CN201971150U - Aircraft tailplane with front edge reinforced element - Google Patents
Aircraft tailplane with front edge reinforced element Download PDFInfo
- Publication number
- CN201971150U CN201971150U CN2010206179313U CN201020617931U CN201971150U CN 201971150 U CN201971150 U CN 201971150U CN 2010206179313 U CN2010206179313 U CN 2010206179313U CN 201020617931 U CN201020617931 U CN 201020617931U CN 201971150 U CN201971150 U CN 201971150U
- Authority
- CN
- China
- Prior art keywords
- leading edge
- sandwich layer
- honeycomb sandwich
- reinforcing member
- wing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Abstract
The utility model provides an aircraft tailplane with a front edge reinforced element; an upper honeycomb core layer, a lower honeycomb core layer, the front edge reinforced element and an airfoil lining layer are arranged among spans of the front edge of an airfoil along the aircraft tailplane. One angle of the front edge reinforced element is located at the front end of the front edge of the tailplane. The upper honeycomb core layer and the lower honeycomb core layer which are in a parallelogram shape are respectively fixed on upper and lower internal surfaces of a tailplane skin, and the sides of one top angle of each honeycomb core layer are fixed with the surfaces of the front edge reinforced element and the tailplane skin; and the sides of the other top angle are respectively fixed with the surfaces of the tailplane skin and the airfoil lining layer. The honeycomb core layers and the front edge reinforced element are coated between the internal surfaces of the airfoil lining layer and the airplane skin through the airfoil lining layer. An aerial bird body is cut through the front edge reinforced element, and the impact force of the aerial bird body is effectively absorbed through the honeycomb core layers, moreover, the internal structure of the front edge of the tailplane is protected by the airfoil lining layer so as not to be damaged. The aircraft tailplane is also applied to a vertical tail, the front edge of the airfoil and any beam edge positions on the aircraft that can suffer from collision of aerial birds.
Description
Technical field
The present invention relates to civil aircraft structure design field, specifically is a kind of horizontal tail leading edge structure.
Background technology
The bird accident of hitting is meant that the birds of aircraft such as the aircraft of airflight and flight bump against the accident that is taken place.Along with the develop rapidly of civil aviation industry, the civil aircraft bird accident of hitting becomes one of the most serious security threat of civil aviation.Show that according to the relevant report of U.S. United Airlines, Inc in the period of nineteen ninety to 2008, U.S. civil aviaton reports 89727 animals and aircarrier aircraft collision accident altogether, wherein 97.4% cause by flying bird.Relevant data shows that the windward side of aircraft comprises that aircraft windscreen, radome, driving engine, the leading edge of a wing and empennage leading edge are to be vulnerable to the position that bird is hit most.Leading edge structure is inner standing to be had oil piping system or control path, these inner facilities in a single day to be subjected to bird to crash through badly, and catastrophic failure just is difficult to avoid.Therefore, resolving the problem that the anti-bird of aircraft tail leading edge hits performance counts for much.Clearly stipulate in 631 sections of the 25th in " airplane in transportation category airworthiness standard " that CAAC formulates, the aircraft tail structure Design must guarantee at aircraft after bumping against with 3.6 kilograms (8 pounds) bird heavily, still can continue safe flight and landing, the speed of aircraft equals the cruising speed of aircraft on selected sea level during collision.Studies show that under high-speed impact, the bird body surface reveals tangible fluid mechanics behavior.Hit design high-intensity composite material and the simple sandwich constructions of adopting at the anti-bird of empennage leading edge at present more.Its mentality of designing mostly is the function profile of sacrificial structure, absorbs bird body Impact energy with its big as far as possible distortion.As a kind of vertical fin leading edge structure that people such as Alessandro Airoldi mention in pertinent literature, its outside face adopts aluminum alloy materials, and is inner then adopt the carbon fiber composite material of being with cellular sandwich.With 4 pounds the bird body speed impact structures with 270 joints, structural failure is obvious in the test.People such as M.A.McCARTHY then propose the leading edge of a wing structure that a kind of skins front edges is the FML composite material.Structure has been born 4 pounds of bumps that the bird body carries out with the speed of 200m/s in the test, and leading edge is breakdown but produce huge distortion.People such as nearest Michele Guida have proposed a kind of sandwich leading edge structure again, and the sandwich construction two-layer panel adopts FML composite material and metallic material respectively, and sandwich layer is a honeycomb.Bird body with 8 pounds in the process of the test clashes into structure with the speed of 250 joints, and leading edge is not breakdown as a result, but total has produced very big distortion.As can be seen, it is very expensive that existing structure designs its manufacturing cost, total or breakdown, or produce greatly distortion, it is unsatisfactory that its anti-bird is hit effect.
