Bulletproof armor structure and transporter with bulletproof armor structure

Abstract

The utility model relates to the technical field of armor protection, and discloses a bulletproof armor structure which comprises a crack arrest layer, a ceramic layer, a metal layer, a transition layer, a first supporting layer and a second supporting layer which are sequentially bonded from outside to inside in the bullet receiving direction. The crack arrest layer and the transition layer are both made of a fiber reinforced composite material; the first supporting layer and the second supporting layer are both fiber reinforced composite material laminated plates, and the thickness of the first supporting layer is larger than that of the second supporting layer. According to the bulletproof armor, the ceramic layer is restrained through the crack arrest layer, the ceramic layer is effectively supported through the metal layer, the transition layer, the first supporting layer and the second supporting layer, the defense capacity of the bulletproof armor for armor-piercing bullets is improved, and the bulletproof armor has the advantages of being good in armor-piercing bullet attack protection effect and capable of preventing ceramic fragments from splashing.

Description

Technical Field

[0001] The utility model relates to the technical field of armor protection, in particular to a bulletproof armor structure and a transport aircraft equipped with the bulletproof armor structure. Background Art

[0002] The armor structures currently used in aircraft are unable to effectively utilize the ceramic layer's ability to resist armor-piercing projectiles, resulting in penetration of the armor structure and splashing of ceramic fragments after being hit by armor-piercing projectiles. At the same time, the splashing ceramic fragments may also affect the flight stability of the aircraft. Utility Model Content

[0003] In response to the shortcomings of existing armor structures, such as being easily penetrated by armor-piercing projectiles and ceramic fragments easily scattering after being struck by projectiles, the present invention aims to provide a bulletproof armor structure and a transport aircraft equipped with the same. The bulletproof armor structure constrains the ceramic layer through a crack arrester layer to prevent it from shattering and scattering. At the same time, the metal layer, transition layer, first support layer, and second support layer effectively support the ceramic layer, thereby improving the transport aircraft equipped with the bulletproof armor structure's defense capabilities against armor-piercing projectiles. The bulletproof armor structure and transport aircraft equipped with the same provide solutions to the problems of existing armor structures being easily penetrated by armor-piercing projectiles and causing ceramic fragments to scatter, which in turn affects the transport aircraft's flight stability, and provide excellent protection against armor-piercing projectile attacks.

[0004] The utility model is achieved through the following technical solutions:

[0005] In a first aspect, the utility model provides a bulletproof armor structure, comprising a crack arrest layer, a ceramic layer, a metal layer, a transition layer, a first support layer, and a second support layer, which are bonded and arranged in sequence from the outside to the inside in the direction of bullet exposure;

[0006] The material of the crack arrest layer and the material of the transition layer are both fiber reinforced composite materials;

[0007] The first supporting layer and the second supporting layer are both fiber-reinforced composite laminates, and the first supporting layer is thicker than the second supporting layer.

[0008] Through the above technical solution, the bullet-proof armor structure of the present application has a fiber-reinforced composite material crack-stop layer adhered to the ceramic layer. Therefore, when attacked by an armor-piercing projectile, the crack-stop layer, which is only partially damaged, can maintain the constraint on the ceramic layer, preventing the ceramic from shattering and splashing. The ceramic layer absorbs part of the bullet's kinetic energy through its own fragmentation, while also causing the bullet to deform and shatter, thereby reducing the bullet's erosion ability. The metal layer is arranged on the back of the ceramic layer, which can provide a certain degree of support for the ceramic layer and further improve the performance of the ceramic layer in abrading the bullet, thereby further reducing the bullet's erosion ability. The transition layer after the metal layer can also provide a certain degree of constraint on the ceramic layer, the metal layer and the first support layer, further preventing fragments from flying. The first support layer and the second support layer are both laminated plates, which can further cooperate with the metal layer to provide a strong support effect for the ceramic layer. When the broken bullet erodes with residual kinetic energy, they work together with the transition layer to consume the residual kinetic energy of the bullet through fiber breakage and tensile deformation. The first support layer can also protect against fragments generated when the previous layers are hit, and the second support layer can also prevent bulging on the back of the armor structure after being hit.

[0009] In order to better realize the present invention, further, the material of the crack arresting layer is aramid III woven fabric or aramid II woven fabric.

[0010] Through the above technical solution, the crack-arresting layer is less damaged when it is hit by bullets, and can achieve a better restraint effect on the ceramic layer, further preventing the ceramic from splashing after breaking, and can also maintain good performance at low temperatures, which is suitable for high-altitude and low-temperature environments.

