CN116907279A - Helicopter armor structure for resisting half-speed 12.7mm armor piercing bullet - Google Patents
Helicopter armor structure for resisting half-speed 12.7mm armor piercing bullet Download PDFInfo
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- 239000000919 ceramic Substances 0.000 claims abstract description 79
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 55
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 53
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 43
- 239000004917 carbon fiber Substances 0.000 claims abstract description 43
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 43
- 239000000463 material Substances 0.000 claims abstract description 31
- 238000005452 bending Methods 0.000 claims abstract description 18
- 239000003733 fiber-reinforced composite Substances 0.000 claims abstract description 16
- 230000006835 compression Effects 0.000 claims abstract description 10
- 238000007906 compression Methods 0.000 claims abstract description 10
- 229910052751 metal Inorganic materials 0.000 claims abstract description 10
- 239000002905 metal composite material Substances 0.000 claims abstract description 6
- 239000011208 reinforced composite material Substances 0.000 claims abstract description 6
- 238000005299 abrasion Methods 0.000 claims abstract description 5
- 239000004699 Ultra-high molecular weight polyethylene Substances 0.000 claims description 10
- 229920000785 ultra high molecular weight polyethylene Polymers 0.000 claims description 10
- 229910052580 B4C Inorganic materials 0.000 claims description 6
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 6
- INAHAJYZKVIDIZ-UHFFFAOYSA-N boron carbide Chemical compound B12B3B4C32B41 INAHAJYZKVIDIZ-UHFFFAOYSA-N 0.000 claims description 6
- 230000009471 action Effects 0.000 claims description 5
- 239000004760 aramid Substances 0.000 claims description 5
- 229920003235 aromatic polyamide Polymers 0.000 claims description 5
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000000853 adhesive Substances 0.000 claims description 3
- 230000001070 adhesive effect Effects 0.000 claims description 3
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 claims description 3
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 3
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 9
- 239000002131 composite material Substances 0.000 description 47
- 239000010410 layer Substances 0.000 description 36
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- 229920006231 aramid fiber Polymers 0.000 description 4
- 239000012634 fragment Substances 0.000 description 4
- 239000013585 weight reducing agent Substances 0.000 description 4
- 229910010293 ceramic material Inorganic materials 0.000 description 3
- 239000012792 core layer Substances 0.000 description 3
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- 238000012360 testing method Methods 0.000 description 2
- 229910001008 7075 aluminium alloy Inorganic materials 0.000 description 1
- 229910000883 Ti6Al4V Inorganic materials 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
- F41H5/00—Armour; Armour plates
- F41H5/02—Plate construction
- F41H5/04—Plate construction composed of more than one layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
- F41H5/00—Armour; Armour plates
- F41H5/02—Plate construction
- F41H5/04—Plate construction composed of more than one layer
- F41H5/0414—Layered armour containing ceramic material
- F41H5/0428—Ceramic layers in combination with additional layers made of fibres, fabrics or plastics
- F41H5/0435—Ceramic layers in combination with additional layers made of fibres, fabrics or plastics the additional layers being only fibre- or fabric-reinforced layers
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a helicopter armor structure for resisting half-speed 12.7mm armor piercing bullet, which relates to the field of helicopter structural design, and comprises the following components: a ceramic panel and a carbon fiber honeycomb sandwich back plate which are sequentially arranged along the incidence direction of the armor-piercing bullet; the ceramic panel is made of anti-bouncing ceramic; the carbon fiber honeycomb sandwich backboard comprises a bullet-facing surface wallboard, a carbon honeycomb sandwich layer and a back bullet-facing surface wallboard which are sequentially arranged along the incidence direction of the armor-piercing bullet; the material of the bullet-facing wall plate and the material of the back bullet-facing wall plate are metal or fiber reinforced composite materials; the carbon honeycomb sandwich layer is of a honeycomb structure; the carbon honeycomb sandwich layer is made of carbon fiber reinforced composite material; the ceramic panel is used for crushing the armor-piercing bullet and reducing armor-piercing bullet kinetic energy through abrasion; the carbon fiber honeycomb sandwich back plate is used for providing bending and compression resistant support for the ceramic panel when the armor-piercing bullet penetrates the ceramic panel. The invention can improve the local support rigidity and reduce the mass of the backing plate of the conforming material in the armor.