Summary of the invention
Hit structure that the back produces or breakdown for overcoming the bird that exists in the prior art, perhaps produce greatly distortion, and defect of high cost, the present invention proposes a kind of aircraft horizontal tail that the leading edge reinforcing member is arranged.
The present invention includes the horizontal tail covering, go up honeycomb sandwich layer and following honeycomb sandwich layer, leading edge reinforcing member and wing lining, between last honeycomb sandwich layer and following honeycomb sandwich layer, leading edge reinforcing member and wing lining are all respectively striden in being arranged in the leading edge of a wing along the exhibition of aircraft horizontal tail.Among the present invention, the leading edge reinforcing member is tri-prismoid, and an angle of this leading edge reinforcing member is positioned at the front end place of the leading edge of a wing.The last honeycomb sandwich layer of parallelogram and following honeycomb sandwich layer are separately fixed at the inside face up and down of horizontal tail covering, and two limits of last honeycomb sandwich layer and following honeycomb sandwich layer the same side drift angle are fixed with the surface of leading edge reinforcing member and horizontal tail covering respectively, and two limits of the drift angle of last honeycomb sandwich layer and following honeycomb sandwich layer opposite side are fixed with the surface of horizontal tail covering and wing lining respectively.The wing lining is fixed on honeycomb sandwich layer and following honeycomb sandwich layer, and the surface of leading edge reinforcing member, will go up honeycomb sandwich layer, following honeycomb sandwich layer and leading edge reinforcing member and be coated between wing lining and the horizontal tail covering inside face.
There is the groove that cooperates with wing lining front end on a surface of leading edge reinforcing member.The outer profile of wing lining just as leading edge of a wing place.The thickness of last honeycomb sandwich layer and following honeycomb sandwich layer is 5～20mm.The groove on leading edge reinforcing member surface, corresponding with the leading edge reinforcing member with the angle that leading edge of a wing front end cooperates.
The present invention has taken into full account the characteristics that bird is hit problem, and promptly the bird body shows the fluid mechanics behavior in knockout process, by the reinforcing member that is positioned at leading edge the bird body is cut, and the front bump that becomes the bird body is oblique bump, has reasonably discharged the energy that the bird body clashes into.Thin aerofoil surface covering is by deformation failure; and distortion by the honeycomb sandwich layer has effectively absorbed the energy that the bird body is cut apart trailing portion; thicker wing lining has then guaranteed the safety of horizontal tail leading edge inner structure; protection wing lining is not breakdown, thereby protection horizontal tail leading edge inner structure is not damaged.Evidence, by the thickness increase horizontal tail covering of change honeycomb sandwich layer and wing lining and the distance between the wing lining, by the angle of leading edge reinforcing member, the anti-bird that all can effectively change whole leading edge is hit performance, hits requirement to adapt to different anti-birds.
Fig. 7 hits the numerical modelling scheme drawing for bird.The bird body surface is shown the cylinder of two ends hemisphere among the figure, and represents with the SPH particle.Bird physique amount is 3.6kg, and velocity of impact is 150m/s.
Fig. 8 is the cutting procedure of leading edge reinforcing member to bird body 6.Fig. 9 (a) is preceding bird body 6 states of bump beginning.Fig. 9 (b) is bird body 6 states behind the bump beginning 1ms.As can be seen, in knockout process, bird body 6 is obviously cut by leading edge reinforcing member 3.After Fig. 9 (c) is bump beginning 2ms, the state of bird body 6.As can be seen, bird body 6 is skidded off along wing lining 4 upper and lower surfaces respectively by formed two parts of leading edge reinforcing member 3 cuttings.
Fig. 9 is bird body impact scheme drawing to structure after cutting apart.Can see that skins front edges 1 lost efficacy, last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 have very large deformation, and these distortion have absorbed the energy of being cut apart back bird body 6, and wing lining 4 has been played protective effect.
Figure 10-11 stands situation behind the birdstrike for structure.Wing lining 4 has than small deformation as can be seen, and is not punctured by the bird body.
Among the present invention, the honeycomb sandwich layer that increases on the wing horizontal tail, leading edge reinforcing member and wing lining are installed in horizontal tail inside, can not impact the aircraft aeroperformance, and making is simple, cost is low, is applicable to any Liang Yuan position that may suffer bird strike on vertical fin, the leading edge of a wing and the aircraft.
