3. Calculate the number of layers based on the thickness at different locations and the thickness of a single layer of prepreg C, and cut to the required shape and number of layers until it reaches the number of layers and dimensions set in step 1). Wrap the prepreg C with the foam board 4 of the predetermined size until it reaches the quantity set in step 1). Place the sandwich foam board in the position set in step 1) to form a complete skin 3; its cross-sectional structure diagram is shown below. Figure 6 As shown;

[0053] 14) Place the skin 3 obtained in step 13) on the blank obtained in step 12), and perform mold closing and pre-pressing to form a preformed part of the spring support;

[0054] Preferably, prepregs A and B are carbon fiber prepregs or glass fiber prepregs, and the fibers are carbon fiber cloth or unidirectional carbon fiber and glass fiber cloth; prepreg C is a continuous carbon fiber prepreg, a continuous glass fiber prepreg cloth, or a chopped fiber prepreg, and the fibers are carbon fiber cloth, unidirectional carbon fiber, chopped fiber, and glass fiber cloth. Prepregs A, B, and C are collectively referred to as prepreg 4.

[0055] Preferably, the foaming material used in the sandwich foam board is a foam core material or a foam film; the foaming ratio is 1 to 5 times.

[0056] Preferably, the number of sandwich foam boards = the number of modules - 1.

[0057] Preferably, the number of plug-ins = the number of modules - 1; the plug-in size is designed based on the number of layers and thickness of a single module in step 2), and the total number of layers of multiple modules in step 7), which determines the size difference between the plug-in and the module.

[0058] Preferably, the number of modules = product thickness ÷ module thickness.

[0059] Preferably, the number of axial module 2 layers at different positions = the thickness of axial module 2 / the thickness of a single layer of fiber material B. If the division is not exact, then the number of layup layers = the integer obtained after the division + 1.

[0060] Preferably, in step 13), the number of layers at different locations = the thickness at different locations ÷ the thickness of a single layer of prepreg C.

[0061] The present invention will be further illustrated below with reference to specific embodiments. It should be understood that these embodiments are for illustrative purposes only and are not intended to limit the scope of the invention. Furthermore, it should be understood that after reading the teachings of this invention, those skilled in the art can make various alterations or modifications to the invention, and these equivalent forms also fall within the scope defined by the appended claims.

[0062] The following examples use instruments and equipment conventional in the art. Experimental methods in the following examples, unless otherwise specified, are generally performed under conventional conditions or as recommended by the manufacturer. All raw materials used in the following examples are conventional commercially available products with specifications conventional in the art. In this specification and the following examples, unless otherwise specified, "%" refers to weight percentage, "parts" refers to parts by weight, and "ratio" refers to weight proportion.

[0063] Example 1

[0064] The manufacturing method of this lightweight composite material sabot includes the following steps:

[0065] 1) Based on the structure, dimensions, and operating conditions of the sabot product, the product structure was designed with material cutting and shaping, and the following parameters were determined: 10 radial modules 1; 1.4mm thickness of radial module 1; 9 radial inserts; 20-40 segments required for each insert; 9 radial core foam boards; each radial core foam board is placed on the top layer of each insert; 3 axial modules 2; each axial core foam board is placed on the side of each insert away from the upper skin 3; the thickness of skin 3 is 1.2mm; the laying sequence of radial modules 1 is: 1 radial module + 1 radial insert + ... + 1 radial insert + 1 radial module; the product layering sequence is: radial module 1 + 3 axial modules 2 + skin 3.

[0066] 2) Use 0.2mm thick carbon fiber prepreg to make radial monoblock modules. Based on the thickness of the radial monoblock module and the thickness of the single layer of carbon fiber prepreg, the number of layup layers is calculated to be 7. Then lay up the layers according to the settings 02 / 45° / 90° / 45° / 02 until the required number of layers is reached.

[0067] 3) Wrap a pre-sized foamed board 4 with 0.2mm thick carbon fiber prepreg, in quantity 1, with a foaming ratio of 1-3 times;

[0068] 4) The inserts are made of 0.2mm thick carbon fiber prepreg. Each insert requires 21 segments, and the size of each segment is different.

[0069] 5) Place the sandwich foam board and inserts from steps 3) and 4) at the parting position in step 1) to form a complete radial module 1;

[0070] 6) Repeat steps 2-5 to obtain 10 radial modules 1;

[0071] 7) Lay out the 10 radial modules 1 obtained in step 6) in the order set in step 1);

[0072] 8) Use 0.3mm thick carbon fiber prepreg to make modules in different axial directions. Calculate the number of lay-up layers based on the thickness of the modules in different positions and the thickness of the carbon fiber prepreg. Cut to the required shape and number of layers until it reaches the number of layers and size set in step 1).

[0073] 9) Wrap one foam board 4 of a predetermined size with 0.3mm thick carbon fiber prepreg, with a foaming ratio of 1-3 times; to obtain an axially sandwiched foam board.

[0074] 10) Place the axial sandwich foam board from step 9) on the topmost position in step 8) to form a complete axial module 2;

[0075] 11) Repeat steps 8-10 to obtain 3 axial modules 2 of different sizes;

[0076] 12) Place the three modules with different axial directions obtained in step 11) into the corresponding parting positions in step 7) to form a spring support blank;

[0077] 13) Load the spring support blank obtained in step 12) into the lower mold, protect the upper surface of the spring support blank, close the mold and place it on the press, adjust the pressure of the press to 10MPa, raise the temperature to 70℃, pre-press for 2-5 minutes and then open the mold, trim the overflow material at the edge of the mold to obtain the preform blank.

