CN116164607A - Non-inclusive airborne antiknock device - Google Patents
Non-inclusive airborne antiknock device Download PDFInfo
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- CN116164607A CN116164607A CN202211312369.7A CN202211312369A CN116164607A CN 116164607 A CN116164607 A CN 116164607A CN 202211312369 A CN202211312369 A CN 202211312369A CN 116164607 A CN116164607 A CN 116164607A
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- explosion
- layer
- impact end
- antiknock
- aircraft
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- 238000004880 explosion Methods 0.000 claims abstract description 77
- 239000002360 explosive Substances 0.000 claims abstract description 43
- 239000007769 metal material Substances 0.000 claims abstract description 33
- 239000000463 material Substances 0.000 claims abstract description 29
- 230000006378 damage Effects 0.000 claims abstract description 22
- 229920002396 Polyurea Polymers 0.000 claims abstract description 18
- 239000003733 fiber-reinforced composite Substances 0.000 claims abstract description 18
- 239000011248 coating agent Substances 0.000 claims abstract description 16
- 238000000576 coating method Methods 0.000 claims abstract description 16
- 238000010008 shearing Methods 0.000 claims abstract description 14
- 230000035939 shock Effects 0.000 claims abstract description 8
- 238000005507 spraying Methods 0.000 claims abstract description 6
- 238000004026 adhesive bonding Methods 0.000 claims abstract description 4
- 238000004080 punching Methods 0.000 claims description 10
- 239000002184 metal Substances 0.000 claims description 6
- 238000010521 absorption reaction Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 4
- 239000004698 Polyethylene Substances 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- -1 polyethylene Polymers 0.000 claims description 3
- 229920000573 polyethylene Polymers 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 238000000034 method Methods 0.000 description 2
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42D—BLASTING
- F42D5/00—Safety arrangements
- F42D5/04—Rendering explosive charges harmless, e.g. destroying ammunition; Rendering detonation of explosive charges harmless
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42D—BLASTING
- F42D5/00—Safety arrangements
- F42D5/04—Rendering explosive charges harmless, e.g. destroying ammunition; Rendering detonation of explosive charges harmless
- F42D5/045—Detonation-wave absorbing or damping means
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Geophysics And Detection Of Objects (AREA)
Abstract
The invention discloses an unconfined airborne antiknock device, and belongs to the field of civil aviation airborne explosion dangerous goods treatment. The invention mainly comprises a cylindrical anti-explosion container body, an impact end head and a shearing pin. The cylindrical anti-explosion container body is made of three layers of materials, namely an inner layer fiber reinforced composite material is used as a clipping layer for generating shock waves by explosion of explosives, a middle layer high-strength metal material is used as a supporting layer, and an outer layer polyurea coating is used as an anti-explosion layer. The connection between the middle layer high-strength metal material supporting layer and the inner layer fiber reinforced composite material clipping layer adopts glue bonding, and the outer layer polyurea antiknock coating is sprayed on the surface of the middle layer high-strength metal material supporting layer in a spraying mode. After the impact end is inserted into the barrel body, the impact end is fixed through a shear pin. The explosive explodes in the interior of the aircraft, so that the barrel body of the anti-explosion device can be prevented from being exploded under the action of limited explosive, the explosion pressure can be directionally discharged out of the interior of the aircraft, and the damage range of the aircraft fuselage wall plate is reduced as far as possible.
Description
Technical Field
The invention belongs to the field of civil aviation airborne explosion dangerous goods treatment, and relates to an unconfined airborne anti-explosion device.
Background
The manufacturer is required to design a' least risk bomb position (LRBL for short) for an aircraft with the maximum qualified passenger seat volume of more than 60 or total take-off weight of more than 100000 pounds (45359 kilograms), the discovered suspicious devices are placed, and the key structures and the systems of the aircraft can be protected to the greatest extent after explosion through the comprehensive design of the structures and the systems, so that the security level of the civil aircraft is improved.