Description of drawings
Fig. 1 is the graphics of horizontal tail leading edge;
Fig. 2 is the structural representation of horizontal tail leading edge;
Fig. 3 is a leading edge reinforcing member scheme drawing;
Fig. 4 is a wing lining scheme drawing;
Fig. 5 is leading edge reinforcing member and inside panel connection diagram;
Fig. 6 is a honeycomb sandwich layer scheme drawing, and wherein (a) is last honeycomb sandwich layer, (b) is following honeycomb sandwich layer;
Fig. 7 hits the numerical modelling scheme drawing for the structure bird;
Fig. 8 be the leading edge reinforcing member to bird body cutting procedure scheme drawing, wherein (a) is bird body state before the bump beginning, (b) is bird body state behind the bump beginning 1ms, (c) is the state of bird body behind the bump beginning 2ms;
Fig. 9 impacts structural representation for the bird body after cutting apart;
Fig. 9 is structure damage situations scheme drawing after bird is hit;
Figure 10 is structure inside panel distortion situation scheme drawing after bird is hit.Wherein:
1. honeycomb sandwich layer 3. leading edge reinforcing members 4. wing linings on the horizontal tail covering 2.
5. descend honeycomb sandwich layer 6. bird bodies
The specific embodiment
Embodiment one
Present embodiment is that the anti-bird that is used for certain type machine knocks machine horizontal tail leading edge away.
As shown in Figure 1, present embodiment comprises horizontal tail covering 1, goes up honeycomb sandwich layer 2 and following honeycomb sandwich layer 5, leading edge reinforcing member 3 and wing lining 4, between last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5, leading edge reinforcing member 3 and wing lining 4 are all respectively striden in being arranged in the leading edge of a wing along the exhibition of aircraft horizontal tail; Wherein, leading edge reinforcing member 3 is tri-prismoid, and an angle of this leading edge reinforcing member is positioned at the front end place of the leading edge of a wing; The inside face up and down that the last honeycomb sandwich layer 2 of parallelogram and following honeycomb sandwich layer 5 are separately fixed at skins front edges 1, and a hypotenuse of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 all cooperates with a side surface of leading edge reinforcing member 3; Wing lining 4 is fixed on honeycomb sandwich layer 2 and following honeycomb sandwich layer 5, and the surface of leading edge reinforcing member 3, will go up honeycomb sandwich layer 2, following honeycomb sandwich layer 5 and leading edge reinforcing member 3 and be coated between wing lining 4 and horizontal tail covering 1 inside face.
The quantity of the last honeycomb sandwich layer 2 in the present embodiment, following honeycomb sandwich layer 5, leading edge reinforcing member 3 and wing lining 4 is all with the quantity of striding in the horizontal tail leading edge inner structure.
Horizontal tail covering 1 is an aluminum alloy, and covering thickness is 0.5 millimeter, with the rib riveted and fixed in the wing.
Leading edge reinforcing member 3 is a tri-prismoid, makes with aluminum alloy materials.An angle of leading edge reinforcing member is positioned at the front end place of the leading edge of a wing, and is connected with rib spot welding.On leading edge reinforcing member 3 and corresponding surface, the angle that cooperates with leading edge of a wing front end, the groove that cooperates with wing lining 4 front ends is arranged, and this groove is connected with the front end spot welding of wing lining.Two surfaces of all the other of leading edge reinforcing member are the plane, and fit with two outside faces of wing lining 4 respectively in aforementioned two surfaces and spot welding is fixed.
Last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 are paper honeycomb structure, its profile parallelogram, and the direction of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 is opposite.The thickness of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 is 15 millimeters.Fit with the leading edge reinforcing member 3 and the surface of horizontal tail covering 1 respectively and be glued fixing in two limits of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 the same side drift angles.Fit with the surface of horizontal tail covering 1 and wing lining 4 respectively and be glued fixing in two limits of the drift angle of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 opposite sides.
The aluminum alloy of wing lining 4 usefulness 5mm is made, and its profile is V-shaped, with the profile at leading edge of a wing place.The groove fit on the front end of this wing lining 4 and leading edge reinforcing member 3 surfaces, the tail end of wing lining 4 is to wing web place.Pass through the gusset plate riveted and fixed between wing lining 4 and the rib.
Embodiment two
Present embodiment is that the anti-bird that is used for certain type machine knocks machine horizontal tail leading edge away.