[0011] In order to better realize the present invention, further, the material of the ceramic layer is boron carbide ceramic or silicon carbide ceramic.

[0012] Through the above technical solution, boron carbide ceramics or silicon carbide ceramics have better hardness and energy absorption effect, and produce less fragments.

[0013] In order to better realize the present invention, further, the metal layer is a titanium alloy plate, an aluminum alloy plate or an alloy steel plate.

[0014] Through the above technical solution, the metal layer can provide good support for the ceramic layer. At the same time, a metal plate of appropriate weight and thickness can be selected according to the actual situation of the conveyor.

[0015] In order to better realize the present invention, further, the material of the transition layer is aramid II woven fabric with a surface density of 240g / ㎡.

[0016] Through the above technical solution, the use of aramid II woven fabric with a surface density of 240g / ㎡ can provide higher strength while maintaining a suitable weight, and can also maintain good performance at low temperatures, which is suitable for high-altitude and low-temperature environments.

[0017] In order to better realize the present invention, further, the first supporting layer is a laminated molded polyethylene UD cloth laminate.

[0018] Through the above technical solution, the polyethylene UD cloth has excellent mechanical properties in the longitudinal and transverse directions after lamination and molding, and can more effectively protect against fragments generated when the previous layers are hit. It can also maintain good performance at low temperatures and is suitable for high-altitude and low-temperature environments.

[0019] In order to better implement the present invention, further, the thickness of the first supporting layer is in the range of 8-10 mm, and the weight of the first supporting layer is less than or equal to 1 kg.

[0020] Through the above technical solution, the polyethylene UD cloth laminated plate with a laminated molded plate within this thickness range and weight range can maintain its strength while controlling its own weight within a suitable range, making it more suitable for use in transport aircraft.

[0021] In order to better realize the present invention, further, the second supporting layer is a laminated molded aramid III woven fabric laminate.

[0022] Through the above technical solution, the aramid fibers in the laminated molded aramid III woven fabric laminate are interwoven between the layers to form a stable three-dimensional structure, which enables the laminate to evenly disperse stress when subjected to force, thereby improving its overall strength and modulus, allowing the laminate to withstand large external forces without being easily deformed or damaged, providing good support for the ceramic layer, and more effectively preventing the armor structure from bulging on the back after being hit. In addition to maintaining good performance even at low temperatures, it is suitable for high-altitude and low-temperature environments and also has good flame retardant effects.

[0023] In order to better implement the present invention, further, the thickness of the second supporting layer is in the range of 2-4 mm, and the weight of the second supporting layer is less than or equal to 0.4 kg.

[0024] Through the above technical solution, the laminated molded aramid III woven fabric laminate within this thickness range and weight range can maintain its strength while controlling its own weight within a suitable range, making it more suitable for use in transport aircraft.

[0025] In a second aspect, the present invention provides a transport aircraft, wherein the bulletproof armor structure of the transport aircraft adopts a bulletproof armor structure as described in any one of the first aspects.

[0026] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0027] (1) The armor structure can maintain the restraint on the ceramic layer through the transition layer and the fiber reinforced composite crack arrest layer bonded to the ceramic layer, preventing the ceramic from splashing after breaking;

[0028] (2) The armor structure provides a strong support effect for the ceramic layer through the metal layer and the first and second support layers set by the laminate, so that the entire armor structure can effectively withstand the impact kinetic energy of the armor-piercing projectile, thereby improving the bulletproof capability of the armor structure and effectively preventing the armor structure from being penetrated by the armor-piercing projectile;

[0029] (3) The armor structure is simple, the manufacturing cost is low, and the one-time molding qualification rate is high. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The present invention is further described in conjunction with the following drawings and embodiments. All the concepts and innovations of the present invention should be regarded as the disclosed contents and the protection scope of the present invention.

[0031] Figure 1 This is a schematic diagram of an embodiment of a bulletproof armor structure in the present utility model.