Description
Technical Field
The invention relates to the field of helicopter structural design, in particular to a helicopter armor structure for resisting half-speed armor piercing bullets of 12.7 mm.
Background
The combat environment of a military helicopter is usually the front edge of a combat or the depth of enemy, the combat airspace is low or ultra-low, and the helicopter is easy to attack by ground air-defense fire, and the typical threat is a armor piercing projectile with the range of 1000 meters (the impact speed of 487 m/s) (hereinafter referred to as a armor piercing projectile with the half speed of 12.7 mm). In order to improve battlefield viability of military helicopters, armor protection designs are commonly employed throughout the world to improve the resilience of military helicopters. However, there is a contradiction between protection and light weight in armor protection design, on one hand, the improvement of the ability of the bullets to damage puts higher demands on the protection of the armor, and on the other hand, if the existing armor structural form is not changed, the improvement of the armor protection is necessarily at the cost of weight increase, which inevitably compromises the high maneuverability of the weapon platform and indirectly reduces the survivability and performance of the military helicopter in the battlefield. Therefore, light weight is the most important research objective in the field of light weight protection. In order to achieve both protection force and light weight, a single material is difficult to meet the requirements, the ceramic/composite armor has excellent protection performance and simple preparation process, and is the main stream direction of the current light composite armor research.
The armor-piercing bullet with the half speed of 12.7mm is used as a protection object, the armor-piercing bullet core is made of quenched steel, the hardness can reach 80HRV, the yield strength can reach 1500MPa, and the initial shooting speed is close to 1000m/s. The armor-piercing bullet core has an oval head shape, and the tangent line of the head generatrix and the clip angle of the bullet core shaft are smaller than 45 degrees, so that the structural form is not easy to generate shearing damage and is very beneficial to penetration. The top of the bullet can be dulled rapidly under the action of axial resistance. The projectile is constrained by radial symmetry of the armor material, the circumferential direction of the projectile is subjected to equal-probability compression deformation, the deformed projectile still has a centrosymmetric structure, and the penetration effect of the projectile head is high. It follows that the penetration capability of a half-rate 12.7mm armor-piercing projectile is mainly derived from the high hardness and high strength of the core, and the armor-piercing projectile of this type needs to be started from the core breaking mechanism in the armor structural design, and the kinetic energy absorption capability of the armor is simultaneously considered.
For a half-speed armor-piercing bullet with the thickness of 12.7mm, the traditional metal armor mainly consumes the kinetic energy of the armor-piercing bullet through local plastic deformation, so that the energy consumption efficiency is low, and the corresponding protection efficiency is also low. Composite armor structures employing ceramic faceplates/composite backplates are currently common, with ceramic faceplates typically having a thickness of about 10mm. The armor structure fully exerts respective protective advantages: the anti-bullet ceramic utilizes the characteristics of high compression strength and high hardness, under the action of impact force, the bullet head of the sharp armor-piercing bullet is subjected to plastic deformation or crushing, and the armor-piercing bullet energy is consumed through the abrasion process of ceramic fragments and the armor-piercing bullet. The composite material backboard bears impact force to provide support for the ceramic panel, so that the performance of the anti-bullet ceramic is fully exerted, and the backboard absorbs the residual kinetic energy of armor piercing bullets and ceramic fragments through mechanisms such as bending deformation, fiber breakage, debonding layering, fiber stretching and the like, so that the anti-bullet purpose is achieved.
