CN107972847B - Aircraft wing folding mechanism and flap mechanism based on same - Google Patents
Aircraft wing folding mechanism and flap mechanism based on same Download PDFInfo
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- CN107972847B CN107972847B CN201711056080.2A CN201711056080A CN107972847B CN 107972847 B CN107972847 B CN 107972847B CN 201711056080 A CN201711056080 A CN 201711056080A CN 107972847 B CN107972847 B CN 107972847B
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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
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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Abstract
The invention discloses an aircraft wing folding mechanism and a cover mechanism based on the same, and mainly solves the problems that in the prior art, the existing wing folding causes the wing joint surface to be uneven, and no cover or cover structure is complex. The aircraft wing folding mechanism comprises an inner wing, an outer wing and a folding actuator; the folding actuator is positioned between the inner wing and the outer wing and is respectively hinged with the upper parts of the end surfaces of the inner wing and the outer wing; the folding actuator is provided with two output ends, and a first-stage revolute pair and a second-stage revolute pair are respectively hinged between the two output ends and the lower parts of the end surfaces of the inner wing and the outer wing. Through the scheme, the purpose of flattening the joint surface of the wing is achieved, and the wing joint surface flattening device has high practical value and popularization value.
Description
Technical Field
The invention relates to the technical field of airborne equipment, in particular to an aircraft wing folding mechanism and a cover mechanism based on the aircraft wing folding mechanism.
Background
The folding of the wings of the airplane is realized by rotating a part of the wings for a certain angle and then turning and folding the wings, so that the wingspan of the airplane is reduced, and the space required by parking the airplane is reduced. The wing folding technology can not only meet the purpose of saving deck space of the carrier-based aircraft, but also increase the carrying capacity. The occupied space during the transportation and the storage of the airplane storeroom can be effectively reduced, and the airplane storage rack has certain significance for the use of various small and medium-sized airplanes.
The wing folding mechanisms of the airplane in the prior art all adopt a single hinge mode, a rotating shaft of an outer section of the wing is perpendicular to the wingspan direction and is positioned at the upper part of a wing skin, and in order to avoid movement interference of a folding part, the rotating shaft of the single hinge folding mode usually protrudes out of the surface of the wing, so that the wing joint surface is uneven; on the other hand, the wing folding mechanism is easy to cause movement interference among parts, and a larger gap is left at the folding position after the wing is unfolded, which have adverse effects on the wing structure and the aerodynamic characteristics of the airplane.
In the prior art, the flap can be designed to fill up the wing surface gap generated by the folding mechanism, but the flap can enlarge the bulge of the folding part, and meanwhile, the folding and unfolding movement of the flap part needs to be driven by a special actuator and a link mechanism, so that not only is the structure complex, but also the movement of the flap needs to be matched with the folding mechanism, and therefore the movement of related mechanisms is difficult to control.
Disclosure of Invention
The invention aims to provide an aircraft wing folding mechanism and a cover mechanism based on the aircraft wing folding mechanism, and aims to solve the problems that the surface of a folding part of a wing is convex, no cover exists in a gap position or a cover driving structure is complex, and the movement control difficulty is high due to the existing wing folding technology.
In order to solve the above problems, the present invention provides the following technical solutions:
an aircraft wing folding mechanism comprises an inner wing, an outer wing and a folding actuator; the folding actuator is positioned between the inner wing and the outer wing and is respectively hinged with the upper parts of the end surfaces of the inner wing and the outer wing; the folding actuator is provided with two output ends, and a first-stage revolute pair and a second-stage revolute pair are respectively hinged between the two output ends and the lower parts of the end surfaces of the inner wing and the outer wing.
The first rotating pair comprises a first-stage driving rod connected with the output end of the folding actuator, and the free end of the first-stage driving rod is hinged with a first rocker arm; the first rocker arm is hinged with the lower part of the end surface of the inner wing.
Specifically, the second revolute pair comprises a second-stage driving rod connected with the output end of the folding actuator, and the free end of the second-stage driving rod is hinged with a second rocker arm; the second rocker arm is hinged with the lower part of the end surface of the outer wing.
A flap mechanism based on an aircraft wing folding mechanism comprises a flap arranged above a folding actuator; the middle part of the folding actuator is provided with an extending end, and a revolute pair for pushing the opening and closing of the opening cover is hinged between the extending end and the opening cover.
Specifically, the revolute pair comprises a connecting rod hinged with one end of the extending end of the folding actuator, and the other end of the connecting rod is hinged with an ear-shaped rocker arm; the ear-shaped rocker arm is fixedly connected with the opening cover.
Specifically, the flap surface is flush with the upper airfoil surfaces of both the inner and outer wings.
