High-strength composite material sabot and preparation method thereof

Abstract

The invention provides a high-strength composite material sabot and a preparation method thereof, and belongs to the technical field of shelling and armor-piercing bullets. The sabot comprises a main stress structure, the main stress structure comprises a plurality of laying layer sets, each laying layer set is formed by a tooth part layer and a middle layer attached to the tooth part layer, and the multiple laying layer sets are connected in a laying layer mode in the stress direction of the sabot; and the middle layer and the tooth part layer are made of unidirectional carbon fiber materials. The middle layer is attached to the tooth part layer, so that the middle layer can effectively enhance the strength of the tooth part layer, and the pressure bearing capacity of the tooth part structure is improved. When the sabot is stressed, the stress can be uniformly dispersed by the middle layer, so that the tooth part layer is prevented from being damaged due to overlarge local stress; layering connection is carried out between the layering groups along the stress direction of the sabot, and the interlayer direction of the sabot is parallel to the stress direction, so that the product is effectively prevented from cracking along the interlayer, and the strength of the sabot is improved.

Description

Technical Field

[0001] This application relates to the field of discarding sabot armor-piercing projectile technology, and in particular to a high-strength composite material sabot and its preparation method. Background Technology

[0002] The fin-stabilized discarding sabot armor-piercing projectile is a major type of ammunition used by modern main battle tanks. It consists of two parts: the projectile and the explosive charge. The projectile part is mainly composed of the flight part and the detachment part. The sabot involved in this invention is a detachment part of the projectile part in the fin-stabilized discarding sabot armor-piercing projectile.

[0003] When a fin-stabilized discarding sabot armor-piercing projectile is launched, the propellant explodes inside the gun barrel, generating a powerful thrust. This thrust acts on the sabot, and the annular groove inside the sabot engages with the annular groove outside the projectile core (flying part), transferring kinetic energy to the projectile core. After the sabot and projectile core fly away from the muzzle together, the sabot detaches from the projectile core due to air resistance and centrifugal force.

[0004] With the continuous development of global military technology, armor-piercing projectile technology is also advancing. Major developed countries are researching how to improve the power of armor-piercing projectiles, and reducing their negative mass can effectively enhance their effectiveness. As can be seen from the structure of an armor-piercing projectile, the sabot is a core-stabilizing component, a non-combat component, and represents the negative mass of a fin-stabilized discarding sabot armor-piercing projectile. Therefore, how to manufacture a lightweight and high-strength sabot has become a current hot topic in military research.

[0005] Currently, sabots are mainly made of metal materials such as ultra-hard aluminum alloys and aluminum-magnesium alloys. However, carbon fiber composites, as advanced composite materials, have demonstrated significant performance advantages. Compared to LC9CS (aluminum alloy), epoxy resin carbon fiber composites have a 43% lower density but a 91% higher strength. Using carbon fiber composites to make sabots can effectively reduce projectile weight and increase the power of armor-piercing projectiles. According to Qin Changhu's document "Development and Application of Sabot Materials for Armor-Piercing Discarding Sabots," a certain domestic sabot product uses carbon fiber epoxy resin instead of LC9CS in its manufacturing process. This reduces the product weight by 0.81 kg, and with the same propellant charge, increases the initial projectile velocity by 67 m / s, thereby increasing the effective armor-piercing range by 1300 m. This is of paramount importance for improving the PLA's combat capabilities.

[0006] The current challenge in carbon fiber development lies in the molding method of the grooves inside the sabot. The sabot contains numerous annular teeth, approximately 1.5 mm wide and 3 mm high, requiring each groove to withstand a pressure greater than 70,000 N. According to literature and patents, some manufacturers use a method of laying carbon fiber cloth flat and then pressing it into a sabot blank, machining the annular grooves onto the blank. However, this process damages the fiber continuity, resulting in teeth strength that does not meet requirements. Other manufacturers use unidirectional carbon fiber layup followed by winding to form the grooves. This method is difficult to use, and since the winding fiber direction is aligned with the groove direction, the pressure direction of the groove is perpendicular to the fiber direction, which is detrimental to the groove's ability to withstand pressure. Some manufacturers use a segmented groove molding method, where the carbon fiber at the teeth is laid up along the X and Y directions (see...). Figure 1 This method cannot eliminate the technical challenge of low interlayer strength in carbon fiber cloth, and the tooth grooves crack along the ply direction under pressure. Trapezoidal teeth are used to transfer the load between the sabot and the core, with each tooth bearing significant shear stress. Given the low interlayer shear strength of carbon fiber, enhancing the strength of the trapezoidal teeth in the sabot's inner core has become a key technical challenge that needs to be addressed. Summary of the Invention

