CN114084358A - Bird collision resisting structure of airplane - Google Patents
Bird collision resisting structure of airplane Download PDFInfo
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- CN114084358A CN114084358A CN202111622157.4A CN202111622157A CN114084358A CN 114084358 A CN114084358 A CN 114084358A CN 202111622157 A CN202111622157 A CN 202111622157A CN 114084358 A CN114084358 A CN 114084358A
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- Prior art keywords
- plate
- aluminum alloy
- end frame
- aluminum
- composition board
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Links
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 41
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 41
- 229910000838 Al alloy Inorganic materials 0.000 claims description 58
- 229920002379 silicone rubber Polymers 0.000 claims description 12
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 239000003292 glue Substances 0.000 claims description 3
- 238000010276 construction Methods 0.000 claims 6
- 239000000203 mixture Substances 0.000 abstract description 29
- 230000000694 effects Effects 0.000 abstract description 13
- 239000004411 aluminium Substances 0.000 abstract description 7
- 239000002131 composite material Substances 0.000 description 19
- 239000000853 adhesive Substances 0.000 description 5
- 230000001070 adhesive effect Effects 0.000 description 5
- 239000004945 silicone rubber Substances 0.000 description 5
- 230000002265 prevention Effects 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- 241001465754 Metazoa Species 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000002633 protecting effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0095—Devices specially adapted to avoid bird strike
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Dampers (AREA)
- Laminated Bodies (AREA)
Abstract
The utility model belongs to aircraft body design field, for an anti bird of aircraft hits structure, through setting up multiunit upper composition board and lower floor's composition board, the upper composition board received the impact earlier when the bird hits, then just reachs front end frame web through lower floor's composition board, the first aluminium honeycomb panel of upper composition board and the second aluminium honeycomb panel of lower floor's composition board all have stronger energy-absorbing and cushioning effect, effectively improve the aircraft by the anterior anti bird of protection architecture and hit the performance, two-layer composition board structure can support each other simultaneously, stable in structure, play effectual guard action to system equipment, through pasting the setting with upper composition board and system equipment mutually, guarantee that the upper composition board can adopt the area as big as possible, in order to guarantee more effectual guard effect.
Description
Technical Field
The application belongs to the field of aircraft body design, and particularly relates to an anti-bird-collision structure of an aircraft.
Background
The bird collision accident is an accident caused by collision between flying birds and aircrafts such as airplanes flying in the air. With the rapid development of the aviation industry, bird strike accidents of airplanes become one of the most serious security threats for aviation flight. United states aviation reports show that 89727 reports of civil aviation were not successful in the event of collision between animals and civil aircraft between 1990 and 2008, with 97.4% of the accidents being caused by flying birds. The data shows that the windward side of the aircraft, including the aircraft windshield, radome, engine, etc., is the most vulnerable location to bird strikes.
The back part of the nose front end frame is the position of a pilot, and the bird collision prevention effect of the nose front end frame directly influences the life safety of the pilot of the airplane and the flight safety of the airplane. At present, bird collision prevention structures are arranged in front of a nose front end frame of most airplanes, and a structural scheme of honeycomb sandwich composite materials is adopted and is arranged in front of the nose front end frame. Through bird collision test, the honeycomb sandwich structure is greatly deformed, part of the structure is punched through, and the bird body continuously collides the front end frame of the machine head after penetrating, so that part of parts are cracked and deformed, and the bird collision resistance effect is not ideal.
Therefore, how to improve the bird strike resistance of the machine body is a problem to be solved.
Disclosure of Invention
The application aims to provide an anti-bird-collision structure of an airplane, and the problem that an effective anti-bird-collision effect is difficult to achieve by adopting a honeycomb sandwich composite material in the prior art is solved.
The technical scheme of the application is as follows: an anti-bird-impact structure of an airplane comprises an upper-layer combination board and a lower-layer combination board, wherein the lower-layer combination board is arranged between the upper-layer combination board and a front-end frame web plate of the airplane, the upper-layer combination board comprises a first aluminum honeycomb panel, the upper-layer combination board comprises multiple groups and is attached to system equipment on the front-end frame web plate, the lower-layer combination board comprises a second aluminum honeycomb panel, the lower-layer combination board comprises multiple groups and is provided with multiple rows along the front-end frame web plate, and at least one group of lower-layer combination board is arranged in each row; the lower-layer combination board is fixedly connected with the front-end frame web in a non-detachable mode, and the upper-layer combination board is fixedly connected with the front-end frame web in a detachable mode.