The above-described ballistic mechanism of ceramic/composite armor has been demonstrated in more detail in the literature. For example, wang Dongzhe et al (Wang Dongzhe, qin Rongman, sun Na, et al) test and numerical simulation study of the resistance of ceramic/fiber composite armor to penetration of projectiles [ J ] Material guide, 2021,35 (18): 18216-18221.) the damaged form of boron carbide ceramic/carbon fiber/ultra high molecular weight polyethylene fiber composite armor was obtained through the test, numerical simulation indicated that ceramic panels damaged armor piercing projectiles by their high hardness, consumed some kinetic energy, the presence of the backing plate limited displacement of the ceramic plate and thereby inhibited the generation of cracks, and the fibrous layers absorbed armor piercing projectile energy primarily by fiber breakage and bulging deformation. Liu et al (Liu W, chen Z, cheng X, et al Design and ballistic penetration of the ceramic composite armor Composites Part B: engineering, 2016, 84: 33-40.) have studied the anti-elastic properties of cylindrical spliced ceramic armor under different multi-layer back plate structures through experiments and numerical simulations, and the results show that the combination of titanium alloy, ultra-high molecular weight polyethylene and titanium alloy in the back plate material can greatly improve the buffering and energy absorbing effects of the back plate. Because the characteristics of high hardness and high yield strength of the half-speed 12.7mm armor-piercing bullet core enable the armor-piercing bullet core to have extremely strong penetration capability, thicker composite material laminated plates are generally adopted as back plates in the ceramic/composite material composite armor for protecting the armor-piercing bullet at present so as to provide sufficient structural support, thereby leading to larger mass of the armor structure and being difficult to meet the increasingly high light-weight design requirements. In addition, the local support stiffness of the back sheet is still insufficient due to the lower modulus of elasticity in the out-of-plane direction of the composite laminate sheet. In general, the composite material backboard mainly plays a role in supporting the ceramic panel in the anti-bullet process, and the composite material backboard itself is bent and deformed, and the composite material backboard in the current anti-half-speed 12.7mm armor piercing composite armor has larger mass and insufficient local supporting rigidity.
Disclosure of Invention
The invention aims to provide a helicopter armor structure resisting half-speed 12.7mm armor piercing bullets, which can improve local support rigidity and reduce the mass of a backboard of a conforming material in armor.
In order to achieve the above object, the present invention provides the following solutions:
a helicopter armor structure for resisting a half-speed armor-piercing bullet with the thickness of 12.7mm comprises a ceramic panel and a carbon fiber honeycomb sandwich back plate which are sequentially arranged along the incidence direction of the armor-piercing bullet;
the ceramic panel is made of anti-bouncing ceramic; the carbon fiber honeycomb sandwich backboard comprises a bullet-facing surface wallboard, a carbon honeycomb sandwich layer and a back bullet-facing surface wallboard which are sequentially arranged along the incidence direction of the armor-piercing bullet; the material of the bullet-facing wall plate and the material of the back bullet-facing wall plate are both metal or fiber reinforced composite materials; the carbon honeycomb sandwich layer is of a honeycomb structure; the carbon honeycomb sandwich layer is made of a carbon fiber reinforced composite material;
the ceramic panel is used for crushing the armor-piercing bullet and reducing the armor-piercing bullet kinetic energy through the abrasion action;
the carbon fiber honeycomb sandwich back plate is used for providing bending support and compression support for the ceramic panel when the armor-piercing bullet penetrates the ceramic panel.
Optionally, the honeycomb structure is a honeycomb grid structure with the diameter of the inscribed circle of the honeycomb holes smaller than the diameter of the armor-piercing bullet.
Optionally, the ceramic panel is in a monolithic structure or a spliced structure.
Optionally, the anti-ballistic ceramic is boron carbide, silicon carbide or aluminum oxide.
Optionally, the metal is a titanium alloy, an aluminum alloy, or an armored steel.
Optionally, the fiber reinforced composite material is an ultra-high molecular weight polyethylene fiber reinforced composite material or an aramid fiber reinforced composite material.
Optionally, the face-to-face wall plate thickness is greater than the back-to-face wall plate thickness.
