Helicopter bulletproof armor with resistance reduction structure

Abstract

The utility model provides a helicopter bulletproof armor with a resistance reduction structure. The helicopter bulletproof armor comprises a crack arrest layer, an armor breaking layer, a transition layer, a supporting layer and a resistance reduction module. The crack arrest layer is laid on the armor breaking layer; the device is used for preventing secondary damage caused by ceramic splashing in the striking process. The armor breaking layer is a ceramic plate laid on the transition layer, the transition layer is laid between the armor breaking layer and the supporting layer and used for buffering kinetic energy of an elastic body, the supporting layer is a high-performance fiberboard carved into a step-shaped structure, and a T-shaped groove structure is prefabricated on each high-performance fiberboard; the resistance reduction module comprises a T-shaped nut, a round head hexagon socket screw, a resistance reduction piece and a pin. According to the bulletproof armor, a backflow type structural member is combined with the bulletproof armor, so that the bulletproof armor with bulletproof and resistance reduction functions is scientific and reliable in design, energy-saving, environment-friendly and suitable for popularization.

Description

Technical Field

[0001] The utility model belongs to the technical field of bulletproof armor, in particular to a helicopter bulletproof armor with a drag reduction structure. Background Art

[0002] As the range and power of ground-based air defense weapons continue to increase, the battlefield survivability of modern military helicopters and transport aircraft faces severe challenges. Currently, military helicopters such as the US military's Black Hawk (UH-60), Apache (AH-64), Russia's Ka-50 and China's armed helicopters are all equipped with different levels of bulletproof armor in the cockpit and crew compartment.

[0003] At present, the helicopter fuselage is mostly divided into three parts: head, middle and tail. According to the protection requirements, the helicopter bulletproof armor is mainly distributed in the cockpit, crew compartment and engine. The cockpit is located at the head of the helicopter, and the crew compartment and engine are generally located in the middle or tail of the helicopter. The most common firepower threats faced by helicopter bulletproof armor are: armor-piercing incendiary bullets fired by anti-aircraft machine guns of 7.62mm, 12.7mm and 14.5mm. The bulletproof armor surface density is 37kg / m 2 -70kg / m 2 In addition, a set of bulletproof armor improves battlefield survivability while also increasing the helicopter's flight resistance to a certain extent; military helicopters have undergone years of iterative updates and have unique aerodynamic characteristics. Their structural design can resist the influence of air resistance and ensure the normal flight of the helicopter; in addition to air resistance, helicopter fuselage resistance is also one of the important sources of flight resistance.

[0004] At present, the power system of military helicopters has the problem of insufficient carrying capacity. After adding bulletproof armor, the power system will face a more severe burden. In addition to the well-known weight factor, the shape design of the bulletproof armor is also a key factor affecting the flight performance of the helicopter. Because the shapes and angles of the bulletproof armor of various parts of helicopters are different, if special-shaped armor is to be prepared, a large number of molds need to be developed, which is not conducive to later maintenance, and the procurement and manufacturing costs will also increase significantly. Therefore, the bulletproof armor of helicopters currently in service is mainly based on a regular right-angled square structure, resulting in the existing bulletproof armor's insufficient ability to resist the influence of air resistance. Utility Model Content

[0005] In order to solve the above technical problems, the utility model provides a helicopter bulletproof armor with a drag reduction structure. Through the design of a composite insert structure, a helicopter bulletproof armor with a backflow shape is produced. Without the need to re-open various molds, the production cost is reduced, the equipment performance is improved, and the finished product is safe and reliable.

[0006] A helicopter bulletproof armor with a drag reduction structure, comprising: a crack arrest layer, an armor-piercing layer, a transition layer, a support layer, and a drag reduction module;

[0007] The crack-stop layer is laid above the armor-piercing layer, the drag-reducing component, and the right side of the support layer; it is used to prevent secondary damage caused by ceramic splashes during the impact process;

[0008] As an example, the stop layer is a single layer of high-performance fiber fabric;

[0009] As an example, the high-performance fiber fabric includes: aramid II woven fabric, aramid III woven fabric, PBO woven fabric or PI woven fabric.