[0078] 14) Use 0.3mm thick chopped prepreg to make the skin, design the number of layers to be 2, cut out the required shape and number of layers and lay them flat;

[0079] 15) Wrap the foam board of the predetermined size with 0.3mm thick chopped prepreg;

[0080] 16) Place the foamed sandwich panel from step 15) in the middle of step 14) to form a complete skin.

[0081] 17) Place the skin 3 obtained in step 16) on the preform blank obtained in step 13), and perform mold closing and pre-pressing to form a preform of the spring support; after closing the upper and lower molds, place them on the press, adjust the pressure to 10MPa, raise the temperature to 70℃, pre-press for 2-5 minutes, open the mold, and trim the overflowing material at the edge of the mold.

[0082] 18) Place the mold after mold closing on the molding machine, adjust the pressure to 6MPa, raise the temperature to 90℃, hold the pressure for 1 hour, raise the temperature to 135℃, hold the pressure for 30 minutes, and then vent the air 5 times under the same pressure. Raise the temperature to 150℃, adjust the pressure to 12MPa, hold the pressure for 3 hours, and then allow it to cool naturally before heating and curing.

[0083] The above content is only for illustrating the technical concept of the present invention and should not be construed as limiting the scope of protection of the present invention. Any modifications made to the technical solution based on the technical concept proposed in this invention shall fall within the scope of protection of the claims of this invention.

Claims

1. A method of making a lightweight high strength composite material prop band, characterized by, It comprises the following steps: S1: firstly, according to the structure, size and working condition requirements of the ejector product, the number, size and placement position of the radial module (1), radial sandwich foam board, radial insert, axial module (2) at different positions, axial insert and axial sandwich foam board are determined; the size and number of the skin (3) at different positions; S2: using prepreg A as the raw material for making radial single block module, calculating the number of layers needed according to the thickness of radial single block module and the thickness of single layer prepreg A, then laying up according to the setting layer angle, laying up to the required number of layers, forming a radial single block module; then using prepreg A to wrap the foam board (4) of a predetermined size, obtaining the number and size of the radial sandwich foam board set in S1; using prepreg A to make the number and size of the radial insert set in S1; then placing the radial insert and radial sandwich foam board at the position of the radial single block module set in S1 to form a radial module; repeat the above steps until the number of radial modules (1) set in S1 is obtained; lay the radial modules (1) according to the sequence set in S1; S3: using prepreg B as the raw material for making axial single block module, calculating the number of layers according to the thickness of the axial module placed at different positions set in S1 and the thickness of single layer prepreg B, cutting to the required shape and number of layers, until the size set in S1 is reached, obtaining the axial single block module; using prepreg B to wrap the foam board (4) of a predetermined size, obtaining the number and size of the axial sandwich foam board set in S1; using prepreg B to make the number and size of the axial insert set in S1; then placing the axial insert and axial sandwich foam board at the position of the axial single block module set in S1 to form an axial module (2); repeat the above steps until the number of axial modules (2) set in S1 is obtained; lay the axial modules (2) according to the sequence set in S1 according to the sequence set in S1, forming the sandwich structure of the ejector blank; placing the skin (3) on the sandwich structure, and forming the preform of the ejector after pre-pressing; The raw material of the skin (3) is prepreg C; the prepreg C is continuous carbon fiber prepreg, continuous glass fiber prepreg cloth or short fiber prepreg; The light weight high strength composite ejector includes a sandwich structure in which radial modules (1) and axial modules (2) are arranged alternately, and the outer surface of the sandwich structure is provided with a skin (3); The radial module is composed of a plurality of radial single block modules, radial inserts and radial sandwich foam boards; the axial module is composed of a plurality of axial single block modules, axial inserts and axial sandwich foam boards.

2. The method of claim 1, wherein the method further comprises the step of: The preparation process of the skin (3) is as follows: According to the thickness of different positions and the thickness of single layer prepreg C, the number of layers is calculated, and the shape and number of layers are cut until the size and number set in S1 are reached.

3. The method for preparing a lightweight, high-strength composite material sabot according to claim 1, characterized in that, The prepreg A and prepreg B are carbon fiber prepreg or glass fiber prepreg; the fiber is carbon fiber cloth or glass fiber cloth.

4. The method of claim 1, wherein the method further comprises the step of: The material of the foam board (4) is foam core or foam adhesive film; the foaming ratio of the foam board (4) is 1-5 times.

5. The method for preparing a lightweight, high-strength composite material sabot according to claim 1, characterized in that, The number of radial sandwich foam plates is one less than the number of radial modules (1); the number of axial sandwich foam plates is one less than the number of axial modules (2).

6. The method of claim 1, wherein the method further comprises: The number of radial inserts is one less than the number of radial modules (1); the number of axial inserts is one less than the number of axial modules (2); the size of the radial and axial inserts is determined by the number of layers and thickness of the radial and axial single-piece modules, and the total number of layers of the radial modules (1) and axial modules (2).

7. The method for preparing a lightweight, high-strength composite material sabot according to claim 1, characterized in that, The number of radial modules (1) is determined by the thickness of the preform divided by the thickness of the radial modules (1); the number of axial modules (2) is determined by the thickness of the preform divided by the thickness of the axial modules (2).

8. The method for preparing a lightweight, high-strength composite material sabot according to claim 1, characterized in that, The number of layers of the axial modules (2) in different positions = the thickness of the axial modules (2) ÷ the thickness of a single layer of fiber material B; if not divisible, the number of layers of the axial modules (2) in different positions = the integer obtained after division + 1; The number of layers of the skin (3) = the thickness of different positions ÷ the thickness of a single layer of prepreg C.

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