The importance of an on-board antiknock device can be seen by the above analysis. When dangerous explosives are processed, the requirements of the anti-explosion device are high, on one hand, the anti-explosion container cannot be exploded to cause injury to passengers on an aircraft, and on the other hand, the explosive cannot cause damage to the aircraft body after being exploded in the anti-explosion device. In a case of a high altitude of ten minutes, the aircraft body is easily disassembled once being damaged greatly due to the pressure difference between the inside and the outside of the aircraft.
Disclosure of Invention
The invention mainly aims to provide the non-containing type airborne anti-explosion device, wherein explosives explode in the device, so that the barrel body of the anti-explosion device can be prevented from being exploded under the action of limited explosives, and the personal safety of passengers is prevented from being damaged after the explosion of the anti-explosion device; the explosion pressure can be directionally discharged into the aircraft, the damage range of the wall plate of the aircraft body is reduced as much as possible, and the integral structure of the aircraft body is not damaged.
The invention aims at realizing the following technical scheme:
the invention discloses an unconfined airborne antiknock device which is used for a civil aircraft to eliminate the threat of explosives. The cylindrical anti-explosion container body is made of three layers of materials, namely an innermost fiber reinforced composite material is used as a clipping layer for generating shock waves by explosion of explosives, a middle layer of high-strength metal material is used as a supporting layer, and an outermost polyurea coating is used as an anti-explosion layer. The connection between the middle layer high-strength metal material supporting layer and the inner layer fiber reinforced composite material clipping layer is bonded by adopting a strong glue bonding mode, and the outer layer polyurea antiknock coating is sprayed on the surface of the middle layer high-strength metal material supporting layer by adopting a spraying mode. After the impact end is inserted into the barrel body, the impact end is fixed through a shear pin.
Furthermore, the outer polyurea antiknock coating, the middle high-strength metal material supporting layer and the inner fiber reinforced composite material clipping layer are distributed by adopting a wave impedance matching principle, so that the energy of explosion impact wave can be weakened, and the weight of the antiknock device can be reduced.
Furthermore, the head part of the impact end is an annular blade, the strength of the annular blade is enhanced through heat treatment, and the annular blade type impact end is used for reducing the damage range of explosives to the aircraft panel and reducing the damage to the integral structural strength of the aircraft.
Furthermore, the shear pin is made of a cylindrical metal rod with a notch, and on one hand, the shear pin has a fixing effect on the impact end, on the other hand, when the explosive equivalent is smaller, the shear pin is continuous, the impact end cannot fly out, so that the explosion energy cannot leak, when the explosive equivalent is larger, the shear pin breaks, the impact end can fly out in a directional manner, the aircraft wallboard is broken, the explosion energy is released out of the aircraft in a directional manner, and the influence of the explosion energy on personnel and equipment in the cabin is reduced.
Furthermore, the impact end is embedded in four corresponding holes arranged on the middle layer high-strength metal material supporting layer.
Furthermore, the middle layer high-strength metal material supporting layer is made of a high-strength and high-toughness metal material, and is not limited to a specific metal.
The inner fiber reinforced composite material clipping layer is made of ultra-high strength polyethylene material, has absorption effect on shock waves, and reduces damage of the shock waves to the explosion-proof device.
Further, a handle is welded on the impact end.
Further, the impact end is made of steel metal material.
The invention discloses a working method of an unconfined airborne antiknock device, which comprises the following steps: when the explosive is detected on the aircraft, the explosive is placed into the barrel body of the antiknock device, and then the impact end handle is held by hand to install the explosion-proof device on the barrel body of the antiknock device. After the explosive is exploded in the anti-explosion device, when the explosion equivalent is smaller, the shearing pin is not broken, and the deformation energy absorption of the structure of the anti-explosion device is used for eliminating the damage of the explosive to passengers and a fuselage; when the explosion equivalent is larger, the outer polyurea antiknock coating, the middle layer high-strength metal material supporting layer and the inner fiber reinforced composite material clipping layer weaken the explosion impact wave energy by utilizing wave impedance matching, the shear pin breaks under the action of explosion pressure, the annular blade of the impact end is punched towards the airframe, the airframe wallboard of the aircraft is punched and destroyed under the punching action of the impact end, the airframe wallboard punching block is formed, the impact end and the airframe wallboard punching block punch out of the airframe, thereby directionally releasing the explosion energy, eliminating the damage of the explosive to passengers and the integral structure of the airframe, and the integral structure of the aircraft body can not be destroyed.