Optionally, the ceramic face plate and the carbon fiber honeycomb sandwich back plate are fixed in an adhesive or bolting way.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
the invention provides a helicopter armor structure for resisting half-speed armor piercing of 12.7mm, which adopts a novel carbon fiber honeycomb sandwich backboard structure of ceramic/composite material composite armor, and from the anti-ballistic mechanism of the ceramic/composite material composite armor, the composite material backboard in a laminated form in the prior art is replaced by a carbon fiber honeycomb sandwich backboard with a face-to-bullet wallboard, a carbon honeycomb sandwich layer and a back-to-bullet wallboard, so that the local supporting rigidity can be obviously increased under the same weight. In addition, the carbon fiber honeycomb sandwich backboard adopts metal or fiber reinforced composite material as the elastic face wallboard and the elastic back face wallboard, and adopts the carbon honeycomb board as the core layer, thereby achieving the purpose of reducing weight on the premise of not obviously sacrificing the bending rigidity of the backboard and being beneficial to the weight reduction of the whole armor structure.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic structural view of a helicopter armor structure of the present invention resistant to half-speed 12.7mm armor piercing;
FIG. 2 is a schematic perspective view of a detailed structure of a carbon honeycomb sandwich layer according to the present invention;
FIG. 3 is a schematic top view of a detailed structure of a carbon honeycomb sandwich layer of the present invention;
FIG. 4 is a schematic diagram of a simulation model of a carbon honeycomb structure according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of a comparative structural simulation model according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of simulation results of a carbon honeycomb structure and a comparative structure according to an embodiment of the present invention; fig. 6 (a) is a schematic diagram of the damage morphology of a carbon fiber honeycomb sandwich back plate of a carbon honeycomb structure after being penetrated by a half-speed armor-piercing bullet of 12.7 mm; fig. 6 (b) is a schematic diagram of the damage morphology of the composite backboard of the comparative structure after penetration by a half-speed 12.7mm armor-piercing bullet;
FIG. 7 is a graph showing the residual speed versus time for a half-rate 12.7mm armor piercing projectile penetration process according to an embodiment of the present invention.
Reference numerals illustrate:
ceramic panel-1, bullet facing wallboard-2, carbon honeycomb sandwich layer-3, back bullet facing wallboard-4, carbon fiber honeycomb sandwich back plate-5, armor-piercing bullet-6, honeycomb holes-21, inner diameter of carbon honeycomb holes-22, thickness of carbon honeycomb Kong Biban-23, thickness of carbon honeycomb sandwich layer-24, composite back plate-41, ultra-high molecular weight polyethylene sublayer-42, aramid sublayer-43, protrusion-51, depression-52, debonding layering-53, bullet pit-54, residual speed-time curve-61 of half speed 12.7mm armor-piercing bullet penetration versus structure, residual speed-time curve-62 of half speed 12.7mm armor-piercing bullet penetration versus carbon honeycomb structure.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a helicopter armor structure resisting half-speed 12.7mm armor piercing bullets, which can improve local support rigidity and reduce the mass of a backboard of a conforming material in armor.
The invention provides a novel ceramic/composite material composite armor structure design, and the novel carbon fiber honeycomb sandwich backboard is adopted, so that the weight reduction and the increase of local supporting rigidity of the whole armor structure are realized on the premise of not reducing the protection capability of the ceramic/composite material composite armor, and the design requirements of taking the protection capability and the light weight into consideration are met.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Example 1
As shown in fig. 1, the invention provides a helicopter armor structure resisting a half-speed armor piercing bullet of 12.7mm, which comprises a ceramic face plate 1 and a carbon fiber honeycomb sandwich back plate 5 which are sequentially arranged along the incidence direction of the armor piercing bullet 6. The ceramic panel 1 and the carbon fiber honeycomb sandwich back plate 5 are fixed in an adhesive or bolt connection mode.
The ceramic panel 1 is in a monolithic structure or a spliced structure. The ceramic panel 1 is made of anti-bouncing ceramic; specifically, the anti-bouncing ceramic is boron carbide, silicon carbide or aluminum oxide. The anti-elastic ceramic has the characteristics of high hardness, high compression strength, high elastic modulus and low density.
