Fireproof heat insulation liner for realizing miniaturization of fragments after crushing

Abstract

The invention discloses a fireproof heat-insulation liner for realizing miniaturization of fragments after crushing, belongs to the technical field of missile launching and protection, and aims to solve the problem that an existing fireproof heat-insulation liner forms large-size fragments with hard texture and damages an aircraft skin. Comprising a strength layer, two surface layers, two adhesive films and a core layer which are the same in outline, the strength layer, the surface layers, the adhesive films, the core layer, the adhesive films and the surface layers are sequentially aligned and stacked, a plurality of launching holes are formed in the strength layer and matched and aligned with a plurality of missiles one by one, a plurality of hole sets are formed in the core layer, and each hole set is composed of a plurality of small holes. The plurality of small holes of each hole group are uniformly distributed in a circular area, the plurality of circular areas are matched and aligned with the plurality of missiles one by one, the strength layer and the adjacent surface layer are cured into a whole through an autoclave, and the surface layer is connected with the core layer through an adhesive film in an adhesive manner. As a large number of small holes are formed in the core layer, the size of generated fragments can be effectively reduced, and damage caused by collision of the fragments generated after the fireproof heat-insulation liner is broken to an airplane is effectively reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of missile launching and protection, and in particular relates to a fireproof and heat-insulating pad that can miniaturize fragments after being broken. Background Art

[0002] When a fighter jet is equipped with a multi-link missile launcher, it can carry multiple missiles, greatly improving its strike capability. However, for multi-link missiles, the missiles are not launched at the same time, and there are differences in the launch time. Therefore, it is necessary to set a fireproof and heat-insulating pad in the missile launcher to block the unlaunched missiles and the flames ejected when the missiles are launched. After the missile is launched, the area corresponding to the fireproof and heat-insulating pad is broken and formed into fragments, which are ejected from the missile launcher together with the missile. Since a huge impact force is also generated when the missile is launched, the fireproof and heat-insulating pad must meet certain rigidity and strength requirements in addition to meeting the fireproof and heat-insulating requirements. After the rigidity and strength of the fireproof and heat-insulating pad are improved, the fragments generated after the missile is launched are not only large in size but also hard in texture. Once they collide with the aircraft skin, the aircraft surface will be damaged. Summary of the invention

[0003] The purpose of the present invention is to provide a fireproof and heat-insulating pad that can miniaturize fragments after being broken, so as to solve the problem that the existing fireproof and heat-insulating pad forms large-sized fragments with hard texture after missile launch, which damages the aircraft skin. The technical solution adopted by the present invention is as follows:

[0004] A fireproof and heat-insulating pad for miniaturizing fragments after crushing, wherein the fireproof and heat-insulating pad is installed in a missile launcher of a fighter, wherein the missile launcher comprises a launch tube and a tube front cover, wherein a plurality of missiles are installed on the launch tube, and the fireproof and heat-insulating pad is connected to an interface on a cross section of the tube front cover;

[0005] The fireproof and heat-insulating pad comprises a strength layer with the same contour, two surface layers, two adhesive films and a core layer. The strength layer, a surface layer, a adhesive film, the core layer, another adhesive film and another surface layer are aligned and stacked in sequence. A plurality of launching holes are arranged on the strength layer, and the plurality of launching holes are matched and aligned one by one with a plurality of missiles. A plurality of circular areas are arranged on the core layer, and a plurality of small holes are evenly arranged in the circular areas, and the plurality of circular areas are matched and aligned one by one with a plurality of missiles. The strength layer and the adjacent surface layer are cured into one by an autoclave, and the surface layer and the core layer are bonded together by adhesive films.

[0006] Furthermore, the surface layer is a glass fiber prepreg material component.

[0007] Furthermore, the strength layer is a carbon fiber prepreg material component.

[0008] Furthermore, the core layer is a carbon fiber prepreg material component.

[0009] Furthermore, the strength layer, surface layer, adhesive film and core layer are all circular, and are radially provided with notches extending from the center to one end, and the contours of the strength layer, surface layer, adhesive film and core layer are adapted to the interface.

[0010] Furthermore, two first pin holes symmetrical to the notch are provided on the strength layer, surface layer, film and core layer, and two second pin holes are provided on the end surface of the transmitting tube facing the front cover. The first pin holes on the strength layer, surface layer, film and core layer are aligned with each other and matched with the two second pin holes through positioning pins.

