CN110697023A - Wing trailing edge bending degree structure - Google Patents
Wing trailing edge bending degree structure Download PDFInfo
- Publication number
- CN110697023A CN110697023A CN201911137238.8A CN201911137238A CN110697023A CN 110697023 A CN110697023 A CN 110697023A CN 201911137238 A CN201911137238 A CN 201911137238A CN 110697023 A CN110697023 A CN 110697023A
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- trailing edge
- pair
- wing
- wing trailing
- stringers
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- 238000005452 bending Methods 0.000 title claims abstract description 16
- 239000011324 bead Substances 0.000 claims 1
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
- B64C3/50—Varying camber by leading or trailing edge flaps
Abstract
The application belongs to wing trailing edge bending design field, concretely relates to wing trailing edge bending structure, include: the connecting stringers of each pair are oppositely arranged on the upper skin at the trailing edge of the wing and the lower skin at the trailing edge of the wing; each connecting stringer having a connecting flange; a plurality of connected curved surface discs, each connected curved surface disc having a curved surface rim strip disposed along an edge thereof; each curved surface edge strip is correspondingly connected with the connecting edge strips of the pair of connecting stringers and can rotate relative to the connecting edge strips of the pair of connecting stringers; the eccentric beam is connected with each connecting curved disc, and each curved disc is distributed along the axial direction of the eccentric beam; the eccentric beam can drive each curved surface disc to rotate, so that each curved surface edge strip rotates relative to the corresponding connecting edge strip, each pair of connecting stringers is driven to move, and then the upper skin of the trailing edge and the lower skin of the trailing edge of the wing connected with each pair of connecting stringers are deformed, and the camber of the trailing edge of the wing is changed.
Description
Technical Field
The application belongs to the field of wing trailing edge bending design, and particularly relates to a wing trailing edge bending structure.
Background
The existing wing design mostly takes the optimal aerodynamic efficiency in a cruising state as a design target, only the camber of the trailing edge of the wing is designed to keep higher aerodynamic efficiency in the cruising state, under the design condition, along with the consumption of flight fuel oil and the change of weight, the required lift force is reduced, the optimal cruising aerodynamic efficiency is kept by changing the flight height, and the utilization rate of energy and airspace is reduced.
The present application is made in view of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a wing trailing edge camber structure that overcomes or alleviates at least one of the deficiencies of the prior art.
The technical scheme of the application is as follows:
a wing trailing edge camber structure, comprising:
the connecting stringers of each pair are oppositely arranged on the upper skin at the trailing edge of the wing and the lower skin at the trailing edge of the wing; each connecting stringer having a connecting flange;
a plurality of connected curved surface discs, each connected curved surface disc having a curved surface rim strip disposed along an edge thereof; each curved surface edge strip is correspondingly connected with the connecting edge strips of the pair of connecting stringers and can rotate relative to the connecting edge strips of the pair of connecting stringers;
the eccentric beam is connected with each connecting curved disc, and each curved disc is distributed along the axial direction of the eccentric beam; the eccentric beam can drive each curved surface disc to rotate, so that each curved surface edge strip rotates relative to the corresponding connecting edge strip, each pair of connecting stringers is driven to move, and then the upper skin of the trailing edge and the lower skin of the trailing edge of the wing connected with each pair of connecting stringers are deformed, and the camber of the trailing edge of the wing is changed.
According to at least one embodiment of the present application, further comprising:
a plurality of pairs of connectors, one connector of each pair connecting one of the pair of connecting stringers to a corresponding curved edge, the other connecting stringer of the pair connecting stringers to the curved edge.
According to at least one embodiment of the present application, each connector includes:
a connecting shaft, both ends of which are bent oppositely;
two connecting bearings, wherein one connecting bearing is arranged at one end of the connecting shaft, and the outer ring of the connecting bearing is in contact with the inner side of the corresponding edge strip; the other connecting bearing is arranged at the other end of the connecting shaft, and the outer ring of the other connecting bearing is contacted with the inner side of the corresponding curved surface edge strip.
According to at least one embodiment of the present application, each connector further comprises:
the limiting bearing is sleeved on the connecting shaft;
the wing trailing edge bending degree structure still includes:
and each pair of limiting stringers is oppositely arranged on the wing trailing edge upper skin and the wing trailing edge lower skin, one of the limiting stringers is correspondingly abutted with one limiting bearing outer ring of the pair of connectors, and the other limiting stringer is abutted with the other limiting bearing outer ring of the pair of connectors.
According to at least one embodiment of the application, one end of the eccentric beam passes through the wing back spar for connection with the servo drive.
