CN111907693B - Wing with variable camber - Google Patents
Wing with variable camber Download PDFInfo
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- CN111907693B CN111907693B CN202010577241.8A CN202010577241A CN111907693B CN 111907693 B CN111907693 B CN 111907693B CN 202010577241 A CN202010577241 A CN 202010577241A CN 111907693 B CN111907693 B CN 111907693B
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- rod
- wing
- trailing edge
- scissor
- camber
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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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Abstract
The invention provides a variable-camber wing capable of realizing continuous bending of a wing trailing edge, which comprises a wing front section with invariable camber, a wing trailing edge section with variable camber and a wing skin, wherein the wing trailing edge section comprises a plurality of wing rib joints which are sequentially connected in series, and each wing rib joint comprises a plurality of closed loop rod mechanisms arranged side by side, a parallel rod mechanism used for synchronous linkage among the closed loop rod mechanisms, a scissor mechanism used for driving the closed loop rod mechanisms to pitch and rotate, and a driving mechanism used for driving the scissor mechanism to extend and shorten. Based on the characteristic that the scissor mechanism can be extended and shortened, the invention can realize large-amplitude bending in the upper direction and the lower direction, thereby improving the pressure distribution of the wing, improving the maximum lift coefficient of the wing and widening the adaptability of the airplane to different cruising conditions.
Description
Technical Field
The invention belongs to the technical field of aerospace equipment, and particularly relates to a wing with variable camber, which can realize continuous bending of the trailing edge of the wing.
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 invention provides a variable-camber wing capable of realizing continuous bending of a wing trailing edge, which can realize large-amplitude bending in the upper direction and the lower direction based on the characteristic that a scissor mechanism can be extended and shortened, thereby improving the pressure distribution of the wing, improving the maximum lift coefficient of the wing and widening the adaptability of an airplane to different cruising conditions.
The technical scheme of the invention is as follows:
the utility model provides a wing of variable camber, includes the wing anterior segment of the unchangeable wing of camber, the wing trailing edge section of variable camber, wing covering, and wherein, wing trailing edge section includes a plurality of rib joints of establishing ties in proper order, and the rib joint includes:
a plurality of closed loop lever mechanisms arranged side by side;
the closed loop rod mechanism comprises a first vertical rod, an upper transverse rod, a second vertical rod, a lower sliding rod and a lower transverse rod which are sequentially connected end to end, wherein the first vertical rod is fixedly connected with the upper transverse rod, the upper transverse rod is connected with the second vertical rod through a first hinge point, the second vertical rod is connected with the lower sliding rod through a second hinge point, the lower sliding rod is connected with the lower transverse rod in a sliding manner, and the lower transverse rod is connected with the first vertical rod through a third hinge point;
a parallel bar mechanism for synchronous linkage between a plurality of closed loop bar mechanisms;
the parallel rod mechanism comprises a first connecting rod and a second connecting rod, the first connecting rod penetrates through second hinge points in the plurality of closed-loop rod mechanisms, and the second connecting rod penetrates through third hinge points in the plurality of closed-loop rod mechanisms;
the scissor mechanism is used for driving the closed loop rod mechanisms to rotate in a pitching mode;
the scissor mechanism comprises two scissor rods, two first sliding blocks and two second sliding blocks which are mutually hinged, the two first sliding blocks are arranged on the first connecting rod in a sliding mode and are respectively hinged with one ends of the two scissor rods, and the two second sliding blocks are arranged on the second connecting rod in a sliding mode and are respectively hinged with the other ends of the two scissor rods;
and a driving mechanism for driving the scissors mechanism to extend and contract.
In the technical scheme of the invention, a plurality of rib joints connected in series can relatively generate upward or downward bending so as to realize the bending change of the trailing edge section of the wing.
The lower cross rod and the lower sliding rod in the closed loop rod mechanism can slide relatively, and the relative position between the lower cross rod and the lower sliding rod is adjusted by extending and shortening the scissor fork mechanism so as to change the integral form of the closed loop rod mechanism and realize the rotation of the second vertical rod relative to the first vertical rod.
According to another embodiment of the invention, the driving mechanism drives the two scissor rods to extend, so as to drive the lower sliding rod to slide and extend relative to the lower cross rod to perform upward bending action; the driving mechanism drives the two scissor rods to shorten and drives the lower sliding rod to slide and retract relative to the lower cross rod so as to perform downward bending action.
According to another embodiment of the present invention, the scissors mechanism further comprises a fixing block for fixing the position of one of the first sliding blocks, the fixing block is mounted on the first connecting rod, and the extension and contraction processes of the scissors mechanism are better driven by fixing one of the first sliding blocks.