As shown in Figure 1, present embodiment comprises horizontal tail covering 1, goes up honeycomb sandwich layer 2 and following honeycomb sandwich layer 5, leading edge reinforcing member 3 and wing lining 4, between last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5, leading edge reinforcing member 3 and wing lining 4 are all respectively striden in being arranged in the leading edge of a wing along the exhibition of aircraft horizontal tail; Wherein, leading edge reinforcing member 3 is tri-prismoid, and an angle of this leading edge reinforcing member is positioned at the front end place of the leading edge of a wing; The inside face up and down that the last honeycomb sandwich layer 2 of parallelogram and following honeycomb sandwich layer 5 are separately fixed at skins front edges 1, and a hypotenuse of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 all cooperates with a side surface of leading edge reinforcing member 3; Wing lining 4 is fixed on honeycomb sandwich layer 2 and following honeycomb sandwich layer 5, and the surface of leading edge reinforcing member 3, will go up honeycomb sandwich layer 2, following honeycomb sandwich layer 5 and leading edge reinforcing member 3 and be coated between wing lining 4 and horizontal tail covering 1 inside face.
The quantity of the last honeycomb sandwich layer 2 in the present embodiment, following honeycomb sandwich layer 5, leading edge reinforcing member 3 and wing lining 4 is all with the quantity of striding in the horizontal tail leading edge inner structure.
Horizontal tail covering 1 is an aluminum alloy, and covering thickness is 1 millimeter, with the rib riveted and fixed in the wing.
Leading edge reinforcing member 3 is a tri-prismoid, makes with composite material.An angle of leading edge reinforcing member is positioned at the front end place of the leading edge of a wing, and is connected with rib is glued.On leading edge reinforcing member 3 and corresponding surface, the angle that cooperates with leading edge of a wing front end, the groove that cooperates with wing lining 4 front ends is arranged, and this groove is connected with the front end of wing lining is glued.Two surfaces of all the other of leading edge reinforcing member are the plane, and fit and glued fixing with two outside faces of wing lining 4 respectively in aforementioned two surfaces.
Last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 are paper honeycomb structure, its profile parallelogram, and the direction of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 is opposite.The thickness of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 is 25 millimeters.Fit with the leading edge reinforcing member 3 and the surface of horizontal tail covering 1 respectively and be glued fixing in two limits of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 the same side drift angles.Fit with the surface of horizontal tail covering 1 and wing lining 4 respectively and be glued fixing in two limits of the drift angle of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 opposite sides.
The aluminum alloy of wing lining 4 usefulness 4mm is made, and its profile is V-shaped, with the profile at leading edge of a wing place.The groove fit on the front end of this wing lining 4 and leading edge reinforcing member 3 surfaces, the tail end of wing lining 4 is to wing web place.Pass through the gusset plate riveted and fixed between wing lining 4 and the rib.
Embodiment three
Present embodiment is that the anti-bird that is used for certain type machine knocks machine horizontal tail leading edge away.
As shown in Figure 1, present embodiment comprises horizontal tail covering 1, goes up honeycomb sandwich layer 2 and following honeycomb sandwich layer 5, leading edge reinforcing member 3 and wing lining 4, between last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5, leading edge reinforcing member 3 and wing lining 4 are all respectively striden in being arranged in the leading edge of a wing along the exhibition of aircraft horizontal tail; Wherein, leading edge reinforcing member 3 is tri-prismoid, and an angle of this leading edge reinforcing member is positioned at the front end place of the leading edge of a wing; The inside face up and down that the last honeycomb sandwich layer 2 of parallelogram and following honeycomb sandwich layer 5 are separately fixed at skins front edges 1, and a hypotenuse of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 all cooperates with a side surface of leading edge reinforcing member 3; Wing lining 4 is fixed on honeycomb sandwich layer 2 and following honeycomb sandwich layer 5, and the surface of leading edge reinforcing member 3, will go up honeycomb sandwich layer 2, following honeycomb sandwich layer 5 and leading edge reinforcing member 3 and be coated between wing lining 4 and horizontal tail covering 1 inside face.
The quantity of the last honeycomb sandwich layer 2 in the present embodiment, following honeycomb sandwich layer 5, leading edge reinforcing member 3 and wing lining 4 is all with the quantity of striding in the horizontal tail leading edge inner structure.
Horizontal tail covering 1 is the FLM composite material, and covering thickness is 0.5 millimeter, with the rib riveted and fixed in the wing.
