CN206939049U - A kind of leading edge of a wing structure - Google Patents
A kind of leading edge of a wing structure Download PDFInfo
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- CN206939049U CN206939049U CN201720806571.3U CN201720806571U CN206939049U CN 206939049 U CN206939049 U CN 206939049U CN 201720806571 U CN201720806571 U CN 201720806571U CN 206939049 U CN206939049 U CN 206939049U
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- leading edge
- covering
- corrugated plating
- wing
- wing structure
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Abstract
The utility model discloses a kind of leading edge of a wing structure, it is related to aircraft skin technical field.The leading edge of a wing structure includes covering (1) and corrugated plating (2)；The corrugated plating (2) is arranged on the inner surface of the covering (1), and the bellows segment of the corrugated plating (2) is protruded away from the direction of the covering (1).The utility model has the advantage of：Leading edge of a wing structure of the present utility model is when bird body hits leading edge of a wing covering; under the impact of bird body, after outer layer covering damage inactivation, the corrugated board structures of covering inner surface constantly stretch opening; extend the collision time of bird body; impact, whole process constantly dissipation bird body kinetic energy are reduced, corrugated plating full extension is opened; bird body is intercepted; most load is reached at rib at last, is carried by rib, so as to protect leading edge of a wing equipment and front beam structure.
Description
Technical field
It the utility model is related to aircraft skin technical field, and in particular to a kind of leading edge of a wing structure.
Background technology
Bird knocks the problem of machine is a band generality in aeronautical chart away.The international people as world wide Niao Zhuan data centers
Navigate tissue (ICAO), receives 4000 to 5000 parts of birds every year and hits report, is about averaged every 6 times and just once causes aircraft damage,
About 1.5 ten thousand dollars of the economic loss that an average bird is hit.Hit due to bird and threaten flight safety big, cost height, increasingly
Cause countries in the world army boat, the great attention of Civil Aviation System.
There is data to show, only from 1912 to 1999, bird hits that to result in seven AIRLINE ＆ AIRPORT machines in the whole world great
Aircraft accident, dead people more than 200.Military aircraft bird hits accident also not wherein.Whole world aviation transport is every year because bird is hit just
The loss of about 1300 engine damages may be caused.The 41 member's Kuomintang-Communists of International Civil Aviation Organization in 1993 occur bird and knock machine away
Accident 3427 as many as rises, and the loss thereby resulted in is difficult to estimate.20 birds about occur every year for each airline in Europe hit to start
Machine accident.Counted according to NASA, from 1993 to nineteen ninety-five, the damage that civil aircraft damages caused by wild animal every year
It is about 1.53 hundred million dollars to lose, and aircraft grounds 63.5 ten thousand hours, and it is as caused by being hit bird wherein just to have 95% or so accident.
For in aircraft all parts, machine, empennage, these windward sides of empennage leading edge are the portions for being easiest to hit by bird body
Position.Bird collides, empennage, empennage will seriously change its pneumatic external form；Control operating rod, which is hit deformation, can cause aircraft handling difficult；Fly
Bird breakdown fluid pressure line, fuel pipe causes to catch fire to manipulate；Breakdown cable can also make aircraft out of hand.Therefore, design
It is particularly importantly existing that the leading edge structure that bird is hit can suitably be resisted.
Provided according to CCAR the 25th (CCAR-25)：The structures such as plane nose, machine, empennage leading edge by
In the case that the shock of the bird heavy to 1.8 kilograms (4 pounds) causes structural damage, aircraft allows for completing this flight；In addition,
The design of tail structure must assure that aircraft with 3.6 kilograms (8 pounds) bird bump against after, remain to continue safe flight and
Land.
Utility model content
The purpose of this utility model is to provide a kind of leading edge of a wing structure, effectively prevents bird from hitting harm, ensures flight safety,
To solve the problems, such as or at least mitigate at least one in the presence of background technology.
To achieve these goals, the technical solution adopted in the utility model is：A kind of leading edge of a wing structure is provided, comprising
Covering and corrugated plating；
The corrugated plating is arranged on the inner surface of the covering, and the bellows segment of the corrugated plating is away from the covering
Protrude in direction.
Preferably, the corrugated plating includes straightway and arc section in the tangential section of wing, the straightway with it is described
Arc section arranged for interval.
Preferably, the corrugated plating wing open up to section include straightway and arc section, the straightway with it is described
Arc section arranged for interval.
Preferably, the covering is aluminium lamination or composite laminated plate.
Preferably, the arc section is arranged to semicircle segmental arc.