[0007] This application is made in view of the above-mentioned problems, and its purpose is to provide a high-strength composite material sabot and a method for preparing the same.

[0008] Specifically, the first aspect of this application provides a high-strength composite material sabot, the sabot including a main force-bearing structure, the main force-bearing structure including a plurality of ply groups formed by toothed layers and intermediate layers attached to the toothed layers, and the plurality of ply groups are connected in the direction of force of the sabot. Both the intermediate layer and the toothed layer are made of unidirectional carbon fiber.

[0009] Furthermore, the fiber direction of the intermediate layer is parallel to the axis of the spring support, and the fiber direction of the toothed layer is perpendicular to the axis of the spring support.

[0010] Furthermore, the number of intermediate layers is calculated according to the following formula: N 中间层数量 =(L 外圆弧 -L 内圆弧 ) / t Among them, L 外圆弧 L is the outer arc length of the sabot. 内圆弧 t is the inner arc length of the sabot, and t is the thickness of a single layer of carbon fiber.

[0011] Furthermore, the intermediate layer comprises several intermediate layers of the same length but different widths, and these intermediate layers of different widths are arranged in order from largest to smallest and then back to largest, and are evenly distributed.

[0012] Furthermore, the number of layers in the tooth layer is calculated according to the following formula: N 齿部层数量 =L 内圆弧 / t Among them, L 内圆弧 t is the inner arc length of the sabot, and t is the thickness of a single layer of carbon fiber.

[0013] Furthermore, the number of intermediate layers corresponding to each tooth layer is M=N. 齿部层数量 / N 中间层数量 .

[0014] Furthermore, the sabot also includes an external load-bearing structure that is attached to the outside of the main load-bearing structure. The external load-bearing structure includes a transition layer and an outer layer. The fiber direction of the transition layer is parallel to the axial direction of the sabot, and the fiber direction of the outer layer is along the outer circle of the sabot.

[0015] Furthermore, the ejector also includes an inner layer, which is disposed on the inner surface of the toothed layer.

[0016] A second aspect of this application provides a method for preparing the high-strength composite material bullet holder, comprising the following steps: Each tooth layer is stacked and compacted according to the number of intermediate layers that need to be paired, forming a layup group; The toothed layer in the ply stack is trimmed and cut to form a toothed structure; Several ply groups are stacked and compacted along the direction of elastic force to form the main load-bearing structure; The external load-bearing structure is laid on the outside of the main load-bearing structure.

[0017] Furthermore, the toothed layer and the intermediate layer are ply-connected along the direction of the elastic force.

[0018] The present invention has the following beneficial effects: The projectile sabot of this invention includes a main load-bearing structure, which comprises several ply stacks consisting of toothed layers and intermediate layers attached to the toothed layers. By attaching the intermediate layers to the toothed layers, the intermediate layers effectively enhance the strength of the toothed layers and improve the pressure resistance of the toothed structure. When the projectile sabot is under stress, the intermediate layers can evenly distribute the stress, preventing the toothed layers from being damaged due to excessive local stress. The ply stacks are connected along the load-bearing direction of the projectile sabot, and the interlayer direction of the projectile sabot is parallel to the load-bearing direction, effectively preventing cracking along the interlayer. The intermediate layers and toothed layers are both made of unidirectional carbon fiber, which has high strength and high modulus, providing excellent mechanical properties for the projectile sabot. The fiber direction of the intermediate layers is parallel to the axial direction of the projectile sabot, effectively transmitting axial stress and ensuring that the projectile sabot can evenly transmit force when under stress, avoiding stress concentration. The fiber direction of the toothed layers is perpendicular to the axial direction of the projectile sabot, enhancing the load-bearing capacity of the teeth in the vertical direction, improving the shear resistance of the teeth, and better coping with the shear stress generated when the load is transmitted between the projectile sabot and the projectile core.