According to at least one embodiment of the present application, further comprising:
the butt joint stringers are arranged on the upper skin of the trailing edge of the wing and the lower skin of the trailing edge of the wing oppositely;
the plurality of abutting curved surface discs are connected with the eccentric beam and are distributed along the axial direction of the eccentric beam; the edge correspondence of every butt curved surface disc and a pair of butt stringer butt can rotate for this pair of butt stringer.
According to at least one embodiment of the present application, further comprising:
each pair of sliding blocks is used for being oppositely arranged on the upper covering of the trailing edge of the wing and the lower covering of the trailing edge of the wing; each slide block is provided with a sliding connection surface, and the sliding connection surfaces of each pair of slide blocks are in sliding connection.
According to at least one embodiment of the present application, each pair of sliders has a guide groove on one sliding contact surface and a guide projection on the other sliding contact surface, the guide groove being inserted into the guide groove of the pair of sliders.
According to at least one embodiment of the present application, each pair of sliders is configured to be disposed at a trailing edge tip of the wing.
According to at least one embodiment of the present application, further comprising:
and each skin connecting rod is used for being connected with the upper skin of the wing trailing edge, and the other end of each skin connecting rod is used for being connected with the lower skin of the wing trailing edge.
Drawings
FIG. 1 is a schematic view of a trailing edge camber configuration provided by an embodiment of the present application;
FIG. 2 is a partial view of area A of FIG. 1;
FIG. 3 is a schematic diagram of the eccentric beam, the connecting curved disc and the abutting curved disc provided in the embodiment of the present application;
FIG. 4 is a partial schematic view of a trailing edge camber configuration provided by an embodiment of the present application;
FIG. 5 is another schematic illustration in partial section of a wing trailing edge camber configuration provided by an embodiment of the present application;
wherein:
1-connecting stringers; 2-wing trailing edge upper skin; 3-wing trailing edge lower skin; 4-connecting the edge strips; 5-connecting a curved disc; 6-curved surface edge strip; 7-eccentric beam; 8-a connector; 9-a connecting shaft; 10-connecting a bearing; 11-a limit bearing; 12-spacing stringers; 13-wing back spar; 14-abutting stringers; 15-abutting a curved disc; 16-a slide block; 17-skin tie-rod.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.
The present application is described in further detail below with reference to fig. 1 to 5.
A wing trailing edge camber structure, comprising:
the device comprises a plurality of pairs of connecting stringers 1, wherein each pair of connecting stringers 1 are oppositely arranged on an upper skin 2 at the trailing edge of the wing and a lower skin 3 at the trailing edge of the wing; each connecting stringer 1 has a connecting flange 4;
a plurality of connected curved discs 5, each connected curved disc 5 having a curved rim strip 6 disposed along an edge thereof; each curved surface edge strip 6 is correspondingly connected with the connecting edge strips 4 of the pair of connecting stringers 1 and can rotate relative to the connecting edge strips 4 of the pair of connecting stringers 1;
the eccentric beam 7 is connected with each connecting curved disc 5, and each curved disc 5 is distributed along the axial direction of the eccentric beam 7; the eccentric beam 7 can drive each curved surface disc 5 to rotate, so that each curved surface edge strip 6 rotates relative to the corresponding connecting edge strip 4, each pair of connecting stringers 1 is driven to move, and the wing trailing edge upper skin 2 and the wing trailing edge lower skin 3 connected with each pair of connecting stringers 1 are deformed to change the wing trailing edge camber.
For the wing trailing edge bending degree structure disclosed in the above embodiments, it can be understood by those skilled in the art that the eccentric beam 7 drives each curved disc 5 to rotate, so that the curved surface edge strip 6 on each curved disc 5 rotates relative to the corresponding connecting edge strip 4, and thus each pair of connecting stringers 1 can be driven to move, so that the wing trailing edge upper skin 2 and the wing trailing edge lower skin 3 connected to each pair of connecting stringers 1 deform, and the wing trailing edge bending degree is changed.
For the wing trailing edge bending degree structure disclosed in the above embodiments, it can be further understood by those skilled in the art that the bending degree of the wing trailing edge can be continuously changed by the rotation of the eccentric beam 7, so that the wing trailing edge can be adjusted to an appropriate bending degree in real time according to different flight states, thereby maintaining better aerodynamic efficiency and reducing energy consumption.
With respect to the wing trailing edge camber structure disclosed in the above embodiments, it can be further understood by those skilled in the art that the geometric shapes of the eccentric beam 7 and the connecting camber disk 5, and the number and the distribution positions of the connecting camber disks 5 can be optimally determined according to the specific shape of the wing and the flight target thereof.
In some optional embodiments, further comprising:
a plurality of pairs of connectors 8, one connector 8 of each pair connecting one connecting cap 4 of a pair of connecting stringers 1 to a corresponding curved cap 6 and the other connecting cap 4 of the pair of connecting stringers 1 to the curved cap 6.