Preferably, the upper assembling plate further comprises a first aluminum alloy sheet and a second aluminum alloy sheet, the first aluminum alloy sheet and the second aluminum alloy sheet are both bonded with the first aluminum honeycomb plate through structural glue, and the first aluminum alloy sheet and the second aluminum alloy sheet are respectively arranged on the upper side and the lower side of the first aluminum honeycomb plate.
Preferably, the thickness of the first aluminum alloy thin plate is 1-2mm, the thickness of the first aluminum honeycomb plate is 25-35mm, and the thickness of the second aluminum alloy thin plate is 1-2 mm.
Preferably, be equipped with the inserts on the upper strata assembled sheet, be equipped with the support frame between second aluminum alloy sheet metal and the front end frame web, the height of support frame is highly unanimous with second aluminum honeycomb panel, be connected with the bolt between support frame, front end frame web and the inserts.
Preferably, the lower-layer composite board further comprises a third aluminum alloy thin plate arranged on the upper portion of the second aluminum honeycomb plate, a silicon rubber plate arranged on the upper portion of the third aluminum alloy thin plate and a fourth aluminum alloy thin plate arranged on the lower portion of the second aluminum honeycomb plate, the silicon rubber plate is attached to the upper-layer composite board, the lower-layer composite board is provided with three rows, and each group of the fourth aluminum alloy thin plates is connected with the front-end frame web plate through structural adhesive.
Preferably, the thickness of the silicon rubber plate is 3-5mm, the thickness of the third aluminum alloy thin plate and the fourth aluminum alloy thin plate is 1-2mm, and the thickness of the second aluminum honeycomb plate is 25-35 mm.
Preferably, the inserts are arranged on the side of the lower combined plate, and part of the inserts are tightly attached to the side wall of the lower combined plate.
The utility model provides an anti bird of aircraft hits structure, through setting up multiunit upper composition board and lower floor's composition board, the upper composition board receives the impact earlier when the bird hits, then just reachs front end frame web through lower floor's composition board, the first aluminium honeycomb panel of upper composition board and the second aluminium honeycomb panel of lower floor's composition board all have stronger energy-absorbing and cushioning effect, effectively improve the aircraft by the anterior anti bird of protective structure and hit the performance, two-layer composition board structure can support each other simultaneously, stable in structure, play effectual guard action to system's equipment, through pasting the setting with upper composition board and system's equipment mutually, guarantee that the upper composition board can adopt the area as big as possible, in order to guarantee more effectual protection effect.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic view of the connection structure of the upper assembly and the front end frame web of the present application;
FIG. 2 is a view of the connection structure of the lower assembly and the front end frame web of the present application;
FIG. 3 is a schematic structural view of a superstructure of the present application;
fig. 4 is a schematic structural diagram of a lower assembly of the present application.
In the figure, 1, a first aluminum honeycomb panel; 2. a first aluminum alloy sheet; 3. a second aluminum alloy sheet; 4. a second aluminum honeycomb panel; 5. a third aluminum alloy sheet; 6. a fourth aluminum alloy sheet; 7. a silicone rubber sheet; 8. an insert; 9. a support frame; 10. a front end frame web; 11. and (4) system equipment.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
An aircraft bird-impact-resistant structure is shown in fig. 1 and 2 and comprises an upper layer composite board and a lower layer composite board, wherein the lower layer composite board is arranged between the upper layer composite board and a front end frame web 10 of an aircraft, the upper layer composite board comprises a first aluminum honeycomb panel 1, the upper layer composite board comprises multiple groups and is attached to system equipment 11 on the front end frame web 10, the lower layer composite board comprises a second aluminum honeycomb panel 4, the lower layer composite board comprises multiple groups and is provided with multiple rows along the front end frame web 10, and at least one group is arranged on each row of lower layer composite board; the lower-layer composite board is fixedly connected with the front-end frame web 10 in an undetachable manner, and the upper-layer composite board is fixedly connected with the front-end frame web 10 in a detachable manner.
Through setting up multiunit upper composition board and lower floor's composition board, the upper composition board receives the impact earlier when the bird hits, then just reach front end frame web 10 through lower floor's composition board, the first aluminium honeycomb panel 1 of upper composition board and the second aluminium honeycomb panel 4 of lower floor's composition board all have stronger energy-absorbing and cushioning effect, effectively improve the aircraft by the anterior anti bird of protective structure and hit the performance, two-layer composition board structure can the mutual support simultaneously, stable in structure, play effectual guard action to system equipment 11, through pasting the setting with upper composition board and system equipment 11 mutually, guarantee that the upper composition board can adopt the area as big as possible, in order to guarantee more effective protecting effect.