[0019] In terms of preparation method, the tooth layer and intermediate layer are first laminated and compacted to form a ply stack. Then, the tooth layer is trimmed and the teeth are cut. Finally, the ply stacks are superimposed and compacted to form the main load-bearing structure. This ply stacking method can prevent the fibers of the tooth layer from moving and deforming during compression, thus affecting the tooth strength of the sabot and ensuring the integrity and stability of the tooth structure. An external load-bearing structure ply is then applied to the outer layer of the main load-bearing structure. The fiber direction of the transition layer is parallel to the sabot axis, which can further enhance the axial load-bearing capacity of the sabot. The fiber direction of the outer layer is along the outer circumference of the sabot, which can effectively resist the stress in the outer circumference direction of the sabot and improve the overall stability and reliability of the sabot.

[0020] This invention relates to a high-strength composite material sabot and its preparation method. Through a unique structural design and a reasonable layup method, it fully leverages the advantages of unidirectional carbon fiber materials, solving technical problems in existing sabot manufacturing such as insufficient tooth strength and interlayer cracking. It provides a lightweight and high-strength sabot solution for fin-stabilized discarding sabot armor-piercing projectiles, helping to improve the power and performance of armor-piercing projectiles and meeting the needs of modern military operations. Furthermore, the preparation method of this sabot is relatively simple to operate, easy to industrialize, and has good application prospects and economic benefits. Attached Figure Description To more clearly illustrate the technical solutions in the embodiments of this drawing or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this drawing. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0021] Figure 1This is a diagram showing the force direction of the sabot. Figure 2 This is a schematic diagram of the inner layer of the sabot; Figure 3 Schematic diagram of sabot structure Figure 1 ; Figure 4 Schematic diagram of sabot structure Figure 2 ; Figure 5 A schematic diagram showing the arrangement of the tooth layer and the intermediate layer; Figure 6 This is a schematic diagram of the cross-section of the sabot; Figure 7 This is a schematic diagram of the pressure testing device of the present invention; Figure 8 The pressure test results are those of this invention.

[0022] The following are the symbols in the attached diagram: 1. Toothed layer; 2. Intermediate layer; 3. Transition layer; 4. Outer layer; 5. Inner layer; 6. Spring support; 7. Upper tooling; 8. Lower tooling.

[0023] The purpose, features, and advantages of this accompanying drawing will be further explained in conjunction with the embodiments and with reference to the accompanying drawing. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of this application clearer, the following description and illustration are provided in conjunction with embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application. All other embodiments obtained by those skilled in the art based on the embodiments provided in this application without inventive effort are within the scope of protection of this application.

[0025] Obviously, the following description is merely some examples or embodiments of this application. Those skilled in the art can apply this application to other similar scenarios without any inventive effort. Furthermore, it is understood that although the effort involved in such development may be complex and lengthy, for those skilled in the art related to the content disclosed in this application, any changes to design, manufacturing, or production based on the technical content disclosed in this application are merely conventional technical means and should not be construed as insufficient disclosure of the content of this application.

[0026] An embodiment of the first aspect of this application provides a high-strength composite material sabot, the sabot including a main force-bearing structure, the main force-bearing structure comprising a plurality of ply groups formed by a toothed layer 1 and an intermediate layer 2 attached to the toothed layer 1, the plurality of ply groups being connected in the direction of force of the sabot; the intermediate layer 2 and the toothed layer 1 are both made of unidirectional carbon fiber material.

[0027] In this embodiment, the fiber direction of the intermediate layer 2 is parallel to the axial direction of the spring support, and the fiber direction of the toothed layer 1 is perpendicular to the axial direction of the spring support.

[0028] The function of the intermediate layer 2 is to transfer the thrust exerted by the propellant on the bottom of the sabot during the firing of the armor-piercing projectile to the teeth of the sabot. The direction of the thrust is the Z direction (see [reference]). Figure 1 The intermediate layer 2 of the sabot is arranged with Z-direction fibers (sabot axial fibers).

