CN111907694B - Wing trailing edge and wing with variable camber - Google Patents
Wing trailing edge and wing with variable camber Download PDFInfo
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- CN111907694B CN111907694B CN202010577242.2A CN202010577242A CN111907694B CN 111907694 B CN111907694 B CN 111907694B CN 202010577242 A CN202010577242 A CN 202010577242A CN 111907694 B CN111907694 B CN 111907694B
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- 230000009471 action Effects 0.000 claims description 3
- 230000008859 change Effects 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- 208000002197 Ehlers-Danlos syndrome Diseases 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000006855 networking Effects 0.000 description 2
- 238000005192 partition Methods 0.000 description 2
- 101100134058 Caenorhabditis elegans nth-1 gene Proteins 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
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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
- B64C3/48—Varying camber by relatively-movable parts of wing structures
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
- B64C13/30—Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
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Abstract
The invention provides a variable-camber wing trailing edge and a wing capable of realizing continuous bending of the wing trailing edge, wherein the variable-camber wing trailing edge at least comprises a front sub-wing rib, a rear sub-wing rib and a flexible hinge for connecting the front sub-wing rib and the rear sub-wing rib, the flexible hinge comprises a first cross reed and a second cross reed, and the first cross reed and the second cross reed are arranged in a space cross line mode in the front-rear direction of the wing trailing edge. The trailing edge of the wing adopts a sectional type structure, and adjacent sub-wing ribs are connected through flexible hinges, so that the wing has the advantages of strong flexibility, simple structure and light weight.
Description
Technical Field
The invention belongs to the technical field of aerospace equipment, and particularly relates to a wing trailing edge and a wing with variable camber, wherein the wing trailing edge is continuously bent based on a flexible hinge.
Background
The wings are the lift providers of the aircraft, are important components for determining the flight capability of the aircraft, and have the main function of generating aerodynamic lift and ensuring the performance and the maneuverability of the aircraft in all flight states specified by technical requirements. The traditional fixed rigid wing adopts a flap, a leading edge slat and the like as high lift devices of the wing, and improves the aerodynamic performance of the airplane by changing the camber and the shape of the wing section. However, when the conventional wing is designed, the performance optimization under one specific flight condition is only considered, and the multi-task flight condition is difficult to meet; on the other hand, when the conventional rigid wing deforms, gaps and curvature abrupt changes inevitably occur, so that the continuity of the wing surface is damaged, and the aerodynamic characteristics of the airplane are reduced.
Chinese patent 201410359555.5 discloses a camber-variable trailing edge for an aircraft wing, the aircraft wing including a camber-invariable wing middle, the wing middle including a main beam; the trailing edge of the wing with variable camber comprises a rear beam, a plurality of groups of trailing edge rod group structures arranged in parallel and a trailing edge driving mechanism; the rear beam is connected with the rear end of the main beam; the rear edge driving mechanism comprises a rocker driven by a driving device, one end of the rocker is rotatably connected with the rear beam, and the other end of the rocker is rotatably connected with the rear edge rod group structure; the rear edge rod group structure is a planar rod group structure based on a 5R closed-loop unit and has one degree of freedom; each group of trailing edge rod group structure comprises a plurality of pairs of 5R closed-loop units, a plurality of networking triangular units, 1 tail end 4R closed-loop unit and 1 tail end triangular unit which are in pairs; each pair of 5R closed-loop units comprises an upper 5R closed-loop unit and a lower 5R closed-loop unit; in the prior art, the change of the trailing edge camber is realized by combining a plurality of plane 5R closed-loop units and a plurality of networking triangular units.
Disclosure of Invention
The variable-camber wing trailing edge and the wing provided by the invention can realize continuous bending of the wing trailing edge, the wing trailing edge adopts a sectional structure, and adjacent sub-wing ribs are connected through flexible hinges, so that the variable-camber wing trailing edge has the advantages of strong flexibility, simple structure and light weight.
The technical scheme of the invention is as follows:
the wing trailing edge with variable camber at least comprises a front sub-wing rib, a rear sub-wing rib and a flexible hinge for connecting the front sub-wing rib and the rear sub-wing rib, wherein the flexible hinge comprises a first cross reed and a second cross reed, and the first cross reed and the second cross reed are arranged in a spatial cross line mode in the front-rear direction of the wing trailing edge.