[0010] The armor-piercing layer is a ceramic plate laid on the transition layer;

[0011] As an example, the ceramic plate is a plate structure obtained by shaping and cutting special ceramics; the special ceramics include boron carbide, graphene-modified boron carbide or TiB2-B4C composite ceramics.

[0012] The transition layer is laid between the armor-piercing layer and the support layer to buffer the kinetic energy of the projectile;

[0013] As an example, the transition layer is: a single layer of high-performance fiber fabric.

[0014] The support layer is a high-performance fiberboard carved into a step-like structure, and each high-performance fiberboard is prefabricated with a T-slot structure;

[0015] As an example, the high-performance fiberboard includes: aramid board, ultra-high molecular weight polyethylene (PE) board, carbon fiber board or glass fiber board.

[0016] As an example, the engraving refers to: using an engraving machine to process the high-performance fiberboard into a step shape.

[0017] The drag reduction module includes: a T-nut, a round head hexagon socket bolt, a drag reduction part and a pin;

[0018] The drag reducing member is provided with a drag reducing chamfer structure on one side of the drag reducing member according to the fuselage shape and flight direction of the helicopter mounting portion, and a countersunk hole is provided on the slope surface of the drag reducing chamfer structure; a bolt through hole is provided on the other side of the drag reducing member; the bolt through hole and the countersunk hole are connected left and right;

[0019] The T-nut is embedded in the prefabricated T-slot structure of the support layer, the round-head hexagon socket bolt is placed in the countersunk hole and extends out of the bolt through-hole, the drag reduction component is placed on the stepped structure of the support layer, and the round-head hexagon socket bolt and the T-nut are movably connected to form a whole; at the same time, the top of the drag reduction component is ensured to be flush with the top of the armor-piercing layer, and the drag reduction chamfer structure is consistent with the surface curvature of the right side of the support layer;

[0020] As an example, after the round head hexagon socket bolt is installed on the drag reduction component, the remaining gap in the countersunk hole is filled with a pin, and the external exposed surface of the pin is consistent with the surface curvature of the drag reduction chamfer structure, thereby realizing a closed integrated drag reduction structure and overcoming the air resistance caused by the gap in the countersunk hole.

[0021] As an example, the T-nut adopts: T-type self-locking nut.

[0022] As an example, the material of the drag reducing component is: aluminum alloy, carbon fiber profile or high-strength nylon. The use of the above-mentioned easily machined profiles can improve manufacturing efficiency.

[0023] Beneficial effects of the utility model:

[0024] This utility model targets the threats of 7.62mm, 12.7mm and 14.5mm armor-piercing incendiary bullets. The bulletproof armor requires bulletproof ceramics and high-performance fiberboard and other materials with different physical and chemical properties. According to the original layered arrangement and combination, relying on the scientific integration of the bulletproof differences of each layer, it has the purpose of higher crushing projectiles, consuming projectile energy and preventing projectile penetration.

[0025] The bulletproof armor produced according to the structure of the utility model has the advantages of light weight, wide temperature range, stable anti-ballistic performance, etc.; it solves the problems of bulletproof structure, drag reduction and speed increase, and reduction of overall energy consumption of helicopters (and also aircraft, high-speed armored vehicles and other protective equipment) in the process of bulletproof design integration.

[0026] Without the need to reopen a mold, the utility model breaks through the structure of the composite insert, combines the backflow-type structural parts with the bulletproof armor, and adopts a one-time composite molding process to realize a bulletproof armor with both bulletproof and drag reduction functions. In the future, it can be applied to various special-shaped bulletproof armors with drag reduction requirements. The design is scientific and reliable, energy-saving and environmentally friendly, and suitable for promotion. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is the overall structural design diagram of a helicopter bulletproof armor with a drag reduction structure according to the present utility model.