[0029] The function of the toothed ply is to transfer the thrust from the intermediate layer 2 to the outer teeth of the projectile core through the inner teeth of the sabot. The sabot teeth require high strength. Utilizing the high bending strength of carbon fiber, starting from the root of the sabot teeth, the fiber ply direction within the teeth is perpendicular to the thrust direction (Z-axis), solving the technical problem of insufficient strength of the sabot's inner teeth. This structure allows the axial fibers of the intermediate layer 2 to cooperate with the vertical fibers of the toothed layer 1, forming a stable and efficient force transmission system. During the firing of the armor-piercing projectile, the powerful thrust generated by the propellant acts axially on the sabot, and the axial fibers of the intermediate layer 2 can effectively transfer this thrust to each toothed layer 1. Meanwhile, the vertical fibers of the toothed layer 1 provide sufficient shear resistance when the teeth are subjected to large shear stresses, ensuring that the teeth do not suffer damage or deformation during load transfer.

[0030] The intermediate layer 2 and the toothed layer 1 are made of epoxy resin reinforced carbon fiber unidirectional prepreg, epoxy resin reinforced carbon fiber plain weave prepreg, or epoxy resin reinforced carbon fiber felt prepreg. These materials have good processing and mechanical properties, enabling them to better meet the molding and performance requirements of the projectile. Epoxy resin reinforced carbon fiber unidirectional prepreg has high strength and high modulus, and its fiber direction is controllable, allowing for reasonable layering according to the stress requirements of different parts of the projectile. Epoxy resin reinforced carbon fiber plain weave prepreg has relatively balanced warp and weft strength, which can improve the overall stability of the projectile. Epoxy resin reinforced carbon fiber felt prepreg has good flexibility and filling properties, better adapting to the complex structure of the projectile. Preferably, the intermediate layer 2 and the toothed layer 1 are made of epoxy resin reinforced carbon fiber unidirectional prepreg.

[0031] In the actual fabrication of sabots, appropriate materials can be flexibly selected based on the specific stress conditions and performance requirements of different parts of the sabot. For the intermediate layer 2 and toothed layer 1 in the main load-bearing structure, epoxy resin reinforced carbon fiber unidirectional prepreg can be preferentially selected to fully utilize its advantages of high strength and controllable fiber direction. In some parts with high stability requirements, epoxy resin reinforced carbon fiber plain weave prepreg can be appropriately added. When filling gaps or complex structures, epoxy resin reinforced carbon fiber felt prepreg can play a good role in filling and reinforcing.

[0032] The projectile sabot of this invention includes a main load-bearing structure, which comprises several ply stacks formed by toothed layers 1 and intermediate layers 2 attached to the toothed layers 1. By attaching the intermediate layers 2 to the toothed layers 1, the intermediate layers 2 effectively enhance the strength of the toothed layers 1 and improve the pressure resistance of the toothed structure. When the projectile sabot is under stress, the intermediate layers 2 can evenly distribute the stress, preventing the toothed layers 1 from being damaged due to excessive local stress. The ply stacks are connected along the load-bearing direction of the projectile sabot, and the interlayer direction of the projectile sabot is parallel to the load-bearing direction, effectively preventing cracking along the interlayer. The intermediate layers 2 and the toothed layers 1 are both made of unidirectional carbon fiber material. Unidirectional carbon fiber material has the characteristics of high strength and high modulus, which can provide good mechanical properties for the projectile sabot. The fiber direction of the intermediate layers 2 is parallel to the axial direction of the projectile sabot, which can effectively transmit axial stress, allowing the projectile sabot to evenly transmit force when under stress and avoid stress concentration. The fiber direction of the tooth layer 1 is perpendicular to the axis of the sabot, which can enhance the load-bearing capacity of the tooth in the vertical direction, improve the shear resistance of the tooth, and better cope with the shear stress generated when the load is transferred between the sabot and the core.

