CN110304237A - Aircraft wing and aircraft comprising same - Google Patents
Aircraft wing and aircraft comprising same Download PDFInfo
- Publication number
- CN110304237A CN110304237A CN201910634933.9A CN201910634933A CN110304237A CN 110304237 A CN110304237 A CN 110304237A CN 201910634933 A CN201910634933 A CN 201910634933A CN 110304237 A CN110304237 A CN 110304237A
- Authority
- CN
- China
- Prior art keywords
- leading edge
- aircraft
- side tension
- tension cords
- aircraft 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.)
- Granted
Links
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000013013 elastic material Substances 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 2
- 230000002265 prevention Effects 0.000 abstract 1
- 239000000463 material Substances 0.000 description 4
- 230000035939 shock Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000002131 composite material Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000013139 quantization Methods 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/187—Ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Catching Or Destruction (AREA)
Abstract
A leading edge portion of an aircraft wing comprising: a leading edge deck rail having at least one support rib disposed thereon; the skin is connected to the front-edge cabin beam and encloses an inner space together with the front-edge cabin beam, and the supporting ribs are positioned in the inner space; wherein the leading edge portion further comprises at least one tensioning cable therein, the tensioning cable extending in the interior space in the longitudinal direction of the leading edge portion. The structure of the aircraft wing can meet the existing bird collision prevention design requirement and also give consideration to the lightweight requirement in the aircraft design.
Description
Technical field
The present invention relates to a kind of aircraft.More particularly it relates to the improvement of the wing structure to aircraft, the machine
Wing structure helps to resist the impact that such as bird is hit etc.The invention further relates to the aircraft including the aircraft wing.
Background technique
The aircraft of civil aircraft etc. can face full spectrum of threats in flight course.For example, in the flight of aircraft
In the process, aircraft can meet with bird and hit.According to incomplete statistics, in recent ten years, civil aircraft meets with the accident that bird is hit and is up to 4
Wan Duoqi.Therefore, bird hits an important factor for having become and threatening flight safety.
Therefore, in airplane design, the design of the leading edge structure of the components such as aircaft configuration, especially wing is proposed anti-
The requirement that bird is hit.For fuselage (including the leading edge of a wing, head etc.), usually requires that and still ensured that when with the collision of the bird of 4 pound weights
Aircraft can continue to flight and safe landing.And for empennage, design requirement is higher.For example, being directed to according in " portion CCAR-25 "
The anti-bird impact design of tail structure, it is desirable that the design of tail structure must assure that aircraft is that the bird of 3.6 kilograms of (8 pounds) weights is bumped against
It remains to continue safe flight and landing later.
In traditional wing design, usually there are several selections.A kind of design alternative is to be met using close rib configuration with metal
Wind face matches, and is the form using tilt prop or floor stringer there are also a kind of design alternative.For such wing structure,
To meet the requirement of above-mentioned wing design clause, then it will lead to construction weight and greatly improve, this is again light with Flight Vehicle Design
Quantization requires to contradict.
Therefore, however it remains the demand to the design of improved aircraft wing can not only meet for aircraft knot
The anti-bird of structure hits design requirement, and is also able to satisfy the light-weighted requirement of Flight Vehicle Structure.
Summary of the invention
The present invention is to solve above-described problem of the prior art and make.The object of the present invention is to provide one kind
Improved aircraft wing structure can satisfy existing anti-bird and hit design requirement, while also taking into account in Flight Vehicle Design
Lightweight requirements.
Above-mentioned purpose realized by a kind of structure of improved aircraft wing, the leading edge potion subpackage of the aircraft wing
Include: leading edge Hold Beam is provided at least one supporting rib on leading edge Hold Beam；And covering, the covering are connected to leading edge Hold Beam
On, and inner space is crossed together with leading edge Hold Beam, in the internally positioned space of supporting rib；Wherein, further include in leading edge portion to
Few side tension cords, side tension cords extend along the longitudinal direction of leading edge portion in the interior space.
Side tension cords are set by the inside of the leading edge portion in aircraft wing, when the aircraft wing is hit etc by bird
Impact when, side tension cords can absorb certain impact force, to and protect a possibility that reducing the covering rupture of aircraft wing
Holding the covering not ruptured can export flying bird from upper and lower two sides, so that further decreasing influences caused by shock.
It include at least two supporting ribs in the leading edge portion of aircraft wing, this is at least in a kind of preferable structure
The first supporting rib and the second supporting rib in two supporting ribs are located near the both ends of aircraft wing, and above-described
The first end of at least one side tension cords is connected on the first supporting rib, and the second end of at least one side tension cords is connected to second
On supporting rib, so that at least one side tension cords are stretched between the first supporting rib and the second supporting rib.Supporting rib is simultaneously as a result,
It can play the role of bearing and tensioning side tension cords.