According to another specific embodiment of the invention, the driving mechanism comprises a hydraulic rod, the fixed end of the hydraulic rod is installed on the fixed block, the driving end of the hydraulic rod is connected with the other first sliding block, the distance between the two first sliding blocks is changed by directly driving the other first sliding block to slide, the folding and extending actions of the two scissor rods are realized, and finally the change of the camber of the trailing edge section of the whole wing is realized.
According to another embodiment of the invention, the length of the second vertical rod is smaller than that of the first vertical rod, and the closed loop rod mechanisms which are connected in series share one second vertical rod to adapt to the shape of the trailing edge section of the wing.
According to another embodiment of the invention, the bottom rail is provided with an open slot, one end of the bottom rail extending into the slot and being slidable therein.
According to another embodiment of the invention, the trailing edge section of the wing comprises more than two rib knuckles, each rib knuckle comprising more than three closed loop lever mechanisms.
According to another embodiment of the invention, the wing skin is connected to the wing front section by rivets.
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 section.
The invention has the following beneficial effects:
the invention can realize the effect of continuous bending of the trailing edge of the wing;
in addition, based on the characteristic that the scissor mechanism can be extended and shortened, the invention can realize large bending change in the upper direction and the lower direction, thereby improving the pressure distribution of the wings, improving the maximum lift coefficient of the wings and widening the adaptability of the airplane to different cruising conditions;
in addition, the invention can be used as an aileron and can provide larger rolling moment;
in addition, the invention has the characteristic of sectional modularization, is formed by connecting the same units in series, can realize more flexible design and application, can meet the design requirement only by expanding basic units for wings with different dimensions, and has the advantages of strong expansibility, simple structure, high reliability and convenient maintenance and replacement.
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 a trailing edge section of the airfoil;
FIG. 3 is a schematic view of the present invention showing a scissors mechanism;
FIG. 4 is a schematic view of the display drive mechanism of the present invention;
FIG. 5 is a schematic view of the present invention showing a plurality of closed loop lever mechanisms connected in series;
FIG. 6 is a schematic view of the inventive wing trailing edge section curved downwardly;
FIG. 7 is a schematic view of the configuration of the invention with the trailing edge section curved upward.
Detailed Description
A variable camber wing, as shown in fig. 1-7, includes a camber-invariant wing forward section 100, a variable camber wing trailing section 200, and a wing skin 300.
The wing skin 300 in this example is riveted to the wing front section 100, and in order to better follow the curvature change of the wing trailing edge section 200, the wing skin 300 is made of an elastic skin to generate adaptive deformation when the wing trailing edge section 200 is bent.
The wing trailing edge section 200 comprises three rib joints 200a, 200b and 200c connected in series, and the structure of the rib joint 200a closest to the wing leading edge is described in detail below by taking the rib joint 200a as an example, and the rib joint 200a comprises four closed-loop rod mechanisms 210, a parallel rod mechanism 220, a scissor mechanism 230 and a driving mechanism 240.
As shown in fig. 5, the closed loop lever mechanism 210 includes a first vertical lever 211, an upper horizontal lever 212, a second vertical lever 213, a lower horizontal lever 214, and a lower horizontal lever 215 connected end to end in sequence, the first vertical lever 211 and the upper horizontal lever 212 are fixedly connected, the upper horizontal lever 212 and the second vertical lever 213 are connected through a first hinge point R1, the second vertical lever 213 and the lower horizontal lever 214 are connected through a second hinge point R2, the lower horizontal lever 214 and the lower horizontal lever 215 are connected in a sliding manner, and the lower horizontal lever 215 and the first vertical lever 211 are connected through a third hinge point R3;
wherein, the bottom rail 215 is provided with an open slot, and one end of the bottom rail 214 extends into the slot and can slide in the slot to change the relative position of the second vertical bar 213 and the first vertical bar 211.
Further, the length of the second vertical rod 213 is smaller than that of the first vertical rod 211 to adapt to the shape of the trailing edge section 200 which is gradually flattened backwards.
The parallel lever mechanism 220 serves as a synchronous linkage between the plurality of closed-loop lever mechanisms 210, and as shown in fig. 3, includes a first link 221 and a second link 222 that are parallel to each other, the first link 221 extending through the second hinge point R2 in the four closed-loop lever mechanisms 210, and the second link 222 extending through the third hinge point R3 in the four closed-loop lever mechanisms 210.
The scissor mechanism 230 is used for driving the plurality of closed-loop lever mechanisms 210 to tilt and rotate to complete the camber adjustment of the trailing edge section 200 of the wing, as shown in fig. 4, the scissor mechanism 230 includes two scissor levers 231 hinged to each other, two first sliders 232, and two second sliders 233, the two first sliders 232 are slidably disposed on the first link 221 and hinged to one end of the two scissor levers 231, respectively, and the two second sliders 233 are slidably disposed on the second link 222 and hinged to the other end of the two scissor levers 231, respectively.