According to another embodiment of the present invention, the front sub-wing rib is provided with a front arc-shaped connection portion facing backward, and the rear sub-wing rib is provided with a rear arc-shaped connection portion facing forward, wherein the front end of the first cross reed is disposed on the front arc-shaped connection portion, the rear end of the first cross reed is disposed on the rear arc-shaped connection portion, the front end of the second cross reed is disposed on the front arc-shaped connection portion, and the rear end of the second cross reed is disposed on the rear arc-shaped connection portion.
According to another embodiment of the present invention, the front and rear ends of the first cross spring have first arc engaging lugs respectively matching the radians of the front arc connecting portion and the rear arc connecting portion, and the front and rear ends of the second cross spring have second arc engaging lugs respectively matching the radians of the front arc connecting portion and the rear arc connecting portion.
According to another embodiment of the invention, the intersection of the first cross spring and the second cross spring is located offset to the trailing sub-rib, the first cross spring and the second cross spring having an X-shape or a V-shape therebetween.
According to another embodiment of the present invention, the first cross spring and the second cross spring are respectively located at the left and right sides of the front sub-rib and the rear sub-rib, and the front sub-rib and the rear sub-rib are in contact with each other and form a rotation fit structure at the contact point.
A wing with variable camber comprises a wing leading edge with invariable camber, more than two wing trailing edges with variable camber and a wing skin, and is characterized in that the wing trailing edge comprises:
n sequentially connected sub-ribs, wherein N is more than or equal to 2;
a flexible hinge connecting two adjacent sub-ribs; and
a drive device;
the flexible hinge comprises a first cross reed and a second cross reed, the first cross reed and the second cross reed are arranged in a space cross line mode in the front-back direction of the trailing edge of the wing to respectively connect the nth-1 sub-wing rib and the nth sub-wing rib, wherein N is more than or equal to 2 and less than or equal to N;
the driving device comprises a connecting rod, a rocker and a driver, wherein the connecting rod is fixedly connected with sub-wing ribs in different wing trailing edges, the driver is fixed on the wing leading edge, one end of the rocker is connected with the connecting rod, the other end of the rocker is connected with the output end of the driver, the middle part of the rocker is connected onto the wing leading edge through a hinged joint, and the driver drives the rocker to rotate around the hinged joint so as to drive the wing trailing edge to perform pitching bending action through the connecting rod.
According to another specific embodiment of the invention, the driver is a steering engine, an eccentric rocker arm is arranged at the output end of the driver, a connecting groove is formed in the other end of the rocker arm, and the rocker arm is arranged in the connecting groove and can slide in the connecting groove.
According to another embodiment of the invention, the number of sub-ribs in the trailing edge of the wing is 3-8.
According to another embodiment of the invention, the wing skin is an elastic skin capable of generating elastic deformation along with the process of generating bending deformation of the wing trailing edge, and the wing skin is connected with the wing leading edge through rivets.
The invention has the following beneficial effects:
the invention can realize the effect of continuously bending the trailing edge of the wing, adjust the camber of the wing in the flying process, change the aerodynamic parameters such as lift-drag ratio and the like, and realize that the airplane obtains better aerodynamic efficiency under different flying conditions.
In addition, the wing ribs of the wing adopt a sectional design and a softening design, have simple structure and lighter weight, and avoid a series of problems of hinge clearance, friction force and the like of a rigid structure.
In addition, the first cross spring leaf, the second cross spring leaf, the front sub-wing rib and the rear sub-wing rib adopt circular arc connection structures, the connection matching degree is high, and the fastening connection effect is achieved under any bending condition. Meanwhile, the rigidity of the trailing edge of the wing can be changed by replacing the first cross reed and the second cross reed with different thicknesses so as to adapt to the requirements of different flight conditions of the airplane.
In addition, the invention has larger deformation range, larger bearing capacity because the rigid driving device bears the air load, simple structure and easy maintenance.
The present invention will be described in further detail with reference to the accompanying drawings.