Further preferably in structure, side tension cords fixed part is respectively formed at the both ends of side tension cords, first and second
Mounting hole corresponding with side tension cords fixed part is respectively formed on supporting rib, side tension cords fixed part cooperates in mounting hole.
Wherein, more preferably, it is formed with internal screw thread in mounting hole, and is formed with relatively on side tension cords fixed part mounting hole
The external screw thread answered.The threaded connection allows that the rate of tension of side tension cords is adjusted.
Preferably, side tension cords are located near covering.More preferably, side tension cords are close to covering setting.In this way, side tension cords can be more
Directly absorb impact force suffered by covering.
Preferably, side tension cords are made of elastic material.In this way, while bearing in knockout process to covering 30,
Flexible deformation can occur for the side tension cords, so that more impact forces can be absorbed in side tension cords.
Preferably, the U-shaped profile of covering, the structure of the U-shaped allows to decompose impact force to upper and lower two sides, and also
It can help to guide the rammer of flying bird etc to upper and lower two sides.
Herein, the covering is made of aluminum alloy materials.In addition to this, covering can also be by other well known in the prior art
Suitable aeronautical material is made.
The invention also discloses a kind of aircraft.Wherein, which includes aircraft wing as described above.
Detailed description of the invention
In the description carried out below in conjunction with attached drawing to specific embodiments of the present invention, it can help to advantages of the present invention
With the understanding of feature, these specific embodiments are only exemplary, and are limited the scope of the invention without application.In the accompanying drawings:
Fig. 1 is the exploded perspective view of the part-structure of aircraft wing of the invention, specifically the leading edge portion of the wing
Exploded perspective view.
Fig. 2 is the front view of aircraft wing part shown in FIG. 1.
Fig. 3 A~3C schematically shows aircraft machine of the invention with the obtained sectional view of line A-A in Fig. 2
Anti- bird of the wing structure when being hit hits principle；Wherein, Fig. 3 A shows that aircraft wing will be hit, and Fig. 3 B shows winged
Row device wing is initially subjected to state when hitting and deforming, and Fig. 3 C then shows aircraft wing and exports flying bird from upper and lower two sides
Schematic diagram.
Specific embodiment
Below in conjunction with attached drawing, detailed description of the preferred embodiments.It is to be appreciated that shown in attached drawing
Be only presently preferred embodiments of the present invention, and be not construed to limit the scope of the present.Those skilled in the art can
To carry out various obvious modifications, modification, equivalence replacement to the present invention on the basis of embodiment shown in the drawings, these
All fall within the scope and spirit of the invention.
Fig. 1 shows the exploded perspective view of the part-structure of aircraft wing of the invention, and what is be specifically illustrated in is the machine
The leading edge portion of the wing, Fig. 2 then show the front view of the leading edge portion of the assembled aircraft wing.The aircraft wing can
It applies in the aircraft of such as large-scale passenger airplane etc.
As shown, the leading edge portion 1 of aircraft wing includes leading edge Hold Beam 10, it is provided at least on leading edge Hold Beam 10
One, preferably multiple supporting ribs 20.In exemplary structure shown in the figure, there are two supporting ribs 20 for setting.
Leading edge portion 1 further includes covering 30, which is connected on leading edge Hold Beam 10, and is enclosed together with leading edge Hold Beam 10
An inner space out, supporting rib 20 are arranged in the inner space.Wherein, which is preferably comprised the section of U-shaped,
To which the buffer capacity of 30 pairs of covering shocks can be improved.For manufacturing the gold that the material of covering 30 may include such as aluminium alloy etc
Belong to material, or can be made of other composite materials suitable for aviation field.
In aircraft wing of the invention, at least one, preferably is additionally provided in the leading edge portion 1 of aircraft wing
More side tension cords 40.These side tension cords 40 are arranged in the inner space as encircled by leading edge Hold Beam 10 and covering 30, along institute
The longitudinal of leading edge portion is stated to extend.Preferably, the side tension cords 40 are located near covering 30, and more preferably, side tension cords 40 are close to
Covering 30.By the way that side tension cords 40 are arranged, when its wing is subjected to the shock thing that such as bird is hit etc to aircraft in flight course
When part, side tension cords 40 can provide additional bearing for the covering 30 of the leading edge of a wing, and additionally aid and absorb a part of impact force.
Also, the side tension cords 40 preferably can further be hit by having the material of certain elasticity to be made to can provide
Power absorbability is hit, to improve the crashworthiness of the leading edge portion 1 of aircraft wing.