Simultaneously through adopting aluminium honeycomb panel to carry out anti bird to hit the protection to front end frame web 10, honeycomb holes can play effectual subtract heavy effect, can dismantle fixed connection in order to guarantee that upper strata compoboard and lower floor's compoboard homoenergetic carry out convenient ann and tear open and maintain through with upper strata compoboard and front end frame web 10.
As shown in fig. 3, preferably, the upper combination plate further includes a first aluminum alloy thin plate 2 and a second aluminum alloy thin plate 3, the first aluminum alloy thin plate 2 and the second aluminum alloy thin plate 3 are both bonded to the first aluminum honeycomb panel 1 by structural adhesive, and the first aluminum alloy thin plate 2 and the second aluminum alloy thin plate 3 are respectively disposed on the upper side and the lower side of the first aluminum honeycomb panel 1. Through setting up first aluminum alloy sheet 2 and second aluminum alloy sheet 3, when playing the energy-absorbing effect, play support, protection and honeycomb holes's enclosed action to first aluminum honeycomb panel 1.
Preferably, the thickness of the first aluminum alloy sheet 2 is 1-2mm, the thickness of the first aluminum honeycomb panel 1 is 25-35mm, and the thickness of the second aluminum alloy sheet 3 is 1-2mm, and the upper-layer combined plate is ensured to have a sufficiently strong energy absorbing effect by setting the thickness of the first aluminum honeycomb panel 1 to be large.
Preferably, the second aluminum alloy sheet 3 is provided with an insert 8, a support frame 9 is arranged between the second aluminum alloy sheet 3 and the front end frame web 10, the height of the support frame 9 is consistent with that of the second aluminum honeycomb panel 4, and bolts are connected among the support frame 9, the front end frame web 10 and the insert 8. Insert 8 is equipped with the multiunit on second aluminum alloy sheet metal 3, and insert 8 can be stably cooperated with the bolt, and insert 8's thickness can be greater than second aluminum alloy sheet metal 3's thickness to guarantee that bolt and upper assembling plate can be stable fixed.
As shown in fig. 4, preferably, the lower-layer composite board further includes a third aluminum alloy thin plate 5 disposed on the upper portion of the second aluminum honeycomb plate 4, a silicone rubber plate 7 disposed on the upper portion of the third aluminum alloy thin plate 5, and a fourth aluminum alloy thin plate 6 disposed on the lower portion of the second aluminum honeycomb plate 4, the third aluminum alloy thin plate 5 and the fourth aluminum alloy thin plate 6 are connected to the second aluminum honeycomb plate through structural adhesive, the silicone rubber plate 7 is connected to the third aluminum alloy thin plate 5 through structural adhesive, the silicone rubber plate 7 is attached to the upper-layer composite board, the lower-layer composite board has three rows, and each group of the fourth aluminum alloy thin plates 6 is connected to the front-end frame web 10 through structural adhesive. Through setting up third aluminum alloy sheet 5 and fourth aluminum alloy sheet 6, when playing the energy-absorbing effect, play support, protection and honeycomb holes's enclosed action to second aluminum honeycomb panel 4. The silicon rubber plate 7 is arranged to play an effective role in buffering and absorbing shock of the impact on the first combined plate.
Preferably, the silicone rubber sheet 7 has a thickness of 3-5mm, the third and fourth aluminum alloy sheets 5, 6 have a thickness of 1-2mm, and the second aluminum honeycomb panel 4 has a thickness of 25-35 mm. The upper layer assembling plate is ensured to have a strong enough energy absorption effect by setting the second aluminum honeycomb plate 4 to a larger thickness.
Preferably, there are multiple sets of the inserts 8 and the inserts 8 are disposed on the side of the lower composition board, and part of the inserts 8 are closely attached to the side wall of the lower composition board. The lower combined plate is limited and fixed by arranging the partial inserts 8 to be tightly attached to the lower combined plate.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. An anti-bird strike structure of an aircraft, characterized in that: the combined plate comprises an upper combined plate and a lower combined plate, wherein the lower combined plate is arranged between the upper combined plate and a front end frame web plate (10) of an airplane, the upper combined plate comprises a first aluminum honeycomb plate (1), the upper combined plate comprises multiple groups and is attached to system equipment (11) on the front end frame web plate (10), the lower combined plate comprises a second aluminum honeycomb plate (4), the lower combined plate comprises multiple groups and is provided with multiple rows along the front end frame web plate (10), and at least one group of lower combined plate is arranged in each row; the lower-layer combination board is fixedly connected with the front-end frame web (10) in a non-detachable mode, and the upper-layer combination board is fixedly connected with the front-end frame web (10) in a detachable mode.