The carbon fiber honeycomb sandwich back plate 5 comprises an elastic face wall plate 2, a carbon honeycomb sandwich layer 3 and a back elastic face wall plate 4 which are sequentially arranged along the incidence direction of the armor-piercing shell 6; the elastic face facing wall plate 2, the carbon honeycomb sandwich layer 3 and the back elastic face wall plate 4 are bonded together to form the carbon fiber honeycomb sandwich back plate 5. The material of the elastic face-facing wall plate 2 and the material of the back elastic face wall plate 4 are both metal or fiber reinforced composite materials; in particular, the metal is a titanium alloy, an aluminum alloy or an armored steel. The fiber reinforced composite material is an ultra-high molecular weight polyethylene fiber reinforced composite material or an aramid fiber reinforced composite material. The bullet-facing wall plate thickness is greater than the back bullet-facing wall plate thickness.
The carbon honeycomb sandwich layer 3 is of a honeycomb structure; specifically, the honeycomb structure is a honeycomb grid structure in which the diameter of the inscribed circle of the honeycomb holes 21 is smaller than the diameter of the armor-piercing shell 6. The carbon honeycomb sandwich layer 3 is made of a carbon fiber reinforced composite material.
The ceramic panel 1 is used for breaking up the warhead of the armor-piercing bullet 6 and reducing the kinetic energy of the armor-piercing bullet 6 by abrasion.
The carbon fiber honeycomb sandwich back plate 5 is used for providing bending and compression resistant support for the ceramic panel 1 when the armor-piercing bullet 6 penetrates the ceramic panel 1.
The damage of the anti-bullet ceramic to the armor-piercing bullet 6 comprises two parts of impact fracture and friction erosion: in the early stages of penetration, the impact load promotes fragmentation of the armor-piercing bullet 6 and weakens the kinetic energy and mass of the armor-piercing bullet 6; during the steady penetration phase, armor-piercing bullet 6 needs to expel ceramic fragments that hinder its movement and thus is subject to significant resistance. The thickness and in-plane dimensions of the ceramic panel 1 affect its resistance to springing, and prior studies have shown that the in-plane characteristic length of the ceramic panel 1 should not be less than 45mm, with an optimal thickness of about 10mm. To increase the resistance of the armor unit to single shot, a unitary structure may be used and to increase the resistance of the armor unit to multiple shots, a spliced structure may be used.
The carbon fiber honeycomb sandwich back plate 5 provides enough support for the ceramic panel 1 in the process of playing a target, so that the elastic resistance of the ceramic panel 1 can be fully exerted, and the carbon fiber honeycomb sandwich back plate 5 and the ceramic panel 1 are fixed together in a bonding or bolting mode for forming an elastic resistance structural unit. The carbon fiber honeycomb sandwich back plate 5 is subjected to loads in the form of local compressive loads and global bending loads. As a component of the carbon fiber honeycomb sandwich back plate 5, the functions of the elastic face wall plate 2, the carbon honeycomb sandwich layer 3 and the back elastic face wall plate 4 are respectively emphasized and play a synergistic role.
When the armor-piercing shell 6 penetrates the ceramic face plate 1, the armor-piercing panel 2 serves as a barrier to the projectile body of the armor-piercing shell 6 and the ceramic fragments moving therewith and transfers impact loads to a greater range of structures behind it. The back elastic surface wall plate 4 is connected with the helicopter body structure, plays a supporting role on the whole armor structural unit, and mainly stretches in a loaded mode. In general, since the face plate 2 directly participates in the target action process, its structural strength directly affects the ballistic resistance of the armor unit, the face plate 2 should be made of a material having as high strength as possible and have a thickness greater than the back plate 4.
The carbon honeycomb sandwich layer 3 is a honeycomb grid structure made of carbon fiber reinforced composite material, has higher out-of-plane compression strength, and can play a good supporting role on the elastic face wallboard 2, so that local compression load is converted into compression load with a larger range and is transmitted to the back elastic face wallboard 4. In addition to this, the carbon honeycomb sandwich layer 3 can obtain a larger thickness with a lower mass, thereby enhancing the overall bending resistance of the carbon fiber honeycomb sandwich back sheet 5.