In a kind of preferred construction of the invention, side tension cords 40 can be connected and are stretched between two supporting ribs 20.For example,
In structure as shown in Figure 1, including two supporting ribs 20, the two supporting ribs 20 are separately positioned on the both ends part of wing
Near, mounting hole 21 is formed on each supporting rib 20, the both ends of side tension cords 40 are then accordingly formed with side tension cords fixed part
41.The structure of the side tension cords fixed part 41 is corresponding with the structure of mounting hole 21, so that side tension cords fixed part 41 can be with merging
Fixed in mounting hole 21.
For example, internal screw thread can be formed in mounting hole 21, and phase is formed on the outer surface of side tension cords fixed part 41
Matched external screw thread.By being threadedly engaged between internal screw thread and external screw thread, side tension cords fixed part 41 is installed to mounting hole 21
In.Also, during the installation process, it can permit peace by the way that side tension cords fixed part 41 is screwed in and screwed out relative to mounting hole 21
The rate of tension of dress personnel adjusting side tension cords 40.
Alternatively, the outer diameter of side tension cords fixed part 41 is formed as interior slightly larger than mounting hole 21 in similar alternative arrangements
Diameter, so that side tension cords fixed part 41 is interference fitted in mounting hole 21.
In other structure, the mounting hole 21 being formed on supporting rib 20 also can be omitted, but directly by side tension cords
40 both ends are fixed on supporting rib 20 by the means of welding etc., this is same also within the scope of the invention.
Further, side tension cords 40 are also not necessarily connected on supporting rib 20, but can connect in other suitable knots
On structure, such as it can be respectively formed flange part at the both ends of covering 30, the both ends of side tension cords 40 are then fixed on the flange part.Cause
This, although there are two supporting ribs 20 for setting in preferred structure shown in the drawings of the invention, to be separately connected side tension cords 40
Both ends, but may also set up the supporting rib 20 of other quantity, such as one, three or more supporting ribs 20, and supporting rib 20
It is not structure necessary to connection side tension cords 40.
The principle that the anti-bird of the improvement structure of aircraft wing of the invention is hit is described below in conjunction with Fig. 3 A~3C.
The sectional view that the line A-A in Fig. 2 is obtained is shown in Fig. 3 A~3C, and which schematically illustrates of the invention
The anti-bird of aircraft wing structure hits principle.
As shown in Figure 3A, in the flight course of aircraft, the leading edge of a wing of the aircraft is likely to occur and front
The event that flying bird 2 is bumped against.At this point, the covering 30 of the leading edge of a wing of aircraft is in intact U-shaped section form, and there are more tensionings
Rope 40 is close to covering 30 and is arranged.
When flying bird 2 strikes on the covering 30 of the leading edge of a wing, as shown in Figure 3B, 30 stress deformation of covering, setting is being covered
30 inside of skin and 40 pairs of the side tension cords offer bearings of coverings 30 deformed for being preferably close to the covering 30, to prevent covering 30 because of mistake
Degree is deformed and is damaged.Further, which is preferably made of elastic material, to supported to covering 30
Flexible deformation occurs simultaneously.
Referring next to Fig. 3 C, energy when flying bird 2 hits covering 30 is absorbed by covering 30 and the deformation of side tension cords 40, and
And side tension cords 40 play the supporting role to covering 30, to prevent covering 30 from rupturing.When hitting, due to flying bird 2
Etc rammer it is very high relative to the speed of wing, therefore it can show to be similar to hydromechanical characteristic.It does not break at this time
The covering 30 split can be directed to except the leading edge of wing as treating fluid from upper and lower two sides by flying bird 2, thus protect machine
The internal structure of the wing will not the shock further by flying bird 2 influenced.
It can be seen that, aircraft wing structure of the invention can effectively mitigate bird and hit to wing from the above description
It influences, so as to hit design requirement to the anti-bird of Flight Vehicle Structure with lighter structure satisfaction.
Claims (10)
1. the leading edge portion of a kind of aircraft wing, the aircraft wing includes:
Leading edge Hold Beam is provided at least one supporting rib on the leading edge Hold Beam；And
Covering, the covering is connected on the leading edge Hold Beam, and inner space is crossed together with leading edge Hold Beam, the supporting rib
In the inner space；
It is characterized in that, further including at least one side tension cords in the leading edge portion, the side tension cords are in the inner space
Extend along the longitudinal direction of the leading edge portion.
2. aircraft wing as described in claim 1, which is characterized in that the leading edge portion of the aircraft wing includes at least
Two supporting ribs, the first supporting rib and the second supporting rib at least two supporting rib are located at the aircraft wing
Both ends near, the first end of at least one side tension cords is connected on first supporting rib, at least one tensioning
The second end of rope is connected on second supporting rib, thus at least one side tension cords be stretched in first supporting rib and
Between second supporting rib.