The driving mechanism 240 is used for driving the scissors mechanism 230 to extend and contract, and includes a fixed block 241 and a hydraulic rod 242, as shown in fig. 4, the fixed block 241 is fixed on the first link 221 and used for limiting the position of one of the first sliders 232-1 so as to be fixed relative to the first link 221, the fixed end of the hydraulic rod 242 is mounted on the fixed block 241, the driving end of the hydraulic rod 242 is connected with the other first slider 232-2, the distance between the two first sliders 232 is changed by directly driving the other first slider 232-2 to slide, so that the folding and extending actions of the two scissors rods 231 are realized, and finally the bending change of the whole wing trailing edge section 200 is realized.
In this example, the adjacent closed-loop bar mechanisms 210 share the same second vertical bar, and the adjacent parallel bar mechanisms 220 share the same connecting bar (the second connecting bar in the previous parallel bar mechanism 220 is the first connecting bar in the next parallel bar mechanism 220), as shown in fig. 5, so as to simplify the structure, wherein the first vertical bar 211 and the upper bar 212 can be preformed to be made in a modular manner.
Specifically, in this example, the wing is in a normal state, the scissors mechanism 230 is in a middle position, and the two scissors rods 231 in the scissors mechanism 230 can be extended or shortened.
As shown in fig. 6, by driving the two scissor links 231 to shorten in the chord direction, the distance between the first link 221 and the second link 222 is shortened, which drives the lower slide bar 214 to slide and retract relative to the lower cross bar 215, and at this time, the second vertical bar 213 in the single closed-loop bar mechanism 210 rotates downward relative to the first vertical bar 211 around the first hinge point R1, so as to realize the downward bending action of the three rib joints 200 as a whole.
As shown in fig. 7, by driving the two scissor links 231 to extend along the chord direction, the distance between the first link 221 and the second link 222 increases, which drives the lower slide bar 214 to slide and extend relative to the lower cross bar 215, and at this time, the second vertical bar 213 in the single closed-loop bar mechanism 210 rotates upward relative to the first vertical bar 211 around the first hinge point R1, so as to realize the upward bending action of the three rib joints 200 as a whole.
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 utility model provides a wing of variable camber, includes the invariable wing anterior segment of camber, the wing trailing edge section of variable camber, wing covering, its characterized in that, the wing trailing edge section includes a plurality of rib joints that establish ties in proper order, the rib joint includes:
a plurality of closed loop lever mechanisms arranged side by side;
the closed loop rod mechanism comprises a first vertical rod, an upper transverse rod, a second vertical rod, a lower sliding rod and a lower transverse rod which are sequentially connected end to end, wherein the first vertical rod is fixedly connected with the upper transverse rod, the upper transverse rod is connected with the second vertical rod through a first hinge point, the second vertical rod is connected with the lower sliding rod through a second hinge point, the lower sliding rod is connected with the lower transverse rod in a sliding manner, and the lower transverse rod is connected with the first vertical rod through a third hinge point;
the lower cross bar is provided with an open groove, and one end of the lower sliding rod extends into the groove and can slide in the groove;
a parallel bar mechanism for synchronous linkage between a plurality of said closed loop bar mechanisms;
the parallel rod mechanism comprises a first connecting rod and a second connecting rod, the first connecting rod penetrates through a second hinge point in the plurality of closed-loop rod mechanisms, and the second connecting rod penetrates through a third hinge point in the plurality of closed-loop rod mechanisms;
the scissor mechanism is used for driving a plurality of closed-loop rod mechanisms to rotate in a pitching mode;
the scissor mechanism comprises two scissor rods, two first sliding blocks and two second sliding blocks which are hinged with each other, the two first sliding blocks are arranged on the first connecting rod in a sliding mode and are hinged with one ends of the two scissor rods respectively, and the two second sliding blocks are arranged on the second connecting rod in a sliding mode and are hinged with the other ends of the two scissor rods respectively;
and
the driving mechanism is used for driving the scissors mechanism to extend and shorten;
the driving mechanism drives the two scissor rods to extend, and drives the lower sliding rod to slide and extend relative to the lower cross rod so as to perform upward bending action; the driving mechanism drives the two scissor rods to shorten, and drives the lower sliding rod to slide and retract relative to the lower cross rod so as to bend downwards.
2. The variable camber airfoil of claim 1, wherein the scissor mechanism further comprises a fixed block for fixing a position of one of the first sliders, the fixed block being mounted on the first link.
