CN103057690A - Airplane wing surface front edge structure - Google Patents
Airplane wing surface front edge structure Download PDFInfo
- Publication number
- CN103057690A CN103057690A CN2012105635223A CN201210563522A CN103057690A CN 103057690 A CN103057690 A CN 103057690A CN 2012105635223 A CN2012105635223 A CN 2012105635223A CN 201210563522 A CN201210563522 A CN 201210563522A CN 103057690 A CN103057690 A CN 103057690A
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- leading edge
- edge structure
- composite material
- core layer
- type core
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- 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
Abstract
The invention relates to the technical field of civil airplane structural design, and provides an airplane wing surface front edge structure so as to meet the function of bird impact resistance. The airplane wing surface front edge structure comprises three parts, namely a metal panel, a honeycomb sandwich layer and a composite material inner liner, wherein the three parts are attached together according to an exterior-to-interior order in a laying mode, solidified and formed in an autoclave. The front edge structure can be formed without the requirement for assembly of other parts and components excerpt for the three parts, and therefore manufacturing cost is greatly reduced. Meanwhile, due to arrangement of the honeycomb sandwich layer and the composite material inner liner, rigidity, strength and impact resistant capacity of the structure are greatly improved, and therefore kinetic energy of a bird body can be converted to plastic deformation energy of the structure when the structure is impacted by the bird body.
Description
Technical field
The present invention relates generally to civil aircraft structure-design technique field, is specifically related to a kind of plane airfoil leading edge structure.
Background technology
Commercial aircraft is in flight course, and bird is hit becomes a potential threat.According to incompletely statistics, since nineteen ninety-eight, bird is hit and causes annual 198 people to die; In the U.S., the every annual of economic loss that the bird accident of hitting of commercial aircraft causes surpasses 400,000,000 U.S. dollars, and there are more than 30 hundred million U.S. dollars in the whole world.The generation of hitting accident based on bird will bring serious consequence, and clear airplane design unit should have corresponding anti-bird to hit measure when the design aircraft in the air worthiness regulation that various countries put into effect.Wherein, " airplane in transportation category airworthiness standard " the 25th 631 clauses that CAAC formulates to the anti-bird of tail structure hit require as follows: the design of tail structure must guarantee that aircraft is after bumping against with 3.6 kilograms (8 pounds) heavy bird, still can continue safe flight and landing, the speed of aircraft during collision (along the aircraft flight flight path with respect to bird) equals aircraft at the cruising speed on selected sea level.Usually the bird impact resistance of plane airfoil leading edge is all to sacrifice weight as cost.Some researchers are arranged, such as the people such as Timothy J.Lee of the U.S., propose at the inner reinforcing member of placing of leading edge, utilize reinforcing member cutting bird body to reach anti-bird and hit effect, but this design can strengthen manufacturing cost and can increase structural weight equally, and its assembling in leading edge inside is not easy to realize.In a word, existing anti-bird is hit leading edge structure or sacrificing weight as cost, or is exactly that manufacturing cost is higher, and these all can reduce the macroeconomic of civil aircraft.
Summary of the invention
Therefore, provide a kind of and can satisfy anti-bird and hit function, and expendable weight and the plane airfoil leading edge structure that reduces manufacturing cost will be favourable.
According to one embodiment of the present invention, a kind of plane airfoil leading edge structure has been proposed, it comprises metal decking, cellular type core layer and three parts of composite material as liner, wherein, metal decking, cellular type core layer and composite material as liner are according to from outside to inside order paving together and co-curing moulding in autoclave.
Preferably, above-mentioned cellular type core layer is the overstretching paper honeycomb.
Preferably, the thickness of above-mentioned cellular type core layer is 8～30mm.
Further preferably, the thickness of above-mentioned cellular type core layer is 10～15mm.
Preferably, above-mentioned composite material as liner is made by glass fibre or carbon fiber.