[0028] Figure 2This is a decomposed structural design diagram of a helicopter bulletproof armor with a drag reduction structure according to the present invention.

[0029] Figure 3 This is a design diagram of the support layer structure of a helicopter bulletproof armor with a drag reduction structure according to the present invention.

[0030] Figure 4 This is a top view design diagram of a drag reduction module of a helicopter bulletproof armor with a drag reduction structure according to the present invention.

[0031] Figure 5 The utility model is a schematic diagram of the use position of a helicopter bulletproof armor with a drag reduction structure.

[0032] Figure 6 This is a dimensional diagram of the bulletproof armor for the engine area of ​​an armed helicopter, Example 1 of the utility model, which is a helicopter bulletproof armor with a drag reduction structure.

[0033] Figure 7 This is a schematic diagram of the dimensions of the special ceramic plates after shaping and cutting for the armed helicopter of Example 1 of the utility model, which is a helicopter bulletproof armor with a drag reduction structure.

[0034] Figure 8 This is a schematic diagram of the assembly dimensions of ceramic plates used in an armed helicopter in Example 1 of the utility model, which is a helicopter bulletproof armor with a drag reduction structure.

[0035] Figure 9 This is an example diagram of the processing dimensions of Example 1 of the utility model of a helicopter bulletproof armor with a drag reduction structure, in which the support layer of an armed helicopter is carved into a step-like structure.

[0036] Figure 10 This is an example diagram of the processing dimensions of the drag reduction parts of an armed helicopter in Example 1 of the utility model, which is a helicopter bulletproof armor with a drag reduction structure.

[0037] Figure 11 This is a diagram showing the processing dimension data of the T-slot structure of an armed helicopter in Example 1 of the utility model, a helicopter bulletproof armor with a drag reduction structure. DETAILED DESCRIPTION

[0038] Below, reference Figures 1 to 11 As shown, a helicopter bulletproof armor with a drag reduction structure includes: a crack arrest layer 101, an armor-piercing layer 102, a transition layer 103, a support layer 104 and a drag reduction module;

[0039] The crack-stop layer 101 is laid above the right side of the armor-piercing layer 102, the drag-reducing element 105, and the supporting layer 104; it is used to prevent secondary damage caused by ceramic splashes during the impact process;

[0040] As an example, the stop layer 101 is a single layer of high-performance fiber fabric;

[0041] As an example, the high-performance fiber fabric includes: aramid II woven fabric, aramid III woven fabric, PBO woven fabric or PI woven fabric.

[0042] The armor-piercing layer 102 is a ceramic plate laid on the transition layer 103;

[0043] As an example, the ceramic plate is a plate structure obtained by shaping and cutting special ceramics; the special ceramics include boron carbide, graphene-modified boron carbide or TiB2-B4C composite ceramics.

[0044] The transition layer 103 is laid between the armor-piercing layer 102 and the support layer 104 to buffer the kinetic energy of the projectile;

[0045] As an example, the transition layer 103 is a single layer of high-performance fiber fabric.

[0046] The support layer 104 is a high-performance fiberboard carved into a step-like structure, and each high-performance fiberboard is prefabricated with a T-slot structure 109;

[0047] As an example, the high-performance fiberboard includes: aramid board, ultra-high molecular weight polyethylene (PE) board, carbon fiber board or glass fiber board.

[0048] As an example, the engraving refers to: using an engraving machine to process the high-performance fiberboard into a step shape.

[0049] The drag reduction module includes: a T-nut 106, a round head hexagon socket bolt 107, a drag reduction member 105 and a pin 108;

[0050] The drag reducing member 105 is provided with a drag reducing chamfer structure on one side of the drag reducing member 105 according to the fuselage shape and flight direction of the helicopter mounting portion. A countersunk hole 110 is provided on the slope surface of the drag reducing chamfer structure. A bolt through hole is provided on the other side of the drag reducing member 105. The bolt through hole is connected to the countersunk hole 110 in a left-right manner.