Compared with the prior art, the invention has the following beneficial effects: the double-hinge folding structure is adopted, so that the situation that a rotating shaft protrudes out of the surface of the wing due to the fact that single-hinge folding is adopted can be avoided, a protruding part is formed at the folding position, aerodynamic resistance in the flight process is reduced, the opening cover is driven to turn over when the actuator completes first-stage wing folding, the requirement of follow-up motion is met, the problems of gaps between the outer wing and the inner wing and interference between the opening cover and the inner wing are solved, the redundant actuator is avoided being used due to the adoption of a linkage mode, and the double-hinge folding structure has the advantages of being simple in structure, reliable in motion control, light in weight and the like.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic structural diagram of the first stage folding of the present invention.
In the drawings, the names of the parts corresponding to the reference numerals are as follows:
1-inner wing, 2-ear type rocker arm, 3-connecting rod, 4-opening cover, 5-folding actuator, 6-outer wing, 7-second rocker arm, 8-second stage driving rod, 9-extending end, 10-first rocker arm and 11-first stage driving rod.
Detailed Description
The present invention is further illustrated by the following figures and examples, which include, but are not limited to, the following examples.
As shown in fig. 1 and 2, an aircraft wing folding mechanism includes an inner wing 1, an outer wing 6, and a folding actuator 5; the folding actuator 5 is positioned between the inner wing 1 and the outer wing 6 and is respectively hinged with the upper parts of the end surfaces of the inner wing 1 and the outer wing 6; the folding actuator 5 is provided with two output ends, and a first-stage rotating pair and a second-stage rotating pair are respectively hinged between the two output ends and the lower parts of the end surfaces of the inner wing 1 and the outer wing 6; the structure forms a double-hinge rotating structure, so that the condition that the folding rotating shaft protrudes out of the surface of the wing can be effectively avoided, the flat joint surface of the unfolded wing is ensured, and the aerodynamic resistance in the flying process is reduced.
In a preferred embodiment of the present invention, the first revolute pair comprises a first-stage driving lever 11 connected to the output end of the folding actuator 5, the free end of the first-stage driving lever 11 being hinged to a first rocker arm 10; the first rocker arm 10 is hinged with the lower part of the end surface of the inner wing 1.
In a preferred embodiment of the present invention, the second revolute pair includes a second-stage driving lever 8 connected to the output end of the folding actuator 5, and a second swing arm 7 is hinged to a free end of the second-stage driving lever 8; the second rocker arm 7 is hinged with the lower part of the end surface of the outer wing 6.
A flap 4 mechanism based on an airplane wing folding mechanism comprises a flap 4 arranged above a folding actuator 5; an extending end 9 is arranged in the middle of the folding actuator 5, and a rotating pair for pushing the opening cover 4 to open and close is hinged between the extending end 9 and the opening cover 4; the driving of the opening cover 4 adopts a linkage mode, a special actuator is not needed, the working reliability is high, and the overall weight of the folding system is reduced; folding actuator 5 accomplishes the folding while of first stage wing, drives flap 4 upset, realizes follow-up motion's requirement, has solved clearance problem and flap 4 and the interference problem of interior wing 1 between outer wing 6 and interior wing 1 simultaneously, adopts the mode of linkage, avoids using unnecessary actuator, has characteristics such as simple structure, reliability height, light in weight.
In the preferred embodiment of the invention, the revolute pair comprises a connecting rod 3 hinged with one end of an extending end 9 of the folding actuator 5, and the other end of the connecting rod 3 is hinged with an ear-shaped rocker arm 2; the ear-shaped rocker arm 2 is fixedly connected with the opening cover 4.
In the preferred embodiment of the present invention, the surface of the flap 4 is flush with the upper wing surfaces of the inner wing 1 and the outer wing 6; the flap 4 will not have a height difference with the airfoil, reducing aerodynamic drag during flight.
When the folding actuator 5 is folded at the first stage, the first-stage driving rod 11 of the folding actuator 5 rotates around the rotation center of the folding actuator 5, the folding actuator 5 rotates around the upper edge of the inner wing 1 along the fixed hinge end, at the moment, the rotation between the outer wing 6 and the folding actuator 5 is locked, the folding actuator 5 rotates and simultaneously drives the opening cover 4 to turn around the fixed hinge end, and the effect that the opening cover 4 finishes linkage turning at the first stage of wing folding is realized; and then, the second-stage folding is started, the rotation between the inner wing 1 and the folding actuator 5 is kept locked, and the second-stage driving rod 8 of the folding actuator 5 rotates around the actuator rotation center to drive the outer wing 6 to rotate around the upper edge of the outer wing 6 along the fixed hinge end, so that the second-stage folding is completed, and the increase of the folding angle is realized.