Preferably, above-mentioned composite material as liner is arranged to one deck or multilayer
Preferably, the thickness of above-mentioned metal decking is 0.5～1.5mm.
Further preferably, the thickness of above-mentioned metal decking is 1mm.
Compared with prior art, because plane airfoil leading edge structure of the present invention is only by metal decking, cellular type core layer and composite material face co-curing form, do not need to assemble with other parts again, above-mentioned three parts are made and have namely been formed leading edge structure, like this, greatly reduce manufacturing cost, and meanwhile, the cellular type core layer the rigidity that can provide higher is set, high-intensity composite material as liner further plays booster action to the external metallization panel that withstands shocks, and can be the plastic deformation ability of structure with the kinetic transformation of bird body thereby make outer panels when being subject to the impact of bird body.
Description of drawings
Further feature of the present invention and advantage will be understood better by the preferred implementation of describing in detail below in conjunction with accompanying drawing, in the accompanying drawing, and the same or analogous parts of identical designated, wherein:
Fig. 1 is the schematic three dimensional views of plane airfoil leading edge structure according to the preferred embodiment of the present invention;
Fig. 2 is the schematic diagram after the cross-sectional plane of plane airfoil leading edge structure among Fig. 1 amplifies;
Fig. 3 is the schematic three dimensional views of the metal decking of plane airfoil leading edge structure among Fig. 1;
Fig. 4 is the schematic three dimensional views of the cellular type core layer of plane airfoil leading edge structure among Fig. 1;
Fig. 5 is the schematic three dimensional views of the composite material as liner of plane airfoil leading edge structure among Fig. 1.
Description of reference numerals
1 metal decking, 2 cellular type cores
3 composite material faces 31 are recessed
The specific embodiment
The below describes enforcement and the use of specific embodiments of the invention in detail.Yet, should be appreciated that described specific embodiment only exemplarily illustrates enforcement and uses ad hoc fashion of the present invention, but not limit the scope of the invention.
Referring to Fig. 1, Fig. 2, and in conjunction with Fig. 3, Fig. 4, Fig. 5, the plane airfoil leading edge structure comprises metal decking 1, cellular type core layer 2 and composite material as liner 3 totally three parts according to the preferred embodiment of the present invention, and these three parts according to from outside to inside order paving together and co-curing moulding in autoclave.Preferably, cellular type core layer 2 is the overstretching honeycomb, THICKNESS CONTROL in the scope of 8～30mm, better with THICKNESS CONTROL in the scope of 10～15mm.Composite material as liner 3 is preferably made by glass fibre or carbon fiber, can be arranged to multilayer.The thickness of metal decking 1 is preferably 0.5～1.5mm, is preferably 1mm.
Again as shown in Figure 5, in the present embodiment, composite material as liner 3 preferably is formed with recessed 31 in a side of fitting with cellular type core layer 2, this recessed 31 can be used to receive cellular type core layer 2 within it, thereby paving is together better for three parts that make structure of the present invention.
The present invention takes into full account the essence that bird is hit problem, is the kinetic transformation of bird body the plastic deformation ability of structure how namely.In the above-described embodiment, cellular type core layer 2 can provide higher rigidity, needs more energy when it deforms; The external metallization panel 1 that 3 pairs of high-intensity composite material as liner withstand shocks is strengthened, thereby makes metal decking can produce large-area plastic deformation when being subject to impacting rather than impacted into a hole.Test shows, by changing thickness, the thickness of metal decking and the laying quantity of composite material as liner of cellular type core layer, the anti-bird that all can change the plane airfoil leading edge structure is hit performance, hits requirement to adapt to different anti-birds.
The below provides several examples of plane airfoil leading edge structure in the present embodiment.
Example 1
This example is used for the horizontal tail leading edge of certain model aircraft.
This example comprises metal decking, cellular type core layer and composite material as liner.
Metal decking is aluminum alloy, and thickness is 1mm.
The cellular type core layer is the overstretching paper honeycomb structure, and thickness is 10mm.