[0011] Compared with the prior art, the present invention has the following beneficial effects:

[0012] When launching a missile, the fireproof and heat-insulating pad will be broken. The core layer is the main structure. Due to the presence of a large number of small holes on the core layer, the size of the generated fragments can be effectively reduced. In addition, the strength layer, surface layer and core layer are all made of special glass fiber materials, and the interlayer adhesion is small. After breaking, the layers are delaminated, reducing the weight and stiffness of the fragments. The above measures can effectively reduce the damage caused by the collision of fragments generated by the fireproof and heat-insulating pad after breaking. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is an exploded schematic diagram of the present invention;

[0014] Figure 2 It is a schematic diagram of the structure of the strength layer;

[0015] Figure 3 It is a schematic diagram of the structure of the surface layer;

[0016] Figure 4 It is a schematic diagram of the structure of the core layer;

[0017] Figure 5 It is a schematic diagram of the installation and decomposition of the present invention and a multiple missile launcher.

[0018] In the figure, 1. strength layer, 2. surface layer, 3. adhesive film, 4. core layer, 5. circular area, 6. launching hole, 7. pin hole, 8. notch, 9. small hole, 10. launching tube, 11. missile, 12. second pin hole, 13. fireproof and heat-insulating pad, 14. front cover of the tube, 15. missile hole. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is described below by the specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.

[0020] The connection mentioned in the present invention is divided into fixed connection and detachable connection. The fixed connection is a non-detachable connection including but not limited to conventional fixed connection methods such as folding connection, rivet connection, bonding connection and welding connection. The detachable connection includes but not limited to conventional detachable methods such as bolt connection, snap connection, pin connection and hinge connection. When the specific connection method is not clearly defined, it is assumed that at least one connection method can be found in the existing connection methods to achieve the function, and those skilled in the art can choose according to their needs. For example: welding connection is selected for fixed connection, and bolt connection is selected for detachable connection.

[0021] The present invention will be further described in detail below in conjunction with the accompanying drawings. The following embodiments are provided to explain the present invention, but the present invention is not limited to the following embodiments.

[0022] Example: Figure 1 to Figure 5 As shown, a fireproof and heat-insulating pad for miniaturizing fragments after crushing, the fireproof and heat-insulating pad 13 is installed in a missile launcher of a fighter, the missile launcher includes a launch tube 10 and a tube front cover 14, a plurality of missiles 11 are installed on the launch tube 10, a plurality of missile holes 15 are provided on the tube front cover 14, and the fireproof and heat-insulating pad 13 is connected to an interface on a cross section of the tube front cover 14;

[0023] The fireproof and heat-insulating pad 13 includes a strength layer 1 with the same contour, two surface layers 2, two adhesive films 3 and a core layer 4. The strength layer 1, one surface layer 2, one adhesive film 3, the core layer 4, another adhesive film 3 and another surface layer 2 are aligned and stacked in sequence. The strength layer 1 is provided with a plurality of launch holes 6, and the plurality of launch holes 6 are aligned one by one with a plurality of missiles 11. The core layer 4 is provided with a plurality of circular areas 5, and a plurality of small holes 9 are evenly arranged in the circular areas 5. The plurality of circular areas 5 are aligned one by one with a plurality of missiles 11. The strength layer 1 and the adjacent surface layer 2 are cured into one by an autoclave, and the surface layer 2 and the core layer 4 are bonded and connected by the adhesive film 3.

[0024] The surface layer 2 is a glass fiber prepreg material component.

[0025] The strength layer 1 is a carbon fiber prepreg material component.

[0026] The core layer 4 is a carbon fiber prepreg material component.

[0027] The strength layer 1, surface layer 2, adhesive film 3 and core layer 4 are all circular, and are radially provided with a notch 8 from the center to one end. The contours of the strength layer 1, surface layer 2, adhesive film 3 and core layer 4 are adapted to the interface, and the adhesive film 3 is consistent with the appearance of the surface layer 2.

[0028] Two first pin holes 7 symmetrical to the notch 8 are provided on the strength layer 1, the surface layer 2, the adhesive film 3 and the core layer 4. Two second pin holes 12 are provided on the end surface of the transmitting tube 10 facing the tube front cover 14. The first pin holes 7 on the strength layer 1, the surface layer 2, the adhesive film 3 and the core layer 4 are aligned with each other and matched with the two second pin holes 12 through positioning pins.