[0051] Insert the T-nut 106 into the prefabricated T-slot structure 109 of the support layer 104, insert the round head hexagon socket bolt into the countersunk hole 110, and extend it out of the bolt through hole to tightly connect the drag reducing member 105 and the support layer 104 into one;

[0052] The T-nut 106 is embedded in the prefabricated T-slot structure 109 of the supporting layer, the round head hexagon socket bolt is placed in the countersunk hole 110 and extends out of the bolt through hole, the drag reducing component 105 is placed on the stepped structure of the supporting layer 104, and is movably connected as a whole through the round head hexagon socket bolt and the T-nut; at the same time, the top of the drag reducing component 105 is ensured to be highly flush with the top of the armor-piercing layer 102, and the drag reducing chamfer structure is consistent with the surface curvature of the right side of the supporting layer 104; (that is, a drag reducing chamfer that is connected from top to bottom and has a consistent overall surface curvature) is formed.

[0053] As an example, after the round head hexagon socket bolt 107 is installed on the drag reduction component 105, the remaining gap of the countersunk hole is filled with a pin 108. The external exposed surface of the pin 108 is consistent with the surface curvature of the drag reduction chamfer structure, realizing a closed integrated drag reduction structure and overcoming the air resistance caused by the gap of the countersunk hole 110.

[0054] As an example, the T-nut adopts: T-type self-locking nut.

[0055] As an example, the material of the drag reducing member 105 is aluminum alloy, carbon fiber profile or high-strength nylon. The use of the above-mentioned easily machined profiles can improve manufacturing efficiency.

[0056] As an example, the crack-stop layer 101, the armor-piercing layer 102, the transition layer 103 and the support layer 104 are bonded together into an integrated structure by adhesive.

[0057] The bonded structure can be further hot-pressed into a single piece using a vacuum autoclave to form a more solid integrated structure.

[0058] In order to better illustrate the design principle of the present invention, the benefits of the present invention are now described through specific embodiments.

[0059] Example 1:

[0060] Take the bulletproof armor of the right engine of an armed helicopter for example, which is designed to protect against 12.7mm armor-piercing incendiary bullets with a target impact speed of 488m / s and a 0° angle of incidence. The size diagram of the bulletproof armor is as follows: Figure 6 As shown:

[0061] 1. Cut and punch the 300*300*10mm boron carbide ceramic according to the size of the bulletproof armor. Figure 7 As shown;

[0062] 2. Assemble the cut ceramics and fill the ceramic joints with epoxy adhesive to form a whole plate armor-breaking layer, such as Figure 8 As shown;

[0063] 3. Use the engraving machine to cut the supporting layer aramid board into Figure 9 The dimensions shown are shown, and a "T"-shaped groove is carved out to eventually form a stepped support layer;

[0064] 4. Use CNC machining center to process block nylon material into drag reducing parts with reverse flow structure and preset countersunk holes, such as Figure 10 As shown;

[0065] 5.Insert steel T-shaped self-locking nuts into the T-shaped slots of the support layer. The specifications and dimensions are as follows: Figure 11 As shown, the drag reduction component and the main structure of the bulletproof armor are then connected together through M4 round head hexagon socket bolts, and the remaining through holes of the drag reduction are filled with pins to achieve a closed structure.

[0066] 6. 340g / m 2 Aramid woven fabric covers the armor-piercing layer and drag-reducing module;

[0067] 7. Lay 180g / m between each structural material 2 TPU hot melt adhesive film;

[0068] 8. Place the assembled integrated structure into a vacuum sealed bag and perform vacuum hot pressing and lamination;

[0069] 9. Spray the armor with aviation paint after it comes out of the can.