Drawings
FIG. 1 is a schematic structural view of an airfoil of the present invention;
FIG. 2 is a schematic view of the present invention showing the trailing edge of the airfoil;
FIG. 3 is a schematic view of the present invention showing two adjacent sub-ribs;
FIG. 4 is an exploded view of two of the sub-ribs of FIG. 3;
FIG. 5 is a schematic view of the display drive mechanism of the present invention;
FIG. 6 is a simplified schematic illustration of the invention with the trailing edge curved downward.
Detailed Description
A variable camber wing, as shown in fig. 1-6, includes a camber-invariant leading edge 100, a variable camber trailing edge 200, and a wing skin.
The wing skin (not shown) in this example is riveted to the leading edge 100, and in order to better follow the camber change of the trailing edge 200, the wing skin is made of an elastic skin to generate adaptive deformation when the trailing edge 200 is cambered.
The trailing edge 200 includes five sub-ribs 210 connected in sequence, two adjacent sub-ribs 210 are connected by a flexible hinge 220, and the five sub-ribs 210 are bent upward or downward by the driving of a driving device 230, wherein, in order to adapt to the shape of the trailing edge 200, the five sub-ribs 210 are not identical in shape, see fig. 1 and 2, a first sub-rib 210a, a second sub-rib 210b, a third sub-rib 210c, a fourth sub-rib 210d and a fifth sub-rib 210e, wherein the first sub-rib 210a, the second sub-rib 210b, the third sub-rib 210c and the fourth sub-rib 210d respectively approximately present a ladder shape, and the fifth sub-rib 210e approximately presents a triangle shape.
The following describes a connection structure between the third sub-rib 210c and the fourth sub-rib 210:
as shown in fig. 3 and 4, the flexible hinge 220 includes a first cross spring 221 and a second cross spring 222, and the first cross spring 221 and the second cross spring 222 are arranged so as to spatially intersect with each other in the front-rear direction of the trailing edge 200.
In order to improve the connection matching degree between the first cross reed 221 and the second cross reed 222 and the third sub-rib 210c and the fourth sub-rib 210, the present example adopts a circular arc connection structure.
The third sub-rib 210c is provided with a front arc-shaped connecting portion 211 facing backward, the fourth sub-rib 210d is provided with a rear arc-shaped connecting portion 212 facing forward, the front end of the first cross reed 221 is disposed on (specifically, clamped to) the front arc-shaped connecting portion 211, the rear end of the first cross reed 221 is disposed on the rear arc-shaped connecting portion 212, the front end of the second cross reed 222 is disposed on the front arc-shaped connecting portion 211, and the rear end of the second cross reed 222 is disposed on the rear arc-shaped connecting portion 212.
The front and rear ends of the first cross spring piece 221 have first arc-shaped engaging lugs 223 respectively matching the radians of the front arc-shaped connecting portion 211 and the rear arc-shaped connecting portion 212, and the front and rear ends of the second cross spring piece 222 have second arc-shaped engaging lugs (similar to the first arc-shaped engaging lugs 223, not shown) respectively matching the radians of the front arc-shaped connecting portion 211 and the rear arc-shaped connecting portion 212.
The intersection of first cross reed 221 and second cross reed 222 in this example is located offset from fourth sub-rib 210d, with first cross reed 221 and second cross reed 222 in the X-shaped configuration shown in fig. 2.
Referring to fig. 3 again, in the present example, the first cross reed 221 and the second cross reed 222 are respectively located at the left and right sides of the third sub-rib 210c and the fourth sub-rib 210d, the third sub-rib 210c and the fourth sub-rib 210d are in contact with each other and form a rotation fit structure at the contact point, specifically, a connection angle 213 is provided on the third sub-rib 210c, and a limit groove 214 is provided on the fourth sub-rib 210d, wherein the connection angle 213 is located in the limit groove 214 and can generate a rotation displacement in the limit groove 214.
As shown in fig. 1 and 5, the driving device 230 includes a connecting rod 231, a rocker 232, a steering gear 233, and a rocker arm 234.