Composite material as liner is glass fabric, and laying quantity is 4 layers.
Metal decking, cellular type core layer and composite material as liner are in the same place according to order paving from outside to inside, put then that co-curing is shaped to the horizontal tail leading edge in the autoclave into.
Example 2
This example is used for the leading edge of a wing of certain model aircraft.
This example comprises metal decking, cellular type core layer and composite material as liner.
Metal decking is aluminum alloy, and thickness is 0.5mm.
The cellular type core layer is the overstretching paper honeycomb, and thickness is 8mm.
Composite material as liner is glass fabric, and laying quantity is 6 layers.
Metal decking, cellular type core layer and composite material as liner are in the same place according to order paving from outside to inside, put then that co-curing is shaped to the leading edge of a wing in the autoclave into.
Example 3
This example is used for the leading edge of a wing of certain model aircraft.
This example comprises metal decking, cellular type core layer and composite material as liner.
Metal decking is aluminum alloy, and thickness is 1.5mm.
The cellular type core layer is the overstretching paper honeycomb, and thickness is 15mm.
Composite material as liner is glass fabric, and laying quantity is 4 layers.
Metal decking, cellular type core layer and composite material as liner are in the same place according to order paving from outside to inside, put then that co-curing is shaped to the leading edge of a wing in the autoclave into.
Example 4
This example is used for the leading edge of a wing of certain model aircraft.
This example comprises metal decking, cellular type core layer and composite material as liner.
Metal decking is aluminum alloy, and thickness is 1.2mm.
The cellular type core layer is the overstretching paper honeycomb, and thickness is 30mm.
Composite material as liner is glass fabric, and laying quantity is 4 layers.
Metal decking, cellular type core layer and composite material as liner are in the same place according to order paving from outside to inside, put then that co-curing is shaped to the leading edge of a wing in the autoclave into.
Example 5
This example is used for the vertical fin leading edge of certain model aircraft.
This example comprises metal decking, cellular type core layer and composite material as liner.
Metal decking is aluminum alloy, and thickness is 0.8mm.
The cellular type core layer is the overstretching paper honeycomb, and thickness is 12mm.
Composite material as liner is carbon fibre fabric, and laying quantity is 6 layers.
Metal decking, cellular type core layer and composite material as liner are in the same place according to order paving from outside to inside, put then that co-curing is shaped to the vertical fin leading edge in the autoclave into.
Technology contents and the technical characterstic of the specific embodiment of the present invention and the example have below been disclosed; yet be appreciated that; under creative ideas of the present invention; those skilled in the art can be to above-mentioned disclosed various feature and is not made various changes and improve in the combination of this feature that clearly illustrates, but all belongs to protection scope of the present invention.The description of above-mentioned embodiment and example is exemplary and not restrictive.
Claims (8)
1. plane airfoil leading edge structure, it is characterized in that, described plane airfoil leading edge structure comprises metal decking (1), cellular type core layer (2) and (3) three parts of composite material as liner, and these three parts according to from outside to inside order paving together and co-curing moulding in autoclave.
2. plane airfoil leading edge structure according to claim 1 is characterized in that, described cellular type core layer (2) is the overstretching paper honeycomb.
3. plane airfoil leading edge structure according to claim 2 is characterized in that, the thickness of described cellular type core layer (2) is 8～30mm.
4. plane airfoil leading edge structure according to claim 3 is characterized in that, the thickness of described cellular type core layer (2) is 10～15mm.
5. according to claim 1 to 4 each described plane airfoil leading edge structures, it is characterized in that, described composite material as liner is made by glass fibre or carbon fiber.
6. plane airfoil leading edge structure according to claim 5 is characterized in that, described composite material as liner is arranged to multilayer.
7. according to claim 1 to 4 each described plane airfoil leading edge structures, it is characterized in that, the thickness of described metal decking (1) is 0.5～1.5mm.