3. aircraft wing as claimed in claim 2, which is characterized in that be respectively formed with tensioning at the both ends of the side tension cords
Rope fixed part, is respectively formed with mounting hole corresponding with side tension cords fixed part on first and second supporting rib, and described
Tight rope fixed part cooperation is in the mounting hole.
4. aircraft wing as claimed in claim 3, which is characterized in that it is formed with internal screw thread in the mounting hole, described
Corresponding external screw thread is formed on tight rope fixed part.
5. aircraft wing as described in claim 1, which is characterized in that the side tension cords are located near the covering.
6. aircraft wing as claimed in claim 5, which is characterized in that the side tension cords are close to the covering setting.
7. aircraft wing as described in claim 1, which is characterized in that the side tension cords are made of elastic material.
8. such as aircraft wing according to any one of claims 1 to 7, which is characterized in that the cross section of the covering is in U
Shape.
9. such as aircraft wing according to any one of claims 1 to 7, which is characterized in that the covering is by aluminum alloy materials
It is made.
10. a kind of aircraft, which is characterized in that the aircraft includes such as aircraft according to any one of claims 1 to 9
Wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910634933.9A CN110304237B (en) | 2019-07-15 | 2019-07-15 | Aircraft wing and aircraft comprising same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910634933.9A CN110304237B (en) | 2019-07-15 | 2019-07-15 | Aircraft wing and aircraft comprising same |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110304237A true CN110304237A (en) | 2019-10-08 |
| CN110304237B CN110304237B (en) | 2023-08-25 |
Family
ID=68080109
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910634933.9A Active CN110304237B (en) | 2019-07-15 | 2019-07-15 | Aircraft wing and aircraft comprising same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110304237B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BRPI0509484A (en) * | 2004-04-16 | 2007-09-11 | Airbus Gmbh | aircraft structure fairing |
| US20080237401A1 (en) * | 2004-01-22 | 2008-10-02 | Sonaca S.A. | Mobile Leading Edge Flap for a Main Wing of the Aerofoils of an Aircraft and Main Wing Provided with Such a Flap |
| US20140166818A1 (en) * | 2011-08-23 | 2014-06-19 | Mitsubishi Aircraft Corporation | Slat, wing of aircraft, flight control surface of aircraft, and aircraft |
| CN204846359U (en) * | 2015-06-23 | 2015-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Leading edge is hit to anti bird of embedded net formula |
| CN106184776A (en) * | 2015-05-04 | 2016-12-07 | 姚舜 | A kind of the method that elastic anti-bird hits net is set at aircraft engine air inlet |
| EP3248864A1 (en) * | 2016-05-24 | 2017-11-29 | Airbus Operations, S.L. | Armoured leading edge and manufacturing method thereof |
| CN206939049U (en) * | 2017-07-05 | 2018-01-30 | 中国航空工业集团公司西安飞机设计研究所 | A kind of leading edge of a wing structure |
| CN108248814A (en) * | 2018-01-10 | 2018-07-06 | 中国商用飞机有限责任公司 | Aircraft bird strike resistant front edge and support for aircraft bird strike resistant front edge |
-
2019
- 2019-07-15 CN CN201910634933.9A patent/CN110304237B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080237401A1 (en) * | 2004-01-22 | 2008-10-02 | Sonaca S.A. | Mobile Leading Edge Flap for a Main Wing of the Aerofoils of an Aircraft and Main Wing Provided with Such a Flap |
| BRPI0509484A (en) * | 2004-04-16 | 2007-09-11 | Airbus Gmbh | aircraft structure fairing |
| US20140166818A1 (en) * | 2011-08-23 | 2014-06-19 | Mitsubishi Aircraft Corporation | Slat, wing of aircraft, flight control surface of aircraft, and aircraft |
| CN106184776A (en) * | 2015-05-04 | 2016-12-07 | 姚舜 | A kind of the method that elastic anti-bird hits net is set at aircraft engine air inlet |
| CN204846359U (en) * | 2015-06-23 | 2015-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Leading edge is hit to anti bird of embedded net formula |
| EP3248864A1 (en) * | 2016-05-24 | 2017-11-29 | Airbus Operations, S.L. | Armoured leading edge and manufacturing method thereof |
| CN206939049U (en) * | 2017-07-05 | 2018-01-30 | 中国航空工业集团公司西安飞机设计研究所 | A kind of leading edge of a wing structure |
| CN108248814A (en) * | 2018-01-10 | 2018-07-06 | 中国商用飞机有限责任公司 | Aircraft bird strike resistant front edge and support for aircraft bird strike resistant front edge |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110304237B (en) | 2023-08-25 |
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