[0032] Among them: 1. Crack arrest layer; 2. Ceramic layer; 3. Metal layer; 4. Transition layer; 5. First support layer; 6. Second support layer. DETAILED DESCRIPTION

[0033] Example 1:

[0034] This embodiment provides a bulletproof armor structure, such as Figure 1 As shown, it includes a crack arrest layer 1, a ceramic layer 2, a metal layer 3, a transition layer 4, a first supporting layer 5 and a second supporting layer 6 which are bonded in sequence from the outside to the inside in the direction of the elasticity;

[0035] The material of the crack arrest layer 1 and the material of the transition layer 4 are both fiber reinforced composite materials;

[0036] The first supporting layer 5 and the second supporting layer 6 are both fiber-reinforced composite laminates, and the thickness of the first supporting layer 5 is greater than that of the second supporting layer 6 .

[0037] Specifically, the fiber-reinforced composite material can be a glass fiber-reinforced composite material, an aramid fiber-reinforced composite material or a carbon fiber-reinforced composite material, which is bonded to the ceramic layer 2 to constrain the ceramic layer 2 to prevent fragments from flying; the fiber-reinforced composite material laminate is used as the first support layer 5 and the second support layer 6, which can provide support for the ceramic layer 2 while also effectively consuming the residual kinetic energy of the bullet.

[0038] In summary, the working principle of this embodiment is:

[0039] When the armor structure is attacked by an armor-piercing projectile, the outermost fiber-reinforced composite crack-arresting layer 1 will only be partially damaged, maintaining the constraint on the ceramic layer 2 and preventing ceramic fragments from flying; the ceramic layer 2 absorbs part of the bullet's kinetic energy through its own fragmentation, while also causing the bullet to deform and break, reducing the bullet's erosion ability, and under the joint support of the metal layer 3, the first support layer 5 and the second support layer 6, it effectively resists the impact energy of the armor-piercing projectile; the metal layer 3 further reduces the erosion ability of the armor-piercing projectile through its own tensile deformation; the transition layer 4 after the metal layer 3 can also constrain the ceramic layer 2, the metal layer 3 and the first support layer 5 to a certain extent, and consume part of the bullet's kinetic energy through its own fiber breakage; the first support layer 5 and the second support layer 6 set in the laminate consume residual kinetic energy through fiber breakage and tensile deformation.

[0040] Example 2:

[0041] This embodiment is further optimized on the basis of the embodiment 1 to provide a bulletproof armor structure. Preferably, in this embodiment, the material of the crack arresting layer 1 is aramid III woven fabric or aramid II woven fabric.

[0042] Specifically, in this embodiment, aramid III woven fabric or aramid II woven fabric adopts a fiber interweaving method, has high strength in all directions, is less damaged when it is hit by bullets, can effectively restrain the ceramic layer 2, and can maintain good performance at low temperatures, and is suitable for high-altitude and low-temperature environments.

[0043] Preferably, in this embodiment, the material of the ceramic layer 2 is boron carbide ceramic or silicon carbide ceramic.

[0044] Specifically, according to this embodiment, both boron carbide ceramics and silicon carbide ceramics have the characteristics of high hardness and low density, and are suitable for use in aircraft such as transport aircraft.

[0045] Preferably, in this embodiment, the metal layer 3 is a titanium alloy plate, an aluminum alloy plate or an alloy steel plate.

[0046] Specifically, according to this embodiment, the plate-shaped metal can effectively support the ceramic layer 2 .

[0047] Preferably, the transition layer 4 is made of aramid II woven fabric with a surface density of 240 g / m2.

[0048] Specifically, using this embodiment, the aramid II woven fabric with an area density of 240g / ㎡ has excellent strength and modulus, can withstand large external forces and deformations, and can maintain good performance at low temperatures, and is suitable for high-altitude and low-temperature environments.

[0049] Preferably, the first supporting layer 5 is a laminated molded polyethylene UD cloth laminate.

[0050] Further preferably, the thickness of the first supporting layer 5 is in the range of 8-10 mm, and the weight of the first supporting layer 5 is less than or equal to 1 kg.

[0051] Specifically, with this embodiment, since the armor structure on a transport aircraft is usually modular in order to adapt to the aircraft model, the laminated molded polyethylene UD cloth laminate within this thickness range and weight range can maintain its strength while controlling its own weight within an appropriate range, making it more suitable for use in transport aircraft and able to maintain good performance even in high-altitude and low-temperature environments. Of course, the use of ultra-high-density polyethylene UD cloth will have a better effect.

[0052] Preferably, the second supporting layer 6 is a laminated molded aramid III woven fabric laminate.

[0053] Further preferably, the thickness of the second supporting layer 6 is in the range of 2-4 mm, and the weight of the second supporting layer 6 is less than or equal to 0.4 kg.