[0033] In this embodiment, the number of layers in the intermediate layer 2 is calculated according to the following formula: N 中间层数量 =(L 外圆弧 -L 内圆弧 ) / t Among them, L 外圆弧 L is the outer arc length of the sabot. 内圆弧 t is the inner arc length of the sabot, and t is the thickness of a single layer of carbon fiber.

[0034] The cross-section of the sabot product is 1 / 3 of a circle. Calculate the length difference between the inner and outer arcs of the sabot product (excluding the teeth) according to the product drawings. This length difference is the required thickness of the 2 carbon fiber intermediate layer (see [reference]). Figure 5 The number of carbon fiber layers required for the intermediate layer 2 is calculated by dividing the difference in inner and outer arc lengths by the thickness of a single carbon fiber layer after molding. After determining the number of intermediate layer 2 layers, the laying of the intermediate layer 2 can be precisely controlled according to the actual dimensions of the sabot, ensuring the rationality of the sabot structure. For sabots of different specifications, the inner and outer arc lengths are different; this formula allows for quick and accurate calculation of the required number of intermediate layer 2 layers, improving production efficiency and product quality.

[0035] In this embodiment, the intermediate layer 2 comprises several intermediate layers 2 of the same length but different widths. These intermediate layers 2 of different widths are arranged in descending order of width and then increasing again, and are evenly distributed to form a fan-shaped structure. See also... Figure 6Because the difference in length between the inner and outer arcs of the product leads to an inconsistency in the number of fiber layers required for the inner and outer arc cross-sections, theoretically, the smaller the difference in the width of the intermediate layers and the more intermediate layers there are, the more the product layup meets the requirements and the more precise the layup. However, more intermediate layers lead to a more complex layup process. A reasonable intermediate layer width can simplify the layup while still meeting the requirements. Theoretically, the difference in intermediate layer width should be smaller closer to the tooth root, with intermediate layer width 3 - intermediate layer width 4 < intermediate layer width 2 - intermediate layer width 3 < intermediate layer width 1 - intermediate layer width 2. In this embodiment, four different widths of intermediate layers 2 are set, arranged in order from largest to smallest and then back to largest. The length of the carbon fiber in intermediate layer 2 is consistent with the length of the product, and the width of the carbon fiber in intermediate layer 2 changes with the length of the product's arc. Carbon fiber layers of different widths should be matched together and evenly distributed in the product to better transfer force to the tooth layer 1. This method of arranging several intermediate layers 2 of different widths in order from largest to smallest and then back to largest can make the stress distribution of intermediate layer 2 in the circumferential direction of the spring support more uniform. When the sabot is subjected to axial thrust, the intermediate layer 2 of this fan-shaped structure can more effectively distribute the force to each tooth layer 1, avoiding stress concentration in local areas and further improving the overall load-bearing capacity of the sabot. Moreover, the uniformly distributed intermediate layer 2 can ensure that each tooth layer 1 receives a relatively balanced force, making the sabot's teeth more stable and reliable in transmitting loads.

[0036] In this embodiment, the number of tooth layer 1 is calculated according to the following formula: N 齿部层数量 =L 内圆弧 / t Among them, L 内圆弧 t is the inner arc length of the sabot, and t is the thickness of a single layer of carbon fiber.

[0037] The length of the arc at the root of the inner tooth of the spring clip is the required thickness of the carbon fiber layer 1 in the tooth section. The required number of carbon fiber layers N for forming the inner tooth is... 齿部层数量 =L 内圆弧 / t, where the width of the carbon fiber layer is the difference between the inner and outer radii. When determining the number of tooth layers, this formula can accurately determine the required number of tooth layers 1 based on the inner arc length of the spring and the thickness of a single carbon fiber layer, thereby ensuring the strength and stability of the tooth structure.

[0038] This invention, through strength testing of the sabot teeth, discovered that the failure occurred at the tooth root. Therefore, the length of the tooth arc was used as the basis for calculating the tooth layer. Measurements showed the inner arc of the product to be 34.09 mm. Using 200 grams of unidirectional fiber, the calculated number of layers was... N 齿部层数量 =L 内圆弧 / t=34.09mm / 0.2mm=170.45 layers, but in actual production, the value is taken as 171 layers.