Preferably, the corrugated plating is the thick aluminium laminations of 0.8mm, and the length of each straightway is 50mm, each described
The arc diameter of arc section is 100mm.
Preferably, the covering is fixedly connected with the corrugated plating at the straightway by rivet.
The beneficial effects of the utility model are：
Leading edge of a wing structure of the present utility model is when bird body hits leading edge of a wing covering, under the impact of bird body, outer layer
After covering damage inactivation, the corrugated board structures of covering inner surface constantly stretch opening, extend the collision time of bird body, reduce
Impact, whole process constantly dissipation bird body kinetic energy, corrugated plating full extension are opened, bird body are intercepted, and most load passes at last
To rib, carried by rib, so as to protect leading edge of a wing equipment and front beam structure.
Brief description of the drawings
Fig. 1 is the schematic diagram of the leading edge of a wing structure of the embodiment of the utility model one.
Fig. 2 is along the tangential schematic cross-section of wing in leading edge of a wing structure shown in Fig. 1.
Fig. 3 is the schematic diagram of the leading edge of a wing structure of another embodiment of the utility model.
Fig. 4 be in leading edge of a wing structure shown in Fig. 3 along wing open up to schematic cross-section.
Wherein, 1- coverings, 2- corrugated platings, 21- straightways, 22- arc sections, 3- ribs.
Embodiment
To make the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, the technical scheme in the embodiment of the utility model is further described in more detail.In the accompanying drawings, from beginning
Same or similar element is represented to same or similar label eventually or there is the element of same or like function.Described reality
It is the utility model part of the embodiment to apply example, rather than whole embodiments.Below with reference to the embodiment of accompanying drawing description
It is exemplary, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained under the premise of creative work is not made
Example, belong to the scope of the utility model protection.Embodiment of the present utility model is described in detail below in conjunction with the accompanying drawings.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, it is for only for ease of description the utility model and simplifies description, rather than indicates or imply and be signified
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The limitation of novel protected scope.
Embodiment 1：
As shown in Figure 1 and Figure 2, a kind of leading edge of a wing structure, includes covering 1 and corrugated plating 2；Corrugated plating 2 is arranged on covering 1
Inner surface, the bellows segment of corrugated plating 2 protrudes away from the direction of covering 1.
In the present embodiment, corrugated plating 2 includes straightway 21 and arc section 22 in the tangential section of wing, straightway 21 with
The arranged for interval of arc section 22.In the present embodiment, corrugated plating 2 is the thick aluminium laminations of 0.8mm, and arc section 22 is arranged to semicircle segmental arc,
The length of each straightway 21 is 50mm, and the arc diameter of each arc section 22 is 100mm；It is understood that corrugated plating 2
Thickness can be set according to actual conditions, for example, in an alternative embodiment, the thickness of corrugated plating 2 is 0.6mm；Another
In alternative, the thickness of corrugated plating 2 is 1mm；The diameter of arc section 22 can also be set according to actual conditions, for example,
In one alternative, a diameter of 80mm of arc section 22；In another alternative embodiment, arc section 22 is a diameter of
160mm；The length of arc section 22 is no longer than semi-circumference.
In the present embodiment, covering 1 is fixedly connected with corrugated plating 2 at straightway 21 by rivet.The material of covering 1 is
Composite laminated plate；It is understood that the material of covering 1 can also select different materials, example according to different structures
Such as, in an alternative embodiment, covering 1 is arranged to aluminium lamination.
Exterior skin keeps smooth and its aerodynamic configuration of airfoil outer surface, between two ribs, covering inner surface arrangement
There is corrugated plating, as shown in Figure 1 and Figure 2.The corrugated plating covering of internal layer is made up of straight burr section and semi arch structural sections, wherein directly
Line segment length and ripple diameter are variable, and corrugated plating covering disconnects along wing spanwise arrangement at rib.The work of corrugated plating
With being, when bird body hits leading edge of a wing covering, under the impact of bird body, after outer layer covering damage inactivation, covering inner surface
Corrugated board structures constantly stretch opening, extend the collision time of bird body, reduce impact, whole process constantly dissipation bird body
Kinetic energy, corrugated plating full extension are opened, bird body intercepted, most load is reached at rib at last, is carried by rib, so as to protect
Leading edge of a wing equipment and front beam structure are protected.