Leading edge reinforcing member 3 is a tri-prismoid, makes with aluminum alloy materials.An angle of leading edge reinforcing member is positioned at the front end place of the leading edge of a wing, and is connected with rib spot welding.On leading edge reinforcing member 3 and corresponding surface, the angle that cooperates with leading edge of a wing front end, the groove that cooperates with wing lining 4 front ends is arranged, and this groove is connected with the front end spot welding of wing lining.Two surfaces of all the other of leading edge reinforcing member are the plane, and fit with two outside faces of wing lining 4 respectively in aforementioned two surfaces and spot welding is fixed.
Last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 are paper honeycomb structure, its profile parallelogram, and the direction of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 is opposite.The thickness of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 is 10 millimeters.Fit with the leading edge reinforcing member 3 and the surface of horizontal tail covering 1 respectively and be glued fixing in two limits of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 the same side drift angles.Fit with the surface of horizontal tail covering 1 and wing lining 4 respectively and be glued fixing in two limits of the drift angle of last honeycomb sandwich layer 2 and following honeycomb sandwich layer 5 opposite sides.
The aluminum alloy of wing lining 4 usefulness 5mm is made, and its profile is V-shaped, with the profile at leading edge of a wing place.The groove fit on the front end of this wing lining 4 and leading edge reinforcing member 3 surfaces, the tail end of wing lining 4 is to wing web place.Pass through the gusset plate riveted and fixed between wing lining 4 and the rib.
Claims (5)
1. aircraft horizontal tail that the leading edge reinforcing member is arranged, it is characterized in that, described anti-bird knocks machine horizontal tail leading edge away and comprises horizontal tail covering (1), goes up honeycomb sandwich layer (2) and following honeycomb sandwich layer (5), leading edge reinforcing member (3) and wing lining (4), between last honeycomb sandwich layer (2) and following honeycomb sandwich layer (5), leading edge reinforcing member (3) and wing lining (4) are all respectively striden in being arranged in the leading edge of a wing along the exhibition of aircraft horizontal tail; Wherein, leading edge reinforcing member (3) is tri-prismoid, and an angle of this leading edge reinforcing member is positioned at the front end place of the leading edge of a wing; The last honeycomb sandwich layer (2) of parallelogram and following honeycomb sandwich layer (5) are separately fixed at the inside face up and down of horizontal tail covering (1), and two limits of last honeycomb sandwich layer (2) and following honeycomb sandwich layer (5) the same side drift angle are fixed with the surface of leading edge reinforcing member (3) and horizontal tail covering (1) respectively, and two limits of the drift angle of last honeycomb sandwich layer (2) and following honeycomb sandwich layer (5) opposite side are fixed with the surface of horizontal tail covering (1) and wing lining (4) respectively; Wing lining (4) is fixed on honeycomb sandwich layer (2) and following honeycomb sandwich layer (5), and the surface of leading edge reinforcing member (3), will go up honeycomb sandwich layer (2), following honeycomb sandwich layer (5) and leading edge reinforcing member (3) and be coated between wing lining (4) and horizontal tail covering (1) inside face.
2. a kind of according to claim 1 aircraft horizontal tail that the leading edge reinforcing member is arranged is characterized in that, there is the groove that cooperates with wing lining (4) front end on a surface of leading edge reinforcing member (3).
3. a kind of according to claim 1 aircraft horizontal tail that the leading edge reinforcing member is arranged is characterized in that, the outer profile just as leading edge of a wing place of wing lining (4); The groove fit on the front end of this wing lining (4) and leading edge reinforcing member (3) surface, the tail end of wing lining (4) is to wing web place.
4. a kind of according to claim 1 aircraft horizontal tail that the leading edge reinforcing member is arranged is characterized in that, the thickness of last honeycomb sandwich layer (2) and following honeycomb sandwich layer (5) is 5～20mm.