Further, as shown in fig. 2, considering the weak area of the structure inside the honeycomb holes 21, in order to have a good supporting effect on the face plate 2, the inner diameter 22 of the carbon honeycomb holes and the thickness 23 of the carbon honeycomb Kong Biban should consider the actual size of the armor-piercing shell 6, and the thickness 24 of the carbon honeycomb sandwich layer should consider the bending rigidity requirement of the carbon fiber honeycomb sandwich back plate 5 and avoid instability under compressive load.
The helicopter armor structural unit resisting the half-speed 12.7mm armor piercing bullet and the traditional ceramic/composite material backboard composite armor unit are subjected to comparison of the anti-bullet performance through numerical simulation, wherein the helicopter armor structural unit is simply called a carbon honeycomb structure in the following description, and the helicopter armor structural unit is simply called a comparison structure in the following description.
A schematic diagram of a simulation model of a carbon honeycomb structure is shown in FIG. 4, and the overall length, width and thickness of the carbon honeycomb structure are 100mm, 100mm and 23mm, respectively. The ceramic panel 1, the bullet-facing wall plate 2, the carbon honeycomb sandwich layer 3 and the back bullet-facing wall plate 4 are laminated along the incidence direction of the armor-piercing bullet 6 and are fixed by bonding to form the carbon fiber honeycomb sandwich back plate 5. The ceramic panel 1 is made of boron carbide, has the thickness of 10mm and the density of 2.52 g/cm 3 Has the highest Rockwell hardness and bending strength in the currently commonly used anti-elastic ceramic materials. The material of the elastic facing wallboard 2 is Ti6Al4V titanium alloy, the thickness is 1.5mm, and the density is 4.43 g/cm 3 . Sandwich layer 3 of carbon honeycombThe material is a T700 carbon fiber reinforced composite material, the fiber directions are all towards the outside of the surface, the inner diameter 22 of a carbon honeycomb hole is 6mm, the thickness 23 of a carbon honeycomb Kong Biban is 1mm, the thickness 24 of a carbon honeycomb sandwich layer is 10mm, and the density of the carbon honeycomb sandwich layer 3 is 0.5g/cm 3 . It should be noted that in the simulation model, the carbon honeycomb sandwich layer 3 was equivalently modeled in a homogenized manner, i.e., the detailed structure of the carbon honeycomb sandwich layer 3 was replaced with a homogenized entity but with the same macroscopic mechanical properties, and the effectiveness of the homogenized equivalent modeling was verified in the study of Hou (Wenbin Hou, matrix Shen, kai Jiang, et al study on mechanical properties of carbon fiber honeycomb curved sandwich structure and its application in engine hood, composite Structures,2022 (286), 115302.). The back elastic surface wall plate 4 is made of 7075 aluminum alloy and has a thickness of 1.4mm.
A schematic diagram of a simulation model of the comparative structure is shown in FIG. 5, and the overall length, width and thickness of the comparative structure are 100mm, 100mm and 27mm, respectively. The ceramic face plate 1 and the composite back plate 41 are laminated in the direction of incidence of the armor-piercing bullet 6 and fixed by bonding. The ceramic panel 1 is made of boron carbide and has a thickness of 8mm. The composite backboard 41 consists of an aramid fiber sub-layer 43 and an ultra-high molecular weight polyethylene sub-layer 42, wherein the thickness of the aramid fiber sub-layer 43 is 4mm, and the density is 1.35 g/cm 3 The ultra-high molecular weight polyethylene sublayer 42 has a thickness of 15mm and a density of 1.01 g/cm 3 。
The weight of helicopter armor is typically measured as mass per unit area, i.e., surface density (kg/m 2 ) Measured as a carbon honeycomb structure having an areal density of 40.68 kg/m 2 The areal density of the comparative structure was 40.61kg/m 2 Both structures can be considered to have the same areal density.