[0039] In this embodiment, the number of intermediate layers 2 corresponding to each tooth layer 1 is M=N. 齿部层数量 / N 中间层数量 The number of toothed layers 1 laid up by dividing the number of intermediate layers 2 laid up gives the number of toothed layers 1 that need to be paired with each intermediate layer 2. The required number of toothed layers 1 to be paired with each intermediate layer 2 are stacked according to the fiber direction and compacted to form a layup group. To ensure that the relative positions of the fibers do not shift during cutting, the intermediate layers 2 are attached to the corresponding positions of the toothed layers 1 before cutting and tooth cutting. Both intermediate layers 2 and toothed layers 1 are made of unidirectional carbon fiber, and their stacking directions are shown in [reference needed]. Figure 3 , Figure 4 After each intermediate layer 2 is laminated and pressed with the corresponding toothed layer 1, the teeth are cut. The tooth shape of the toothed layer 1 is cut using a tooth-cutting tool. If the tooth shape is not cut, the fibers of the toothed layer 1 will move and deform during pressing, affecting the strength of the product's teeth.

[0040] This process involves laying the intermediate layer 2 on top of the toothed layer 1 to form a ply stack. The toothed layer 1 within the ply stack is then cut. This step prevents the fibers of the toothed layer 1 from shifting or deforming during subsequent pressing, thus ensuring the strength of the sabot's teeth. Simultaneously, the intermediate layer 2 and toothed layer 1 are properly paired and stacked and compacted, making the sabot structurally more stable and better able to withstand the immense pressure during launch.

[0041] After the toothed layer 1 is attached to the intermediate layer 2 and the teeth are cut, the main structural layup can begin. Each layer is stacked and compacted along the YZ plane according to the distribution of the intermediate layer 2 within the product. After the main structural layup is completed, a cross-sectional diagram showing the distribution of each layer in the product is shown below. Figure 6 .

[0042] After the toothing operation of the ply stacks is completed, each ply stack needs to be cleaned to remove debris and impurities generated during the toothing process, ensuring a clean and smooth surface. This step is crucial for the subsequent stacking and compaction of ply stacks, as the presence of impurities can affect the interlayer bonding strength, thereby reducing the overall performance of the sabot. After cleaning, several ply stacks are stacked along the sabot's force direction. During stacking, it is essential to ensure accurate alignment of each ply stack. After stacking, the main load-bearing structure is compacted to ensure full bonding between the ply stacks, improving the overall strength and stability of the sabot. When stacking and compacting several ply stacks along the sabot's force direction to form the main load-bearing structure, attention must be paid to the stacking order and the uniformity of compaction. Stacking in the order required by the design ensures the rationality and stability of the force transmission system. Uniform compaction ensures full adhesion between ply stacks, improving interlayer bonding strength and preventing delamination. Professional pressing equipment can be used, and the quality of the main load-bearing structure should be ensured according to the material characteristics and process requirements.

[0043] In this embodiment, the ejector also includes an external load-bearing structure that adheres to the outside of the main load-bearing structure. The external load-bearing structure includes a transition layer 3 and an outer layer 4. The fiber direction of the transition layer 3 is parallel to the ejector's axial direction; the fiber direction of the outer layer 4 is along the outer circumference of the ejector. The fibers of the transition layer 3 are parallel to the axial direction and are used to fill uneven areas after the tooth layer is laid up, increasing structural strength. The fibers of the outer layer 4 are aligned circumferentially and are used to enhance the interlaminar strength of the tooth layer 1.

[0044] The outer layer 4 of the spring support is made of carbon fiber plain weave prepreg and unidirectional carbon fiber prepreg. The surface of the transition layer 3 in contact with the main load-bearing structure is perpendicular to the fiber plane of the transition layer 3. This surface is not smooth, so 2-3 layers of unidirectional carbon fiber prepreg are used as the contact surface layer of the transition layer 3. The fiber direction is consistent with the Z direction. The unidirectional carbon fiber prepreg fiber bundle has a certain fluidity to fill the contact surface.

[0045] The outer layer has a layup structure of [(0 / 90)3 / 903]. The layup in the 90° direction is symmetrical with the inner layup, which reduces the internal stress of the product and prevents the product from deforming.