8. plane airfoil leading edge structure according to claim 7 is characterized in that, the thickness of described metal decking (1) is 1mm.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105635223A CN103057690A (en) | 2012-12-21 | 2012-12-21 | Airplane wing surface front edge structure |
| PCT/CN2013/088734 WO2014094549A1 (en) | 2012-12-21 | 2013-12-06 | Aeroplane airfoil leading edge structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105635223A CN103057690A (en) | 2012-12-21 | 2012-12-21 | Airplane wing surface front edge structure |
Publications (1)
| Publication Number | Publication Date |
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| CN103057690A true CN103057690A (en) | 2013-04-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2012105635223A Pending CN103057690A (en) | 2012-12-21 | 2012-12-21 | Airplane wing surface front edge structure |
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| CN (1) | CN103057690A (en) |
| WO (1) | WO2014094549A1 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104002977A (en) * | 2014-05-06 | 2014-08-27 | 浙江美盾航空材料有限公司 | Bird-striking-preventing blocking plate and preparing technology thereof |
| CN106697258A (en) * | 2016-11-28 | 2017-05-24 | 西北工业大学 | Leading edge capable of improving bird impact resistance of airplane |
| CN110550182A (en) * | 2019-09-19 | 2019-12-10 | 中国航空工业集团公司西安飞机设计研究所 | Leading edge structure of airplane |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4124565A1 (en) * | 2021-07-29 | 2023-02-01 | Airbus Operations, S.L.U. | A reinforced leading edge section for an aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5542820A (en) * | 1994-12-23 | 1996-08-06 | United Technologies Corporation | Engineered ceramic components for the leading edge of a helicopter rotor blade |
| US20080265095A1 (en) * | 2007-04-24 | 2008-10-30 | The Boeing Company | Energy absorbing impact band and method |
| US20100140405A1 (en) * | 2008-12-09 | 2010-06-10 | Alenia Aeronautica S.P.A. | Leading edge for aircraft wings and empennages |
| CN102030102A (en) * | 2010-11-18 | 2011-04-27 | 西北工业大学 | Horizontal tail front edge for bird strike-resisting airplane |
| CN201971150U (en) * | 2010-11-18 | 2011-09-14 | 西北工业大学 | Aircraft tailplane with front edge reinforced element |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
-
2012
- 2012-12-21 CN CN2012105635223A patent/CN103057690A/en active Pending
-
2013
- 2013-12-06 WO PCT/CN2013/088734 patent/WO2014094549A1/en active Application Filing
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5542820A (en) * | 1994-12-23 | 1996-08-06 | United Technologies Corporation | Engineered ceramic components for the leading edge of a helicopter rotor blade |
| US20080265095A1 (en) * | 2007-04-24 | 2008-10-30 | The Boeing Company | Energy absorbing impact band and method |
| US20100140405A1 (en) * | 2008-12-09 | 2010-06-10 | Alenia Aeronautica S.P.A. | Leading edge for aircraft wings and empennages |
| CN102030102A (en) * | 2010-11-18 | 2011-04-27 | 西北工业大学 | Horizontal tail front edge for bird strike-resisting airplane |
| CN201971150U (en) * | 2010-11-18 | 2011-09-14 | 西北工业大学 | Aircraft tailplane with front edge reinforced element |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104002977A (en) * | 2014-05-06 | 2014-08-27 | 浙江美盾航空材料有限公司 | Bird-striking-preventing blocking plate and preparing technology thereof |
| CN106697258A (en) * | 2016-11-28 | 2017-05-24 | 西北工业大学 | Leading edge capable of improving bird impact resistance of airplane |
| CN106697258B (en) * | 2016-11-28 | 2019-05-10 | 西北工业大学 | A kind of leading edge of a wing that can be improved bird strike resistance of airplane and hit performance |
| CN110550182A (en) * | 2019-09-19 | 2019-12-10 | 中国航空工业集团公司西安飞机设计研究所 | Leading edge structure of airplane |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2014094549A1 (en) | 2014-06-26 |
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Application publication date: 20130424 |