In the simulation model of the carbon honeycomb structure and the comparative structure, the armor-piercing bullet 6 was vertically penetrated at a speed of 480 m/s. As shown in fig. 6, the simulation results of the carbon honeycomb structure and the comparative structure show that the carbon fiber honeycomb sandwich back plate 5 is integrally bent, and the deflection of the back elastic surface maximum protrusion 51 is 6.75mm as can be seen from (a) in fig. 6. The spring-facing wall plate 2 had a slight depression 52 in the spring-loaded region, the depression 52 being 0.54mm deep. A debonding layer 53 is present between the elastic facing wall plate 2 and the carbon honeycomb sandwich layer 3. A debonding layer 53 is present between the back spring wall plate 4 and the carbon honeycomb sandwich layer 3. As can be seen in fig. 6 (b), the composite back plate 41 is bent integrally, and the deflection of the back elastic surface maximum protrusion 51 is 10.35mm. The aramid sub-layer 43 is penetrated by the armor-piercing bullet 6 and broken to form a pit 54, and the depth of the pit 54 is 4.49mm. Debonding layers 53 are present within the aramid sub-layer 43, within the ultra-high molecular weight polyethylene sub-layer 42, and between the aramid sub-layer 43 and the ultra-high molecular weight polyethylene sub-layer 42, respectively.
Fig. 7 is a graph of the remaining speed versus time of the half-speed 12.7mm armor-piercing projectile penetration process, and as shown in fig. 7, the remaining speed versus time 62 of the half-speed 12.7mm armor-piercing projectile penetration carbon honeycomb structure is always located below the remaining speed versus time 61 of the half-speed 12.7mm armor-piercing projectile penetration vs. the armor-piercing projectile penetration resistance of the carbon honeycomb structure is greater and the armor-piercing projectile deceleration is more severe. Meanwhile, in the process of penetrating the ceramic panel of the carbon honeycomb structure and the ceramic panel of the comparison structure through the armor-piercing bullet within the range of 0-75 mu s, as the carbon fiber honeycomb sandwich back plate meets the bending rigidity requirement of the structure with smaller mass, the ceramic panel corresponding to the carbon honeycomb structure obtains additional thickness of 2mm compared with the ceramic panel corresponding to the comparison structure under the same surface density, so that the carbon honeycomb structure has stronger bullet resistance. Meanwhile, the carbon fiber honeycomb sandwich back plate has better supporting effect, and the composite back plate with a comparison structure has lower elastic modulus in the incidence direction of the armor-piercing shell due to the inherent characteristics of the fiber reinforced composite material, and when the composite back plate is subjected to local compressive load, larger bending deformation is required to be generated so that the fibers in the composite material bear the weight. Therefore, the composite material backboard is insufficient in support of the ceramic panel of the comparison structure at the initial stage of bullet target contact, the bullet resistance of the comparison structure is reduced, and the slope of the residual speed-time curve of the half-speed 12.7mm armor-piercing bullet penetration comparison structure is lower than that of the residual speed-time curve of the half-speed 12.7mm armor-piercing bullet penetration carbon honeycomb structure on the residual speed-time curve of the half-speed 12.7mm armor-piercing bullet penetration process.
Simulation shows that under the same surface density, compared with the traditional ceramic/composite material composite armor structural unit, the armor structural unit of the armor-piercing helicopter resisting the half-speed of 12.7mm has the advantages of smaller bulge degree of the back surface, higher structural integrity and obviously improved protection capability on the armor-piercing helicopter resisting the half-speed of 12.7 mm. If the aim of realizing complete protection of the armor-piercing bullet with the half speed of 12.7mm is fulfilled, the invention realizes the aim of lightening the whole structure.