The beneficial effects are that:
1. the invention discloses an unconfined type airborne anti-explosion device, which is an unconfined type anti-explosion device for eliminating the threat of explosives for civil aviation airplanes. The thickness of the three layers of materials and the materials are distributed according to the wave impedance matching principle, so that the energy of explosion impact wave can be weakened, and the weight of the antiknock device can be lightened. When the explosion equivalent is smaller, the shearing pin of the device is not broken, the anti-explosion device absorbs energy through the deformation of the structure and the material of the anti-explosion device, the damage of the explosive to passengers and the fuselage is eliminated, when the explosion equivalent is larger, the shearing pin breaks under the action of the explosion pressure, and the impact end is punched out of the fuselage, so that the explosion energy is released directionally, and the damage of the explosive to the whole structures of the passengers and the fuselage is eliminated.
2. The invention discloses an unconfined type airborne antiknock device, which is characterized in that a shearing pin is made of a cylindrical metal rod with a notch, the shearing pin is used for fixing an impact end on one hand, the impact end cannot fly off when the explosive equivalent is small, so that explosion energy cannot leak, the shearing pin breaks when the explosive equivalent is large, the impact end can fly off directionally to break through an aircraft wallboard, the explosion energy is released out of an aircraft directionally, and the influence of the explosion energy on personnel and equipment in an engine room is reduced.
3. The invention discloses an unconfined type airborne antiknock device, wherein the head part of an impact end is an annular blade, the strength of the annular blade is enhanced through heat treatment, and the annular blade type impact end is used for reducing the damage range of explosives to an aircraft panel and reducing the damage to the integral structural strength of an aircraft.
Drawings
Figure 1 is an exploded view of the antiknock device of the present invention.
Figure 2 is an isometric view of an antiknock device mount of the present invention.
Figure 3 is a schematic diagram of the operation of the antiknock device of the present invention.
Fig. 4 is a front view of the antiknock device of the present invention after assembly.
Fig. 5 is an assembled left side view of the antiknock device of the present invention.
Figure 6 is a cross-sectional view of the antiknock device of the present invention after assembly.
Wherein: 1-outer polyurea antiknock coating, 2-middle high-strength metal material supporting layer, 3-inner fiber reinforced composite material clipping layer, 4-shear pin, 5-impact end, 6-impact end handle, 7-aircraft fuselage panel, 8-aircraft fuselage panel reinforcement, 9-aircraft fuselage panel punching block and 10-explosive.
Detailed Description
For a better description of the objects and advantages of the present invention, the following description will be given with reference to the accompanying drawings and examples.
Example 1:
as shown in fig. 1, 2, 4 and 5, the embodiment discloses an unconfined antiknock device for removing the threat of explosives for a civil aircraft, wherein the antiknock device consists of a cylindrical antiknock container barrel body, an impact end 5 and a shear pin 4. The cylindrical anti-explosion container body is made of three layers of materials, namely an innermost fiber reinforced composite material is used as a clipping layer 3 for generating shock waves by explosion of explosives, a middle layer of high-strength metal material is used as a supporting layer 2, and an outermost polyurea coating is used as an anti-explosion layer 1. The connection between the middle layer high-strength metal material supporting layer 2 and the inner layer fiber reinforced composite material clipping layer 3 is bonded by adopting a strong glue bonding mode, and the outer layer polyurea antiknock coating 1 is sprayed on the surface of the middle layer high-strength metal material supporting layer 2 by adopting a spraying mode. The outer polyurea antiknock coating 1, the middle high-strength metal material supporting layer 2 and the inner fiber reinforced composite material clipping layer 3 are distributed by adopting a wave impedance matching principle, so that the energy of explosion impact wave can be weakened, and the weight of the antiknock device can be reduced. The intermediate layer high strength metal material support layer 2 is integrally formed from a high strength high toughness metal material. The thickness of the high-strength metal material supporting layer 