[0054] Specifically, with this embodiment, since the armor structure on a transport aircraft is usually modular in order to adapt to the aircraft model, the laminated molded aramid III woven fabric laminate within this thickness range and weight range can maintain its strength while controlling its own weight within an appropriate range, making it more suitable for use in transport aircraft and able to maintain good performance even in high-altitude and low-temperature environments.

[0055] When bonding, modified resin glue is used as an adhesive, which can improve the stability of this embodiment in a high-altitude and low-temperature environment; preferably, after the above layers are prepared separately, epoxy resin glue can also be used as an adhesive at the interface between the layers, and the entire set of armor structure parts is placed in an autoclave for high-temperature and high-pressure curing, and integrally formed, thereby further improving the bulletproof capability of the armor structure.

[0056] The rest of this embodiment is the same as that of embodiment 1, so it will not be described again.

[0057] This embodiment mainly matches appropriate materials for each layer, and also matches appropriate shapes, thicknesses, and weights for the first supporting layer 5 and the second supporting layer 6, so that the entire armor structure can maintain excellent bulletproof capabilities even in high-altitude and low-temperature environments. Therefore, the main working principle is similar to that of Example 1, so it will not be repeated here.

[0058] In summary, the beneficial effects of this embodiment also include:

[0059] The use of low-temperature resistant materials such as aramid III woven fabric, aramid II woven fabric, and polyethylene UD fabric enables the armor structure to maintain good performance even at high altitudes and low temperatures;

[0060] Each layer is matched with an optimal shape, thickness, weight, etc. For example, a laminated molded polyethylene UD cloth laminate with a thickness range of 8-10 mm and a weight less than or equal to 1 kg is selected as the first supporting layer 5. While maintaining the overall weight within an appropriate range, the bulletproof performance of the armor structure is further improved, making it more suitable for use in transport aircraft.

[0061] Example 3

[0062] This embodiment provides a transport aircraft, the bulletproof armor structure of the transport aircraft adopts a bulletproof armor structure as described in any one of Embodiment 1 or Embodiment 2.

[0063] The beneficial effects of this embodiment include:

[0064] Due to the adoption of the bulletproof armor structure in the above embodiment, the transport aircraft in this embodiment has a better defense effect against armor-piercing bullets and can also avoid the adverse effects of flying caused by flying ceramic fragments.

[0065] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent change made to the above embodiment based on the technical essence of the present invention shall fall within the scope of protection of the present invention.

Claims

1. A bulletproof armor structure, characterized in that: It comprises a crack arresting layer (1), a ceramic layer (2), a metal layer (3), a transition layer (4), a first supporting layer (5) and a second supporting layer (6) which are bonded and arranged in sequence from the outside to the inside in the direction of elasticity; The material of the crack arrest layer (1) and the material of the transition layer (4) are both fiber-reinforced composite materials; The first supporting layer (5) and the second supporting layer (6) are both fiber-reinforced composite material laminates, and the thickness of the first supporting layer (5) is greater than that of the second supporting layer (6).

2. The bulletproof armor structure according to claim 1, characterized in that: The material of the crack arresting layer (1) is aramid III woven fabric or aramid II woven fabric.

3. The bulletproof armor structure according to claim 1, characterized in that: The material of the ceramic layer (2) is boron carbide ceramic or silicon carbide ceramic.

4. The bulletproof armor structure according to claim 1, characterized in that: The metal layer (3) is a titanium alloy plate, an aluminum alloy plate or an alloy steel plate.

5. The bulletproof armor structure according to claim 1, characterized in that: The material of the transition layer (4) is aramid II woven fabric with a surface density of 240 g / ㎡.

6. The bulletproof armor structure according to claim 1, characterized in that: The first supporting layer (5) is a laminated and molded polyethylene UD cloth laminate.

7. The bulletproof armor structure according to claim 6, characterized in that: The thickness of the first supporting layer (5) is in the range of 8-10 mm, and the weight of the first supporting layer (5) is less than or equal to 1 kg.

8. The bulletproof armor structure according to claim 1, characterized in that: The second supporting layer (6) is a laminated molded aramid III woven fabric laminate.

9. The bulletproof armor structure according to claim 8, characterized in that: The thickness of the second supporting layer (6) is in the range of 2-4 mm, and the weight of the second supporting layer (6) is less than or equal to 0.4 kg.

10. A transport aircraft, characterized in that: The bulletproof armor structure of the transport aircraft adopts a bulletproof armor structure as described in any one of claims 1-9.

Images