The invention provides a novel carbon fiber honeycomb sandwich backboard structure form of a ceramic/composite material composite armor, which starts from an anti-ballistic mechanism of the ceramic/composite material composite armor. In the composite armor, the main function of the back plate is to provide structural support, and the back plate is particularly characterized in that the movement of the anti-bullet ceramic material along the incident direction is limited by higher local support rigidity in the sticking area, so that the performance of the anti-bullet ceramic material is fully exerted, and the impact load of armor piercing bullets is born through integral bending. Therefore, the composite material backboard in the laminated form in the prior art is replaced by the carbon fiber honeycomb sandwich backboard with the face-to-bullet wall board, the carbon honeycomb sandwich layer and the back-bullet wall board, and the local supporting rigidity can be obviously increased under the same weight. In addition, considering that the back plate provides bending-resistant support for the ceramic panel in the anti-flicking process, the carbon fiber honeycomb sandwich back plate provided by the invention adopts metal or fiber reinforced composite materials as the flick facing wall plate and the back flick facing wall plate, the flick facing wall plate and the back flick facing wall plate bear stretching or bending load in the bending process of the back plate, and the carbon honeycomb plate is adopted as the core layer, and the core layer has small contribution to the bending rigidity of the structure, so that weight reduction can be realized on the premise of not obviously sacrificing the bending rigidity of the back plate, and the weight reduction of the whole armor structure is facilitated.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to assist in understanding the methods of the present invention and the core ideas thereof; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (8)
1. The helicopter armor structure for resisting the half-speed armor piercing bullet with the thickness of 12.7mm is characterized by comprising a ceramic panel and a carbon fiber honeycomb sandwich backboard which are sequentially arranged along the incidence direction of the armor piercing bullet;
the ceramic panel is made of anti-bouncing ceramic; the carbon fiber honeycomb sandwich backboard comprises a bullet-facing surface wallboard, a carbon honeycomb sandwich layer and a back bullet-facing surface wallboard which are sequentially arranged along the incidence direction of the armor-piercing bullet; the material of the bullet-facing wall plate and the material of the back bullet-facing wall plate are both metal or fiber reinforced composite materials; the carbon honeycomb sandwich layer is of a honeycomb structure; the carbon honeycomb sandwich layer is made of a carbon fiber reinforced composite material;
the ceramic panel is used for crushing the armor-piercing bullet and reducing the armor-piercing bullet kinetic energy through the abrasion action;
the carbon fiber honeycomb sandwich back plate is used for providing bending support and compression support for the ceramic panel when the armor-piercing bullet penetrates the ceramic panel.
2. The helicopter armor structure resistant to half-rate 12.7mm armor piercing bullet of claim 1 wherein the honeycomb structure is a honeycomb grid structure having an inscribed circle diameter of the honeycomb holes less than the diameter of the armor piercing bullet.
3. The helicopter armor structure resistant to half-rate 12.7mm armor piercing bullet of claim 1 wherein the ceramic panel structure is a monolithic or spliced structure.
4. The helicopter armor structure resistant to half-rate 12.7mm armor piercing of claim 1 wherein said ballistic ceramic is boron carbide, silicon carbide or aluminum oxide.
5. The helicopter armor structure resistant to half-rate 12.7mm armor piercing bullet of claim 1 wherein said metal is a titanium alloy, an aluminum alloy or an armor steel.
6. The helicopter armor structure resistant to half-rate 12.7mm armor piercing of claim 1 wherein said fiber-reinforced composite is an ultra-high molecular weight polyethylene fiber-reinforced composite or an aramid fiber-reinforced composite.
7. The helicopter armor structure resistant to half-rate 12.7mm armor piercing of claim 1 wherein said face wall thickness is greater than said back face wall thickness.
8. The helicopter armor structure resistant to half-rate 12.7mm armor piercing bullet of claim 1 wherein said ceramic face sheet and said carbon fiber honeycomb sandwich back sheet are secured by means of adhesive or bolting.
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| CN202310934237.6A CN116907279A (en) | 2023-07-28 | 2023-07-28 | Helicopter armor structure for resisting half-speed 12.7mm armor piercing bullet |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310934237.6A CN116907279A (en) | 2023-07-28 | 2023-07-28 | Helicopter armor structure for resisting half-speed 12.7mm armor piercing bullet |
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| CN202310934237.6A Pending CN116907279A (en) | 2023-07-28 | 2023-07-28 | Helicopter armor structure for resisting half-speed 12.7mm armor piercing bullet |
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