[0070] 10. Using the Kriging proxy model to calculate the drag coefficient, the utility model bulletproof armor reduces the drag coefficient by 11.7% compared to traditional bulletproof armor. Combat tests have shown that the utility model helicopter bulletproof armor effectively improves helicopter combat performance and has been widely praised by local forces. For details, please see the attached certification of the installation effect during the internal confidential testing of the troops, which was included in the simultaneous application materials when applying for the patent.

[0071] The above is only a preferred embodiment of the present invention. It should be understood that the description of the above embodiment is only used to help understand the method and core idea of ​​the present invention, and is not used to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, etc. made within the ideas and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A helicopter bulletproof armor with a drag reduction structure, characterized in that: include: Crack arrest layer, armor-piercing layer, transition layer, support layer and drag reduction module; The crack-stop layer is laid above the armor-piercing layer, the drag-reducing component, and the right side of the support layer; it is used to prevent secondary damage caused by ceramic splashes during the impact process; The armor-piercing layer is a ceramic plate laid on the transition layer; The transition layer is laid between the armor-piercing layer and the support layer to buffer the kinetic energy of the projectile; The support layer is a high-performance fiberboard carved into a step-like structure, and each high-performance fiberboard is prefabricated with a T-slot structure; The drag reduction module includes: a T-nut, a round head hexagon socket bolt, a drag reduction part and a pin; According to the fuselage shape and flight direction of the helicopter installation part, the drag reducing part is provided with a drag reducing chamfer structure on one side of the drag reducing part, and a countersunk hole is provided on the slope surface of the drag reducing chamfer structure; a bolt through hole is provided on the other side of the drag reducing part; the bolt through hole and the countersunk hole are connected left and right; the T-nut is embedded in the T-slot structure prefabricated on the supporting layer, the round head hexagon socket bolt is placed in the countersunk hole and extended out of the bolt through hole, the drag reducing part is placed on the stepped structure of the supporting layer, and is movably connected to each other through the round head hexagon socket bolt and the T-nut; at the same time, it is ensured that the top of the drag reducing part is highly flush with the top of the armor-piercing layer, and the surface curvature of the drag reducing chamfer structure is consistent with that of the right side of the supporting layer.

2. The helicopter bulletproof armor with a drag reduction structure according to claim 1, characterized in that: The crack arresting layer is a single layer of high-performance fiber fabric.

3. The helicopter bulletproof armor with a drag reduction structure according to claim 1, characterized in that: The ceramic plate is a plate structure obtained by shaping and cutting special ceramics.

4. The helicopter bulletproof armor with a drag reduction structure according to claim 1, characterized in that: The transition layer is: a single-layer high-performance fiber fabric layer.

5. The helicopter bulletproof armor with a drag reduction structure according to claim 1, characterized in that: The high-performance fiberboard includes: aramid board, ultra-high molecular weight polyethylene board, carbon fiber board or glass fiber board.

6. The helicopter bulletproof armor with a drag reduction structure according to claim 1, characterized in that: After the round head hexagon socket bolt is installed on the drag reducing component, the remaining space of the countersunk hole is filled with a pin.

7. The helicopter bulletproof armor with a drag reduction structure according to claim 1, characterized in that: The exposed outer surface of the pin is consistent with the surface curvature of the drag reduction chamfered structure.

8. The helicopter bulletproof armor with a drag reduction structure according to claim 1, characterized in that: The T-nut adopts: T-type self-locking nut.

9. The helicopter bulletproof armor with a drag reduction structure according to claim 1, characterized in that: The material of the drag reducing component is: aluminum alloy, carbon fiber profile or high-strength nylon.

10. The helicopter bulletproof armor with a drag reduction structure according to claim 1, characterized in that: The crack-stop layer, the armor-piercing layer, the transition layer and the supporting layer are bonded and connected as a whole by adhesive.

Images