Embodiment 2：
As shown in Figure 3, Figure 4, in the present embodiment, it is with the difference in the embodiment 1：Corrugated plating 2 is in machine
The span to section include straightway 21 and arc section 22, straightway 21 and the arranged for interval of arc section 22.In the present embodiment
In, corrugated plating 2 is the thick aluminium laminations of 0.8mm, and arc section 22 is arranged to semicircle segmental arc, and the length of each straightway 21 is 50mm, often
The arc diameter of individual arc section 22 is 100mm；It is understood that the thickness of corrugated plating 2 can be set according to actual conditions, example
Such as, in an alternative embodiment, the thickness of corrugated plating 2 is 0.6mm；In another alternative embodiment, the thickness of corrugated plating 2 is
1mm；The diameter of arc section 22 can also be set according to actual conditions, for example, in an alternative embodiment, arc section 22 it is straight
Footpath is 80mm；In another alternative embodiment, a diameter of 160mm of arc section 22；The length of arc section 22 is no longer than half
Circumference.
Exterior skin keeps smooth and its aerodynamic configuration of airfoil outer surface, between two ribs, covering inner surface arrangement
There is corrugated plating, as shown in Figure 3, Figure 4.The corrugated plating covering of internal layer is made up of straight burr section and semi arch structural sections, wherein directly
Line segment length and ripple diameter are variable, and corrugated plating covering disconnects along wing spanwise arrangement at rib.The work of corrugated plating
With being, when bird body hits leading edge of a wing covering, under the impact of bird body, after outer layer covering damage inactivation, covering inner surface
Corrugated board structures constantly stretch opening, extend the collision time of bird body, reduce impact, whole process constantly dissipation bird body
Kinetic energy, corrugated plating full extension are opened, bird body are intercepted, and most load is reached at rib 3 at last, is carried by rib, so as to
Protect leading edge of a wing equipment and front beam structure.
It is last it is to be noted that：Above example is only to illustrate the technical solution of the utility model, rather than it is limited
System.Although the utility model is described in detail with reference to the foregoing embodiments, one of ordinary skill in the art should manage
Solution：It can still be modified to the technical scheme described in foregoing embodiments, or which part technical characteristic is entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the utility model
The spirit and scope of technical scheme.
Claims (7)
1. a kind of leading edge of a wing structure, it is characterised in that include covering (1) and corrugated plating (2)；
The corrugated plating (2) is arranged on the inner surface of the covering (1), and the bellows segment of the corrugated plating (2) is away from described
The direction protrusion of covering (1).
2. leading edge of a wing structure as claimed in claim 1, it is characterised in that：The corrugated plating (2) is in the tangential section of wing
Comprising straightway (21) and arc section (22), the straightway (21) and the arc section (22) arranged for interval.
3. leading edge of a wing structure as claimed in claim 1, it is characterised in that：The corrugated plating (2) wing open up to section
Comprising straightway (21) and arc section (22), the straightway (21) and the arc section (22) arranged for interval.
4. leading edge of a wing structure as claimed in claim 2 or claim 3, it is characterised in that：The covering is aluminium lamination or composite layer
Plywood.
5. leading edge of a wing structure as claimed in claim 4, it is characterised in that：The arc section (22) is arranged to semicircle segmental arc.
6. leading edge of a wing structure as claimed in claim 5, it is characterised in that：The corrugated plating (2) is the thick aluminium laminations of 0.8mm,
The length of each straightway (21) is 50mm, and the arc diameter of each arc section (22) is 100mm.
7. leading edge of a wing structure as claimed in claim 6, it is characterised in that：The covering (1) is with the corrugated plating (2) in institute
Straightway (21) place is stated to be fixedly connected by rivet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720806571.3U CN206939049U (en) | 2017-07-05 | 2017-07-05 | A kind of leading edge of a wing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720806571.3U CN206939049U (en) | 2017-07-05 | 2017-07-05 | A kind of leading edge of a wing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206939049U true CN206939049U (en) | 2018-01-30 |
Family
ID=61367940
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720806571.3U Active CN206939049U (en) | 2017-07-05 | 2017-07-05 | A kind of leading edge of a wing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206939049U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110304237A (en) * | 2019-07-15 | 2019-10-08 | 中国商用飞机有限责任公司 | Aircraft wing and aircraft including the aircraft wing |
-
2017
- 2017-07-05 CN CN201720806571.3U patent/CN206939049U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110304237A (en) * | 2019-07-15 | 2019-10-08 | 中国商用飞机有限责任公司 | Aircraft wing and aircraft including the aircraft wing |
| CN110304237B (en) * | 2019-07-15 | 2023-08-25 | 中国商用飞机有限责任公司 | Aircraft wing and aircraft comprising same |
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