2 is 10 mm-20 mm. The yield strength of the high-strength high-toughness metal is more than 800MPa, and the fracture toughness is more than 60 MPa.m. The inner fiber reinforced composite material clipping layer 1 is made of ultra-high strength polyethylene. The outer polyurea antiknock coating 3 is formed by spraying a polyurea material on the outer side of the middle layer high-strength metal material supporting layer. The spraying thickness of the polyurea material is 1 mm-3 mm. The head of the impact end 5 is an annular blade, the strength of the annular blade is enhanced through heat treatment, and the annular blade type impact end is used for reducing the damage range of explosives to the aircraft panel and reducing the damage to the integral structural strength of the aircraft. The impact end 5 is embedded in four corresponding holes formed in the middle layer high-strength metal material supporting layer 2. After the impact end 5 is inserted into the barrel body, the impact end is fixed by a shear pin 4. The impact end 5 is made of steel metal material. The shear pin 4 is made of a cylindrical metal rod with a notch, and on one hand, the shear pin has a fixing effect on the impact end, on the other hand, when the explosive equivalent is smaller, the shear pin is continuous, the impact end 5 cannot fly out, so that the explosion energy cannot leak, when the explosive equivalent is larger, the shear pin 4 breaks, the impact end 5 flies out in a directional manner, the aircraft wallboard is broken, the explosion energy is released out of the aircraft in a directional manner, and the influence of the explosion energy on personnel and equipment in the cabin is reduced. The impact end 5 is welded with a handle 6.
As shown in fig. 3, the working method of the non-containment type airborne antiknock device disclosed by the invention is as follows: when an explosive 10 is detected on the aircraft, the explosive 10 is placed inside the body of the antiknock device and then the impact head handle 6 is held by hand to mount it on the body of the antiknock device. When the explosive 10 explodes in the anti-explosion device, the shear pin 4 is not broken when the explosion equivalent is smaller, and the damage of the explosive to passengers and a fuselage is eliminated by the deformation energy absorption of the structure of the anti-explosion device; when the explosion equivalent is larger, the outer polyurea anti-explosion coating 1, the middle layer high-strength metal material supporting layer 2 and the inner fiber reinforced composite material clipping layer 3 weaken the explosion impact wave energy by utilizing wave impedance matching, the shearing pin 4 breaks under the action of explosion pressure, and the section view of the anti-explosion device in combination with fig. 5 can show that the annular blade of the impact end 5 is punched towards the airframe, the airframe wall plate 7 is punched and destroyed under the punching action of the impact end 5 to form an impact airframe wall plate punching block 9, the impact end 5 and the impact airframe wall plate punching block 9 are punched out of the exterior of the airframe, so that the explosion energy is directionally released, the damage of the explosion to passengers and the integral structure of the airframe is eliminated, and the integral structure of the airframe is not destroyed.
While the foregoing is directed to embodiments of the present invention, other and further embodiments of the invention may be devised without departing from the basic scope thereof, and the scope thereof is determined by the claims that follow.
Claims (8)
1. An unconfined airborne antiknock device is characterized in that: the non-containing type anti-explosion device for eliminating the threat of explosives for the civil aircraft mainly comprises a cylindrical anti-explosion container body, an impact end (5) and a shear pin (4); the cylindrical anti-explosion container body is made of three layers of materials, namely an innermost fiber reinforced composite material is used as a clipping layer (3) for generating shock waves by explosion of explosives, a middle layer of high-strength metal material is used as a supporting layer (2), and an outermost polyurea coating is used as an anti-explosion layer (1); the connection between the middle layer high-strength metal material supporting layer (2) and the inner layer fiber reinforced composite material clipping layer (3) is bonded by adopting a strong glue bonding mode, and the outer layer polyurea antiknock coating (1) is sprayed on the surface of the middle layer high-strength metal material supporting layer (2) by adopting a spraying mode; after the impact end (5) is inserted into the barrel body, the impact end is fixed by a shear pin (4).