In some alternative embodiments, each connector 8 comprises:
a connecting shaft 9, both ends of which are bent oppositely;
two connecting bearings 10, wherein one connecting bearing 10 is arranged at one end of the connecting shaft 9, and the outer ring of the connecting bearing 10 is in contact with the inner side of the corresponding edge strip 4; the other connecting bearing 10 is arranged at the other end of the connecting shaft 9, and the outer ring of the other connecting bearing is in contact with the inner side of the corresponding curved surface edge strip 6.
In some alternative embodiments, each connector 8 further comprises:
the limiting bearing 11 is sleeved on the connecting shaft 9;
the wing trailing edge bending degree structure still includes:
and each pair of limiting stringers 12 is oppositely arranged on the wing trailing edge upper skin 2 and the wing trailing edge lower skin 3, one of the limiting stringers 12 is correspondingly abutted with the outer ring of one limiting bearing 11 of the pair of connectors 8, and the other limiting stringer is abutted with the outer ring of the other limiting bearing 11 of the pair of connectors 8.
In some alternative embodiments, one end of the eccentric beam 7 passes through the wing back spar 13 for connection to the servo drive.
In some optional embodiments, further comprising:
a plurality of pairs of abutting stringers 14, each pair of abutting stringers 14 being arranged on the wing trailing edge upper skin 2 and the wing trailing edge lower skin 3 in an opposing manner;
a plurality of abutting curved surface discs 15 which are connected with the eccentric beam 7 and distributed along the axial direction of the eccentric beam 7; the edge of each contact curved surface disk 15 is in contact with a pair of contact stringers 14, and can rotate relative to the pair of contact stringers 14.
For the wing trailing edge bending degree structure disclosed in the above embodiments, those skilled in the art can understand that through the design of the abutting curved surface disc 15 structure, the abutting curved surface disc 15 can be always kept in abutting contact with the abutting stringer 14 in the wing trailing edge bending degree changing process, so that the shapes of the wing trailing edge upper skin 2 and the wing trailing edge lower skin 3 can be well supported and kept, and the distribution positions of the curved surface discs 15 can be correspondingly set according to the shapes of the wings.
In some optional embodiments, further comprising:
a plurality of pairs of sliders 16, wherein each pair of sliders 16 is used for being oppositely arranged on the wing trailing edge upper skin 2 and the wing trailing edge lower skin 3; each slider 16 has a sliding connection face, the sliding connection faces of each pair of sliders 16 being slidably connected.
In some alternative embodiments, each pair of sliders 16 has a guide groove on one sliding contact surface and a guide projection on the other sliding contact surface, the guide groove being inserted into the guide groove of the pair of sliders 16.
In alternative embodiments, each pair of sliders 16 is configured to be disposed at the trailing edge tip of the wing.
With regard to the wing trailing edge camber structure disclosed in the above embodiments, it can be understood by those skilled in the art that a plurality of pairs of sliders 16 are provided at the wing trailing edge tip, and the sliding contact surfaces of each pair of sliders 16 can maintain sliding connection during the change of the wing trailing edge camber, so as to enable the wing trailing edge upper skin 2 and the wing trailing edge lower skin 3 to generate corresponding deformation camber at the wing trailing edge tip.
In some optional embodiments, further comprising:
and a plurality of skin connecting rods 17, wherein each skin connecting rod 17 is used for being connected with the wing trailing edge upper skin 2, and the other end of each skin connecting rod 17 is used for being connected with the wing trailing edge lower skin 3.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (10)
1. A wing trailing edge camber structure, comprising:
the connecting stringers (1) of each pair are oppositely arranged on the upper skin (2) and the lower skin (3) of the trailing edge of the wing; each connecting stringer (1) having a connecting bead (4);
a plurality of connected curved discs (5), each of said connected curved discs (5) having a curved rim strip (6) disposed along an edge thereof; each curved surface edge strip (6) is correspondingly connected with the connecting edge strips (4) of a pair of the connecting stringers (1) and can rotate relative to the connecting edge strips (4) of the pair of the connecting stringers (1);
the eccentric beam (7) is connected with each curved disc (5), and each curved disc (5) is distributed along the axial direction of the eccentric beam (7); the eccentric beams (7) can drive the curved surface disks (5) to rotate, so that the curved surface flanges (6) rotate relative to the corresponding connecting flanges (4), each pair of connecting stringers (1) are driven to move, the wing trailing edge upper skin (2) and the wing trailing edge lower skin (3) connected with each pair of connecting stringers (1) deform, and the wing trailing edge camber is changed.
2. The wing trailing edge camber structure of claim 1,
further comprising:
a plurality of pairs of connectors (8), one of each pair of connectors (8) connecting one connecting flange (4) of a pair of said connecting stringers (1) to a corresponding curved flange (6), the other connecting flange (4) of the pair of connecting stringers (1) to the curved flange (6).