The connecting rod 231 is fixedly connected with the sub wing ribs 210 (specifically, connected to the fifth sub wing rib 210) in different wing trailing edges 200, the wing box 300 is arranged on the wing leading edge 100, the wing box 300 is provided with a partition plate 310 and a fixing frame 320, the steering gear 233 is fixed on the partition plate 310 and located in the wing box 300, the rocker arm 234 is arranged at the output end of the steering gear 233 in an eccentric mode, one end of the rocker arm 232 is connected with the connecting rod 231, the other end of the rocker arm 232 is provided with a connecting groove 232a, the rocker arm 234 is arranged in the connecting groove 232a and can slide in the connecting groove 232a, the rocker arm 232 is connected to the fixing frame 320 through a hinge point 235, and the rotation of the steering gear 233 can drive the rocker arm 232 to rotate around the hinge point 235, so that the connecting rod 231 drives the wing trailing edge 200 to perform downward bending motion and upward bending motion.
Specifically, when the wing needs to be deformed, the steering engine 233 rotates according to a set direction, and the rocker arm 232 is driven by the rocker arm 234 to rotate around the hinge point 235, and since the rocker arm 232 is fixedly connected with the connecting rod 231 (specifically, a carbon fiber rod), and the connecting rod 231 is fixedly connected with the sub-wing rib 210 in the wing trailing edge 200, the rotation of the rocker arm 232 can drive the wing rib trailing edge 200 to move together.
Each group of the first cross reed 221 and the second cross reed 222 in the wing rib trailing edge 200 forms a flexible hinge 220, and each flexible hinge 220 is bent under the action of the driving device 230, so that the wing rib trailing edge 200 is bent upwards or downwards section by section, and the wing bending process is realized.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the scope of the invention. It will be appreciated by those skilled in the art that variations may be made without departing from the scope of the invention, and equivalents may be resorted to without departing from the scope of the invention.
Claims (7)
1. The wing trailing edge with variable camber is characterized by at least comprising a front sub-wing rib, a rear sub-wing rib and a flexible hinge for connecting the front sub-wing rib and the rear sub-wing rib, wherein the flexible hinge comprises a first cross reed and a second cross reed, the first cross reed and the second cross reed are arranged in a spatial cross line mode in the front-rear direction of the wing trailing edge, and the position of a cross point of the first cross reed and the second cross reed is offset to the rear sub-wing rib;
the front sub-wing rib is provided with a front arc-shaped connecting part facing the rear, the rear sub-wing rib is provided with a rear arc-shaped connecting part facing the front, the front end of the first cross reed is arranged on the front arc-shaped connecting part, the rear end of the first cross reed is arranged on the rear arc-shaped connecting part, the front end of the second cross reed is arranged on the front arc-shaped connecting part, and the rear end of the second cross reed is arranged on the rear arc-shaped connecting part;
the front end and the rear end of the first cross reed are provided with first arc-shaped connecting lugs which are respectively matched with the radians of the front arc-shaped connecting part and the rear arc-shaped connecting part, and the front end and the rear end of the second cross reed are provided with second arc-shaped connecting lugs which are respectively matched with the radians of the front arc-shaped connecting part and the rear arc-shaped connecting part.
2. The variable camber trailing edge of claim 1, wherein the first cross-spring and the second cross-spring are X-shaped or V-shaped therebetween.
3. The variable camber trailing edge of claim 1, wherein the first cross reed and the second cross reed are located on the left and right sides of the leading sub-rib and the trailing sub-rib, respectively, and the leading sub-rib and the trailing sub-rib contact each other to form a running fit at the contact point.