[0029] When the missile 11 is launched, the fireproof and heat-insulating pad 13 is broken, wherein the core layer 4 is the main structure. Since there are a large number of small holes on the core layer 4, the size of the generated fragments can be effectively reduced. In addition, the strength layer 1, the surface layer 2 and the core layer 4 are all made of special glass fiber materials, and the interlayer adhesion is small. After the breakage, the layers are delaminated, which reduces the weight and rigidity of the fragments. The above measures can effectively reduce the damage caused by the collision of the fragments of the fireproof and heat-insulating pad 13 with the aircraft after the breakage.

[0030] The characteristics of each layer are:

[0031] a) The surface layer 2 is a whole layer, made of glass fiber prepreg material, used to isolate the flame ejected when the missile 11 is launched;

[0032] b) The strength layer 1 is dropped at the launch hole 6. The material is carbon fiber prepreg material. It is cured together with the adjacent surface layer 2 through an autoclave. The strength layer 1 of the fireproof and heat-insulating pad 13 faces away from the missile 11 to receive impact and improve strength;

[0033] c) Adhesive film 3 is used to bond the surface layer 2 and the core layer 4;

[0034] d) The core layer 4 is the main structure of the fireproof and heat-insulating pad 13, and the material is glass fiber prepreg material. A number of small holes 9 are arranged in the circular area 5 adapted to the missile 11 to facilitate the formation of small-sized fragments.

[0035] The final fireproof and heat-insulating pad product after each layer is bonded and formed is fixedly connected to the positioning pin on the missile launcher through the first pin hole 7 shared by each layer. During installation, one side of the strength layer 1 faces away from the missile 11. When the missile 11 is launched, the strength layer 1 directly bears the impact of the tail flame of the missile 11.

[0036] The above embodiments are merely exemplary descriptions of the present invention and do not limit its protection scope. Those skilled in the art may also make partial changes thereto, which are within the protection scope of the present invention as long as they do not exceed the spirit of the present invention.

Claims

1. A fireproof and heat-insulating pad for miniaturizing fragments after crushing, wherein the fireproof and heat-insulating pad (13) is installed in a missile launcher of a fighter, wherein the missile launcher comprises a launch tube (10) and a tube front cover (14), wherein a plurality of missiles (11) are installed on the launch tube (10), and the fireproof and heat-insulating pad (13) is connected to an interface on a cross section of the tube front cover (14); Features: The fireproof heat-insulating pad (13) comprises a strength layer (1) with the same profile, two surface layers (2), two adhesive films (3) and a core layer (4); the strength layer (1), one surface layer (2), one adhesive film (3), the core layer (4), another adhesive film (3) and another surface layer (2) are aligned and stacked in sequence; a plurality of launch holes (6) are provided on the strength layer (1); the plurality of launch holes (6) are matched and aligned with a plurality of missiles (11) one by one; a plurality of circular areas (5) are provided on the core layer (4); a plurality of small holes (9) are evenly arranged in the circular areas (5); the plurality of circular areas (5) are matched and aligned with a plurality of missiles (11) one by one; the strength layer (1) and the adjacent surface layer (2) are cured into one by an autoclave; and the surface layer (2) and the core layer (4) are bonded and connected by the adhesive film (3).

2. A fireproof and heat-insulating pad for miniaturizing broken pieces according to claim 1, characterized in that: The surface layer (2) is a glass fiber prepreg material component.

3. The fireproof and heat-insulating pad for miniaturizing the fragments after crushing according to claim 2, characterized in that: The strength layer (1) is a carbon fiber prepreg material component.

4. The fireproof and heat-insulating pad for miniaturizing the fragments after crushing according to claim 3, characterized in that: The core layer (4) is a carbon fiber prepreg material component.

5. A fireproof and heat-insulating pad for miniaturizing crushed fragments according to any one of claims 1 to 4, characterized in that: The strength layer (1), the surface layer (2), the adhesive film (3) and the core layer (4) are all circular and are radially provided with a notch (8) extending from the center to one end. The contours of the strength layer (1), the surface layer (2), the adhesive film (3) and the core layer (4) are adapted to the interface.

6. The fireproof and heat-insulating pad for miniaturizing the fragments after crushing according to claim 5, characterized in that: Two first pin holes (7) symmetrical to the notch (8) are provided on the strength layer (1), the surface layer (2), the adhesive film (3) and the core layer (4); two second pin holes (12) are provided on the end surface of the transmitting tube (10) facing the tube front cover (14); the first pin holes (7) on the strength layer (1), the surface layer (2), the adhesive film (3) and the core layer (4) are aligned with each other and are matched with the two second pin holes (12) through positioning pins.

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