3. The wing trailing edge camber structure of claim 2,
each connector (8) comprises:
a connecting shaft (9) with two opposite ends bent;
two connecting bearings (10), wherein one connecting bearing (10) is arranged at one end of the connecting shaft (9), and the outer ring of the connecting bearing is in contact with the inner side of the corresponding edge strip (4); and the other connecting bearing (10) is arranged at the other end of the connecting shaft (9), and the outer ring of the connecting bearing is contacted with the inner side of the corresponding curved surface edge strip (6).
4. The wing trailing edge camber structure of claim 3,
each connector (8) further comprises:
the limiting bearing (11) is sleeved on the connecting shaft (9);
the wing trailing edge bending degree structure still includes:
the limiting long purlins (12) are arranged on the wing trailing edge upper skin (2) and the wing trailing edge lower skin (3) oppositely, one limiting long purlins is correspondingly abutted to the outer ring of one limiting bearing (11) of one pair of connectors (8), and the other limiting long purlins are abutted to the outer ring of the other limiting bearing (11) of the pair of connectors (8).
5. The wing trailing edge camber structure of claim 1,
one end of the eccentric beam (7) penetrates through the wing back beam (13) to be connected with the servo driving device.
6. The wing trailing edge camber structure of claim 1,
further comprising:
a plurality of pairs of abutting stringers (14), each pair of abutting stringers (14) being arranged to be opposite to each other on the wing trailing edge upper skin (2) and the wing trailing edge lower skin (3);
a plurality of abutting curved surface discs (15) which are connected with the eccentric beam (7) and are distributed along the axial direction of the eccentric beam (7); the edge of each abutting curved surface disc (15) is correspondingly abutted with the pair of abutting stringers (14) and can rotate relative to the pair of abutting stringers (14).
7. The wing trailing edge camber structure of claim 1,
further comprising:
the sliding blocks (16) in each pair are oppositely arranged on the wing trailing edge upper skin (2) and the wing trailing edge lower skin (3); each slider (16) has a sliding connection face, and the sliding connection faces of each pair of sliders (16) are slidably connected.
8. The wing trailing edge camber structure of claim 7,
one sliding contact surface of each pair of sliders (16) has a guide groove, and the other sliding contact surface has a guide projection, which is inserted into the guide groove of the pair of sliders (16).
9. The wing trailing edge camber structure of claim 7,
each pair of said sliders (16) is intended to be arranged at the trailing edge tip of the wing.
10. The wing trailing edge camber structure of claim 1,
further comprising:
the device comprises a plurality of skin connecting rods (17), wherein each skin connecting rod (17) is used for being connected with the upper skin (2) of the wing trailing edge, and the other end of each skin connecting rod is used for being connected with the lower skin (3) of the wing trailing edge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911137238.8A CN110697023A (en) | 2019-11-19 | 2019-11-19 | Wing trailing edge bending degree structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911137238.8A CN110697023A (en) | 2019-11-19 | 2019-11-19 | Wing trailing edge bending degree structure |
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| Publication Number | Publication Date |
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| CN110697023A true CN110697023A (en) | 2020-01-17 |
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| CN201911137238.8A Pending CN110697023A (en) | 2019-11-19 | 2019-11-19 | Wing trailing edge bending degree structure |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111409816A (en) * | 2020-04-22 | 2020-07-14 | 中国飞机强度研究所 | Variable camber wing leading edge structure |
| CN111661312A (en) * | 2020-05-20 | 2020-09-15 | 北京航空航天大学 | Flexible trailing edge module for trailing edge camber wing |
| CN112141318A (en) * | 2020-09-27 | 2020-12-29 | 西北工业大学 | Rear edge bending mechanism based on knuckle type connecting rod driving |
| CN112224384A (en) * | 2020-09-12 | 2021-01-15 | 西安交通大学 | Self-adaptive variable camber wing trailing edge based on hierarchical piezoelectric stack driving |
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| CN111661312B (en) * | 2020-05-20 | 2022-03-29 | 北京航空航天大学 | Flexible trailing edge module for trailing edge camber wing |
| CN112224384A (en) * | 2020-09-12 | 2021-01-15 | 西安交通大学 | Self-adaptive variable camber wing trailing edge based on hierarchical piezoelectric stack driving |
| CN112224384B (en) * | 2020-09-12 | 2022-04-05 | 西安交通大学 | Self-adaptive variable camber wing trailing edge based on hierarchical piezoelectric stack driving |
| CN112141318A (en) * | 2020-09-27 | 2020-12-29 | 西北工业大学 | Rear edge bending mechanism based on knuckle type connecting rod driving |
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