2. An unconfined airborne antiknock device according to claim 1, wherein: the outer polyurea antiknock coating (1), the middle high-strength metal material supporting layer (2) and the inner fiber reinforced composite material clipping layer (3) are distributed by adopting a wave impedance matching principle, so that the energy of explosion impact wave can be weakened, and the weight of the antiknock device can be reduced.
3. An unconfined airborne antiknock device according to claim 2, wherein: the head of the impact end head (5) is an annular blade type, the strength of the annular blade is enhanced through heat treatment, and the annular blade type impact end head is used for reducing the damage range of explosive to the aircraft panel and reducing the damage to the integral structural strength of the aircraft.
4. A non-contained airborne antiknock device according to claim 3, wherein: the shearing pin (4) is made of a cylindrical metal rod with a notch, on one hand, the shearing pin is fixed to the impact end, on the other hand, when the explosive equivalent is smaller, the shearing pin is continuous, the impact end (5) cannot fly out, so that explosion energy cannot leak, when the explosive equivalent is larger, the shearing pin (4) is broken, the impact end (5) flies out in a directional manner, the aircraft wallboard is broken, the explosion energy is released out of the aircraft in a directional manner, and the influence of the explosion energy on personnel and equipment in the cabin is reduced.
5. An unconfined airborne antiknock apparatus as in claim 4, wherein: the impact end head (5) is embedded in four corresponding holes formed in the middle layer high-strength metal material supporting layer (2).
6. An unconfined airborne antiknock apparatus as in claim 5, wherein: the impact end (5) is welded with a handle (6).
7. An unconfined airborne antiknock apparatus as in claim 6, wherein: the middle layer high-strength metal material supporting layer (2) is made of a high-strength and high-toughness metal material;
the inner fiber reinforced composite material clipping layer (3) is made of ultra-high strength polyethylene material, has absorption effect on shock waves, and reduces the damage of the shock waves to the explosion-proof device;
the impact end head (5) is made of steel metal material.
8. An unconfined airborne antiknock apparatus as in claims 2, 3, 4, 5, 6 or 7 wherein: when the explosive (10) is detected on the aircraft, the explosive (10) is placed into the barrel body of the antiknock device, and then the impact end handle (6) is held by hand to be installed on the barrel body of the antiknock device; after the explosive (10) explodes in the anti-explosion device, when the explosion equivalent is smaller, the shearing pin (4) is not broken, and the damage of the explosive to passengers and the fuselage is eliminated by deforming the structure of the anti-explosion device to absorb energy; when the explosion equivalent is larger, the outer polyurea antiknock coating (1), the middle layer high-strength metal material supporting layer (2) and the inner fiber reinforced composite material clipping layer (3) weaken explosion impact wave energy by utilizing wave impedance matching, the shearing pin (4) breaks under the action of explosion pressure, the impact end (5) is punched towards the airframe, the aircraft airframe wallboard (7) is punched and destroyed under the punching action of the impact end (5) to form an aircraft airframe wallboard punching block (9), the impact end (5) and the aircraft airframe wallboard punching block (9) are punched out of the airframe, so that the explosion energy is directionally released, the damage of the explosives to passengers and the integral structure of the airframe is eliminated, and the integral structure of the aircraft airframe cannot be destroyed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211312369.7A CN116164607B (en) | 2022-10-25 | 2022-10-25 | Non-inclusive airborne antiknock device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211312369.7A CN116164607B (en) | 2022-10-25 | 2022-10-25 | Non-inclusive airborne antiknock device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116164607A true CN116164607A (en) | 2023-05-26 |
| CN116164607B CN116164607B (en) | 2024-08-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211312369.7A Active CN116164607B (en) | 2022-10-25 | 2022-10-25 | Non-inclusive airborne antiknock device |
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| CN114719703A (en) * | 2022-03-31 | 2022-07-08 | 北京理工大学 | Rigid-flexible composite structure airtight explosion-proof device |
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2022
- 2022-10-25 CN CN202211312369.7A patent/CN116164607B/en active Active
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| US20060086735A1 (en) * | 2004-10-21 | 2006-04-27 | Weerth D E | Lightweight spherical blast resistant container |
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| CN116164607B (en) | 2024-08-09 |
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