2. An aircraft bird strike resistant construction as claimed in claim 1, wherein: the upper combination plate further comprises a first aluminum alloy sheet (2) and a second aluminum alloy sheet (3), the first aluminum alloy sheet (2) and the second aluminum alloy sheet (3) are bonded with the first aluminum honeycomb plate (1) through structural glue, and the first aluminum alloy sheet (2) and the second aluminum alloy sheet (3) are respectively arranged on the upper side and the lower side of the first aluminum honeycomb plate (1).
3. An aircraft bird strike resistant construction according to claim 2, wherein: the thickness of the first aluminum alloy thin plate (2) is 1-2mm, the thickness of the first aluminum honeycomb plate (1) is 25-35mm, and the thickness of the second aluminum alloy thin plate (3) is 1-2 mm.
4. An aircraft bird strike resistant construction according to claim 2, wherein: be equipped with on the upper strata assembled sheet mosaic piece (8), be equipped with support frame (9) between second aluminum alloy sheet metal (3) and front end frame web (10), the highly uniform of the height and second aluminum honeycomb panel (4) of support frame (9), be connected with the bolt between support frame (9), front end frame web (10) and mosaic piece (8).
5. An aircraft bird strike resistant construction according to claim 2, wherein: the lower-layer combined plate further comprises a third aluminum alloy thin plate (5) arranged on the upper portion of the second aluminum honeycomb plate (4), a silicon rubber plate (7) arranged on the upper portion of the third aluminum alloy thin plate (5) and a fourth aluminum alloy thin plate (6) arranged on the lower portion of the second aluminum honeycomb plate (4), the silicon rubber plate (7) is attached to the upper-layer combined plate, the lower-layer combined plate is provided with three rows, and each group of fourth aluminum alloy thin plates (6) is connected with the front-end frame web (10) through structural glue.
6. An aircraft bird strike resistant construction according to claim 5, wherein: the thickness of the silicon rubber plate (7) is 3-5mm, the thickness of the third aluminum alloy thin plate (5) and the thickness of the fourth aluminum alloy thin plate (6) are 1-2mm, and the thickness of the second aluminum honeycomb plate (4) is 25-35 mm.
7. An aircraft bird strike resistant construction according to claim 5, wherein: the side of lower floor's compoboard is located in total multiunit and inserts (8) of inserts (8) and inserts (8), and partial inserts (8) are closely laminated with the lateral wall of lower floor's compoboard.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111622157.4A CN114084358A (en) | 2021-12-28 | 2021-12-28 | Bird collision resisting structure of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111622157.4A CN114084358A (en) | 2021-12-28 | 2021-12-28 | Bird collision resisting structure of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114084358A true CN114084358A (en) | 2022-02-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111622157.4A Pending CN114084358A (en) | 2021-12-28 | 2021-12-28 | Bird collision resisting structure of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114084358A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH074460A (en) * | 1993-06-14 | 1995-01-10 | Fuji Seiki Co Ltd | Absorber |
| CN102080439A (en) * | 2010-12-25 | 2011-06-01 | 沈阳飞机工业（集团）有限公司 | Composite honeycomb sandwich structure floor |
| CN201971150U (en) * | 2010-11-18 | 2011-09-14 | 西北工业大学 | Aircraft tailplane with front edge reinforced element |
| CN204527608U (en) * | 2015-03-13 | 2015-08-05 | 哈尔滨飞机工业集团有限责任公司 | A kind of anti-bird hits energy-absorbing sandwich structure |
| CN108099281A (en) * | 2017-12-27 | 2018-06-01 | 山东非金属材料研究所 | A kind of plane nose hits baffle with the anti-bird of composite material |
-
2021
- 2021-12-28 CN CN202111622157.4A patent/CN114084358A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH074460A (en) * | 1993-06-14 | 1995-01-10 | Fuji Seiki Co Ltd | Absorber |
| CN201971150U (en) * | 2010-11-18 | 2011-09-14 | 西北工业大学 | Aircraft tailplane with front edge reinforced element |
| CN102080439A (en) * | 2010-12-25 | 2011-06-01 | 沈阳飞机工业（集团）有限公司 | Composite honeycomb sandwich structure floor |
| CN204527608U (en) * | 2015-03-13 | 2015-08-05 | 哈尔滨飞机工业集团有限责任公司 | A kind of anti-bird hits energy-absorbing sandwich structure |
| CN108099281A (en) * | 2017-12-27 | 2018-06-01 | 山东非金属材料研究所 | A kind of plane nose hits baffle with the anti-bird of composite material |
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