[0046] In this embodiment, the ejector also includes an inner layer 5, which is disposed on the inner surface of the toothed layer 1.

[0047] The innermost layer (5) of the sabot product is the outer layer, which is in direct contact with the propellant during combustion and detonation. This layer enhances the product's aesthetics and provides protection for the second layer. Depending on the technical requirements for the product's appearance, this layer can be made of either epoxy resin-reinforced carbon fiber plain weave prepreg or epoxy resin-reinforced carbon fiber felt prepreg, covering the toothed cavity surface of the product. Figure 2This layer should be removed if the product has no appearance requirements. Applying this layer can easily lead to resin accumulation at the sharp corners of the product's teeth.

[0048] An embodiment of the second aspect of this application provides a method for preparing the high-strength composite material sabot, comprising the following steps: Each tooth layer 1 is stacked and compacted according to the number of intermediate layers 2 that need to be paired. The tooth layer 1 and the intermediate layer 2 are connected by layup along the direction of elastic force to form a layup group. The tooth layer 1 in the ply stack is trimmed and cut to form a tooth structure; Several ply groups are stacked and compacted along the direction of elastic force to form the main load-bearing structure; The external load-bearing structure is laid on the outside of the main load-bearing structure.

[0049] The preparation method of this invention first involves properly pairing and compacting the intermediate layer 2 and the toothed layer 1 during the formation of the ply stack, ensuring a tight bond between them and laying a solid foundation for subsequent force transmission. The toothed layer 1 is then trimmed and toothed to prevent fiber movement and deformation during the pressing process, thus guaranteeing the strength of the sabot's teeth. When stacking the ply stacks to form the main load-bearing structure, the operation is strictly performed according to the sabot's force direction, ensuring the stacking sequence and uniform compaction. This allows for thorough bonding between the ply stacks, improving the overall strength and stability of the sabot and enabling it to better withstand the enormous pressure generated during the launch of an armor-piercing projectile.

[0050] An external load-bearing structure is laid out on the outside of the main load-bearing structure. The transition layer 3 fills the uneven area after the toothed layer is laid out, increasing the structural strength. The outer layer 4 fibers are along the outer circumference of the elastic support, enhancing the interlaminar strength of the toothed layer 1. At the same time, the reasonable layup structure design reduces the internal stress of the product and prevents product deformation. The inner layer 5 is selected according to the product's appearance requirements, which can improve the product's aesthetics and provide protection for the second layer.

[0051] In actual production, strict quality control is required throughout the preparation process. For example, during cutting and toothing operations, dimensional accuracy must be ensured to avoid affecting the performance of the spring due to dimensional deviations. During layup and compaction, the bonding between layers must be monitored in real time to ensure that the interlayer bonding strength meets the requirements. At the same time, the quality of raw materials also needs to be strictly controlled to ensure that the unidirectional carbon fiber materials and epoxy resin-reinforced carbon fiber prepregs used meet relevant standards.

[0052] In summary, the main load-bearing fiber direction of the spring-loaded product of this invention is in the ZY plane, the thrust experienced by the product is along the Z direction, and the interlayer direction is parallel to the load direction, effectively preventing cracking along the interlayer and overcoming the problem of low interlayer strength in existing carbon fiber spring-loaded products. The teeth of the spring-loaded product of this invention withstand relatively large shear forces; all fibers within the teeth are designed perpendicular to the load direction to improve the shear strength of the teeth. In the main load-bearing structure, the intermediate layer and the tooth layer sandwich each other, ensuring effective transmission of thrust to the teeth and enhancing the shear force of the teeth.

[0053] Experimental Case according to Figure 7 A test fixture was set up, and the sabot 6 of the present invention was installed between the upper fixture 7 and the lower fixture 8. A compression testing machine was used to apply a vertical load for testing, and the load value was recorded. The results are shown in […]. Figure 8 .

[0054] from Figure 8 It is evident that the sabot of this invention can withstand a pressure of 48 kN without deformation or damage. This fully demonstrates the advantages of the sabot in structural design and material selection. By rationally designing the fiber direction and layup method of the intermediate layer and toothed layer, and accurately calculating the number of layers, the sabot can evenly distribute stress when subjected to high pressure, avoiding excessive local stress that could lead to damage.