5. as a kind of aircraft horizontal tail that the leading edge reinforcing member is arranged as described in the claim 2, it is characterized in that, the groove on leading edge reinforcing member (3) surface, corresponding with leading edge reinforcing member (3) with the angle that leading edge of a wing front end cooperates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206179313U CN201971150U (en) | 2010-11-18 | 2010-11-18 | Aircraft tailplane with front edge reinforced element |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206179313U CN201971150U (en) | 2010-11-18 | 2010-11-18 | Aircraft tailplane with front edge reinforced element |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201971150U true CN201971150U (en) | 2011-09-14 |
Family
ID=44576254
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010206179313U Expired - Fee Related CN201971150U (en) | 2010-11-18 | 2010-11-18 | Aircraft tailplane with front edge reinforced element |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201971150U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102390520A (en) * | 2011-09-29 | 2012-03-28 | 西北工业大学 | Empennage capable of improving bird strike resistance of airplane |
| CN103057690A (en) * | 2012-12-21 | 2013-04-24 | 中国商用飞机有限责任公司 | Airplane wing surface front edge structure |
| CN105398563A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Wing of membrane structure |
| CN114084358A (en) * | 2021-12-28 | 2022-02-25 | 中国航空工业集团公司西安飞机设计研究所 | Bird collision resisting structure of airplane |
-
2010
- 2010-11-18 CN CN2010206179313U patent/CN201971150U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102390520A (en) * | 2011-09-29 | 2012-03-28 | 西北工业大学 | Empennage capable of improving bird strike resistance of airplane |
| CN102390520B (en) * | 2011-09-29 | 2014-06-18 | 西北工业大学 | Empennage capable of improving bird strike resistance of airplane |
| CN103057690A (en) * | 2012-12-21 | 2013-04-24 | 中国商用飞机有限责任公司 | Airplane wing surface front edge structure |
| WO2014094549A1 (en) * | 2012-12-21 | 2014-06-26 | 中国商用飞机有限责任公司 | Aeroplane airfoil leading edge structure |
| CN105398563A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Wing of membrane structure |
| CN114084358A (en) * | 2021-12-28 | 2022-02-25 | 中国航空工业集团公司西安飞机设计研究所 | Bird collision resisting structure of airplane |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102030102B (en) | Horizontal tail front edge for bird strike-resisting airplane | |
| CN102390520B (en) | Empennage capable of improving bird strike resistance of airplane | |
| US7866605B2 (en) | Energy absorbing impact band and method | |
| CN106697258B (en) | A kind of leading edge of a wing that can be improved bird strike resistance of airplane and hit performance | |
| CN202320773U (en) | Bird collision prevention airplane empennage | |
| EP2196391B1 (en) | Impact resistant aircraft leading edge structures and aircraft including the same | |
| CN106986003B (en) | A kind of anti-bird having monocline plate knocks tail nose of wing away | |
| Herrmann et al. | Sandwich structures technology in commercial aviation: Present applications and future trends | |
| EP2681112B1 (en) | Diamond shaped window for a composite and/or metallic airframe | |
| EP3318481B1 (en) | Panel structure for an aircraft and manufacturing method thereof | |
| US10131415B2 (en) | Airframe leading edge | |
| CN201971150U (en) | Aircraft tailplane with front edge reinforced element | |
| CN101389471A (en) | Protection device | |
| US10369762B2 (en) | Impact resistant sandwich structure | |
| CN204250350U (en) | A kind of anti-bird of aircraft leading edge arranging monocline plate hits structure | |
| CN204250357U (en) | A kind of anti-bird of aircraft leading edge arranging inside panel hits structure | |
| CN112407244B (en) | Aircraft leading edge assembly | |
| WO2014094549A1 (en) | Aeroplane airfoil leading edge structure | |
| CN109383755A (en) | It is a kind of can the aircraft leading edge structure hit of anti-bird | |
| CN207045686U (en) | A kind of leading edge of a wing stressed-skin construction | |
| US11597497B2 (en) | Leading edge structure for an aerodynamic surface of an aircraft | |
| CN204250354U (en) | A kind of anti-bird of aircraft leading edge arranging short beam hits structure | |
| CN115783239A (en) | Anti-bird-collision reinforcement for front edge of A-shaped airplane tail wing | |
| EP4124565A1 (en) | A reinforced leading edge section for an aircraft | |
| CN216332809U (en) | Helicopter tail servo fairing capable of resisting bird collision |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C53 | Correction of patent for invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Li Yulong Inventor after: Shi Xiaopeng Inventor after: Suo Tao Inventor after: Liu Jun Inventor after: Wang Yang Inventor after: Zeng Zhi Inventor before: Li Yulong Inventor before: Shi Xiaopeng Inventor before: Suo Tao Inventor before: Liu Jun |
|
| COR | Change of bibliographic data |
Free format text: CORRECT: INVENTOR; FROM: LI YULONG SHI XIAOPENG SUO TAO LIU JUN TO: LI YULONG SHI XIAOPENG SUO TAO LIU JUN WANG YANG CENG ZHI |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110914 Termination date: 20171118 |