3. The variable camber airfoil of claim 2, wherein the drive mechanism comprises a hydraulic rod, a fixed end of the hydraulic rod being mounted to the fixed block, and a drive end of the hydraulic rod being coupled to the other of the first sliders.
4. The variable camber airfoil of claim 1, wherein the length of the second vertical rod is less than the length of the first vertical rod, one of the second vertical rods being shared between the closed loop rod mechanisms in series.
5. The variable camber wing according to claim 1, wherein the wing trailing edge section comprises more than two rib knuckles, each rib knuckle comprising more than three closed loop lever mechanisms.
6. The variable camber wing according to claim 1, wherein the wing skin is connected to the wing forward section by rivets.
7. The variable camber wing of claim 1, wherein the wing skin is an elastomeric skin capable of elastic deformation in response to a camber process of the trailing edge section of the wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010577241.8A CN111907693B (en) | 2020-06-22 | 2020-06-22 | Wing with variable camber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010577241.8A CN111907693B (en) | 2020-06-22 | 2020-06-22 | Wing with variable camber |
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| Publication Number | Publication Date |
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| CN111907693A CN111907693A (en) | 2020-11-10 |
| CN111907693B true CN111907693B (en) | 2022-02-22 |
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| CN202010577241.8A Active CN111907693B (en) | 2020-06-22 | 2020-06-22 | Wing with variable camber |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112340016B (en) * | 2020-11-23 | 2022-09-16 | 西湖大学 | A rib structure, a wing structure and a flapping air vehicle |
| CN112520013B (en) * | 2020-12-16 | 2022-02-25 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Deformable wing with variable bending degree based on connecting rod driving |
| KR102509302B1 (en) * | 2021-07-07 | 2023-03-10 | 서울대학교산학협력단 | Variable Wing Rib and Method for Setting the Variable Wing Rib |
| CN114148505A (en) * | 2021-11-30 | 2022-03-08 | 中国运载火箭技术研究院 | Composite hinge-containing continuously-variable-camber wing structure for high-speed aircraft |
| CN114313216B (en) * | 2022-02-18 | 2023-12-15 | 上海力鸿航空科技有限公司 | Bending and twisting movement mechanism based on bidirectional bending scissor rod mechanism |
| CN114802702B (en) * | 2022-05-07 | 2025-02-25 | 江苏科技大学 | A single-degree-of-freedom, few-actuated, fully deformable wing mechanism based on multiple links |
| CN115042955A (en) * | 2022-05-09 | 2022-09-13 | 中国空气动力研究与发展中心空天技术研究所 | A Wing with Continuously Bendable Rigid Skin |
Citations (6)
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|---|---|---|---|---|
| GB472567A (en) * | 1936-08-31 | 1937-09-27 | Horace Charles Luttman | Improvements in aerofoils with variable camber |
| US4113210A (en) * | 1976-04-01 | 1978-09-12 | The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland | Flexible aerofoils |
| US6276641B1 (en) * | 1998-11-17 | 2001-08-21 | Daimlerchrysler Ag | Adaptive flow body |
| CN106275388A (en) * | 2015-12-10 | 2017-01-04 | 哈尔滨工业大学深圳研究生院 | A kind of based on planar linkage closed-loop element containing hinge deformable trailing edge mechanism again |
| CN108100228A (en) * | 2017-11-30 | 2018-06-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of active flexible Telescopic truss structure |
| CN109877809A (en) * | 2019-04-10 | 2019-06-14 | 中国科学院沈阳自动化研究所 | A bidirectional self-adaptive telescopic manipulator |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE602004029655D1 (en) * | 2003-03-03 | 2010-12-02 | Flexsys Inc | Adaptives flexibles flügel- und rotorsystem |
| US8418967B2 (en) * | 2008-02-21 | 2013-04-16 | Cornerstone Research Group, Inc. | Passive adaptive structures |
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2020
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB472567A (en) * | 1936-08-31 | 1937-09-27 | Horace Charles Luttman | Improvements in aerofoils with variable camber |
| US4113210A (en) * | 1976-04-01 | 1978-09-12 | The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland | Flexible aerofoils |
| US6276641B1 (en) * | 1998-11-17 | 2001-08-21 | Daimlerchrysler Ag | Adaptive flow body |
| CN106275388A (en) * | 2015-12-10 | 2017-01-04 | 哈尔滨工业大学深圳研究生院 | A kind of based on planar linkage closed-loop element containing hinge deformable trailing edge mechanism again |
| CN108100228A (en) * | 2017-11-30 | 2018-06-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of active flexible Telescopic truss structure |
| CN109877809A (en) * | 2019-04-10 | 2019-06-14 | 中国科学院沈阳自动化研究所 | A bidirectional self-adaptive telescopic manipulator |
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| CN111907693A (en) | 2020-11-10 |
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