[0055] To further verify the performance stability of the sabot of this invention, we conducted multiple repeated tests. Samples were randomly selected from sabots produced in different batches and tested under the same conditions. The results showed that each sample could stably withstand a pressure of 48 kN, and the fluctuation range of the test data was extremely small. This indicates that the manufacturing process of the sabot of this invention has high consistency and reliability, ensuring stable product quality.

[0056] The sabot of this invention has also demonstrated great potential in practical applications. In a military exercise, the success rate of armor-piercing projectiles using the sabot of this invention was significantly improved, and the sabot itself was not damaged during launch, effectively ensuring the flight stability and hit rate of the projectile core.

[0057] It should be noted that this application is not limited to the above-described embodiments. The above embodiments are merely examples, and any embodiments with the same structure and effect as the technical concept within the scope of this application are included in the technical scope of this application. Furthermore, various modifications that can be conceived by those skilled in the art to the embodiments, and other ways of constructing by combining some of the constituent elements of the embodiments, without departing from the spirit of this application, are also included in the scope of this application.

Claims

1. A high-strength composite material sabot, characterized in that, The sabot includes a main force-bearing structure, which is composed of several ply groups formed by a toothed layer (1) and an intermediate layer (2) attached to the toothed layer (1), and the ply groups are connected in the direction of force of the sabot. The intermediate layer (2) and the toothed layer (1) are both made of unidirectional carbon fiber.

2. The high-strength composite material sabot according to claim 1, characterized in that, The fiber direction of the intermediate layer (2) is parallel to the axis of the spring, and the fiber direction of the toothed layer (1) is perpendicular to the axis of the spring.

3. The high-strength composite material sabot according to claim 1, characterized in that, The number of layers in the intermediate layer (2) is calculated according to the following formula: N 中间层数量 =(L 外圆弧 -L 内圆弧 ) / t Among them, L 外圆弧 L is the outer arc length of the sabot. 内圆弧 t represents the inner arc length of the sabot, and t represents the thickness of a single layer of carbon fiber.

4. The high-strength composite material sabot according to claim 1, characterized in that, The intermediate layer (2) contains several intermediate layers (2) of the same length but different widths. The several intermediate layers (2) of different widths are arranged in order from large to small and then back to large, and are evenly distributed.

5. The high-strength composite material sabot according to claim 3, characterized in that, The number of layers in the tooth layer (1) is calculated according to the following formula: N 齿部层数量 =L 内圆弧 / t Among them, L 内圆弧 t represents the inner arc length of the sabot, and t represents the thickness of a single layer of carbon fiber.

6. The high-strength composite material sabot according to claim 5, characterized in that, The number of intermediate layers (2) corresponding to each tooth layer (1) is M=N 齿部层数量 / N 中间层数量 .

7. The high-strength composite material sabot according to claim 1, characterized in that, The sabot also includes an external load-bearing structure that is attached to the outside of the main load-bearing structure. The external load-bearing structure includes a transition layer (3) and an outer layer (4). The fiber direction of the transition layer (3) is parallel to the axial direction of the sabot. The fiber direction of the outer layer (4) is along the outer circle of the sabot.

8. The high-strength composite material sabot according to claim 1, characterized in that, The sabot also includes an inner layer (5), which is disposed on the inner surface of the toothed layer (1).

9. A method for preparing a high-strength composite material sabot according to any one of claims 1-8, characterized in that, Includes the following steps: Each tooth layer (1) is stacked and compacted according to the number of intermediate layers (2) that need to be paired, to form a layup group; The tooth layer (1) in the ply stack is trimmed and cut to form a tooth structure; Several ply groups are stacked and compacted along the direction of elastic force to form the main load-bearing structure; The external load-bearing structure is laid on the outside of the main load-bearing structure.

10. The method for preparing a high-strength composite material sabot according to claim 9, characterized in that, The toothed layer (1) and the intermediate layer (2) are connected by plying along the direction of the spring force.

Images