4. A variable camber airfoil comprising a camber-invariant airfoil leading edge, two or more variable camber airfoil trailing edges, and an airfoil skin, wherein the airfoil trailing edges comprise:
n sequentially connected sub-ribs, wherein N is more than or equal to 2;
a flexible hinge connecting two adjacent sub-ribs; and
a drive device;
the flexible hinge comprises a first cross reed and a second cross reed, the first cross reed and the second cross reed are arranged in a spatial cross line mode in the front-back direction of the trailing edge of the wing to respectively connect the (N-1) th sub-wing rib and the nth sub-wing rib, wherein N is more than or equal to 2 and less than or equal to N, and the position of the cross point of the first cross reed and the second cross reed is offset to the nth sub-wing rib;
the driving device comprises a connecting rod, a rocker and a driver, wherein the connecting rod is fixedly connected with the sub-wing ribs in different wing trailing edges, the driver is fixed on the wing leading edge, one end of the rocker is connected with the connecting rod, the other end of the rocker is connected with the output end of the driver, an eccentric rocker arm is arranged at the output end of the driver, a connecting groove is formed in the other end of the rocker, the rocker arm is arranged in the connecting groove and can slide in the connecting groove, the middle part of the rocker is connected to the wing leading edge through a hinge joint, and the driver drives the rocker to rotate around the hinge joint so as to drive the wing trailing edge to perform pitching bending action through the connecting rod.
5. The variable camber airfoil of claim 4, wherein the actuator is a steering engine.
6. The variable camber wing according to claim 4, wherein the number of sub-ribs in the trailing edge is 3-8.
7. The variable camber wing of claim 4, wherein the wing skin is an elastomeric skin capable of elastically deforming in response to the camber process at the trailing edge of the wing, the wing skin being attached to the leading edge of the wing by rivets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010577242.2A CN111907694B (en) | 2020-06-22 | 2020-06-22 | Wing trailing edge and wing with variable camber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010577242.2A CN111907694B (en) | 2020-06-22 | 2020-06-22 | Wing trailing edge and wing with variable camber |
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| Publication Number | Publication Date |
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| CN111907694A CN111907694A (en) | 2020-11-10 |
| CN111907694B true CN111907694B (en) | 2022-02-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010577242.2A Active CN111907694B (en) | 2020-06-22 | 2020-06-22 | Wing trailing edge and wing with variable camber |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101868407A (en) * | 2007-11-21 | 2010-10-20 | 空中客车营运有限公司 | Landing flap mechanism driven by pinion gears |
| JP2011178292A (en) * | 2010-03-02 | 2011-09-15 | Fuji Heavy Ind Ltd | Moving blade |
| CN105605090A (en) * | 2016-02-14 | 2016-05-25 | 西安电子科技大学 | Zero-pivot and large-corner crossed reed type flexible hinge |
| CN109050878A (en) * | 2018-08-01 | 2018-12-21 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of continuous variable camber structure of aircraft and its distributing drive control method |
| CN109502008A (en) * | 2017-09-15 | 2019-03-22 | 空中客车作业有限公司 | Actuating mechanism, control surface and the aircraft with flexible control surface |
| CN110053760A (en) * | 2019-04-11 | 2019-07-26 | 哈尔滨工业大学（深圳） | A kind of plastic deformation wing |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7229049B2 (en) * | 2004-05-04 | 2007-06-12 | Lockheed Martin Corporation | Unitized rotary actuator hinge fitting |
| DE102004056649A1 (en) * | 2004-11-24 | 2006-06-01 | Airbus Deutschland Gmbh | Covering skin for a shape-variable aerodynamic surface |
| EP3272635B1 (en) * | 2016-07-22 | 2020-01-08 | Giovanni Galeotti | Foil hinge system |
-
2020
- 2020-06-22 CN CN202010577242.2A patent/CN111907694B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101868407A (en) * | 2007-11-21 | 2010-10-20 | 空中客车营运有限公司 | Landing flap mechanism driven by pinion gears |
| JP2011178292A (en) * | 2010-03-02 | 2011-09-15 | Fuji Heavy Ind Ltd | Moving blade |
| CN105605090A (en) * | 2016-02-14 | 2016-05-25 | 西安电子科技大学 | Zero-pivot and large-corner crossed reed type flexible hinge |
| CN109502008A (en) * | 2017-09-15 | 2019-03-22 | 空中客车作业有限公司 | Actuating mechanism, control surface and the aircraft with flexible control surface |
| CN109050878A (en) * | 2018-08-01 | 2018-12-21 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of continuous variable camber structure of aircraft and its distributing drive control method |
| CN110053760A (en) * | 2019-04-11 | 2019-07-26 | 哈尔滨工业大学（深圳） | A kind of plastic deformation wing |
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| CN111907694A (en) | 2020-11-10 |
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