The principle of the invention is as follows:
when the folding actuator 5 rotates clockwise at the first-stage driving rod 11, the second-stage driving rod 8 does not rotate, the relative position of the second-stage driving rod 8 and the second rocker arm 7 is kept unchanged, the first-stage driving rod 11 drives the first rocker arm 10 to rotate anticlockwise around the lower edge of the inner wing 1 along the hinge end, the folding actuator 5 rotates anticlockwise around the upper edge of the inner wing 1 along the hinge end, the rotation between the outer wing 6 and the folding actuator 5 is locked, and at the moment, the outer wing 6 and the folding actuator 5 synchronously rotate anticlockwise around the upper edge of the inner wing 1 along the hinge end; because folding actuator 5's anticlockwise rotation, folding actuator 5 stretches out end 9 and drives ear type rocking arm 2 and flap 4 through connecting rod 3, carries out anticlockwise rotation around fixed hinge end to realize flap 4's follow-up. When the first-stage driving rod 11 and the first rocker arm 10 move to the same straight line, the anticlockwise rotation angle of the first-stage driving rod 11 reaches the maximum, the first-stage folding is completed, and meanwhile, the follow-up opening cover 4 reaches the maximum turnover angle;
and starting the second-stage folding, wherein the first-stage driving rod 11 does not rotate, the relative position between the first-stage driving rod 11 and the first rocker arm 10 is kept unchanged, the rotation between the inner wing 1 and the folding actuator 5 is locked, and when the second-stage driving rod 8 of the folding actuator 5 rotates anticlockwise, the second-stage driving rod 8 drives the second rocker arm 7 to rotate around the lower edge of the outer wing 6 along the hinge end, and at the moment, the outer wing 6 rotates anticlockwise around the upper edge of the outer wing 6 along the hinge end. When the second-stage driving rod 8 and the second rocker arm 7 move to the same straight line, the wing is folded to reach the maximum turnover angle.
The invention uses the double-rotation hinge to replace the single-rotation hinge and two groups of four-bar mechanisms to realize the folding of the double-rotation hinge of the wing in two stages, and uses the dead point position of the mechanisms to realize the good holding of the wing at the folding position; a group of four-bar mechanisms are used for realizing the linkage effect of the opening cover 4, and the reliability is guaranteed to be higher.
The invention is well implemented in accordance with the above-described embodiments. It should be noted that, based on the above structural design, in order to solve the same technical problems, even if some insubstantial modifications or colorings are made on the present invention, the adopted technical solution is still the same as the present invention, and therefore, the technical solution should be within the protection scope of the present invention.
Claims (2)
1. The utility model provides an aircraft wing folding mechanism, includes interior wing (1), outer wing (6) and folding actuator (5), its characterized in that: the folding actuator (5) is positioned between the inner wing (1) and the outer wing (6) and is respectively hinged with the upper parts of the end surfaces of the inner wing (1) and the outer wing (6); the folding actuator (5) is provided with two output ends, a first-stage rotating pair and a second-stage rotating pair are respectively hinged between the two output ends and the lower parts of the end surfaces of the inner wing (1) and the outer wing (6), the first rotating pair comprises a first-stage driving rod (11) connected with the output ends of the folding actuator (5), and the free end of the first-stage driving rod (11) is hinged with a first rocker arm (10); the first rocker arm (10) is hinged with the lower part of the end face of the inner wing (1), a cover opening mechanism (4) is arranged on the outer side of the aircraft wing folding mechanism, and the cover opening mechanism comprises a cover opening (4) arranged above the folding actuator (5); an extending end (9) is arranged in the middle of the folding actuator (5), a rotating pair for pushing the opening cover (4) to open and close is hinged between the extending end (9) and the opening cover (4), the rotating pair comprises a connecting rod (3) hinged with one end of the extending end (9) of the folding actuator (5), and the other end of the connecting rod (3) is hinged with an ear-shaped rocker arm (2); the ear-shaped rocker arm (2) is fixedly connected with the opening cover (4), and the surface of the opening cover (4) is flush with the upper wing surfaces of the inner wing (1) and the outer wing (6).
2. An aircraft wing folding mechanism according to claim 1, characterised in that: the second revolute pair comprises a second-stage driving rod (8) connected with the output end of the folding actuator (5), and the free end of the second-stage driving rod (8) is hinged with a second rocker arm (7); the second rocker arm (7) is hinged with the lower part of the end surface of the outer wing (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711056080.2A CN107972847B (en) | 2017-11-01 | 2017-11-01 | Aircraft wing folding mechanism and flap mechanism based on same |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711056080.2A CN107972847B (en) | 2017-11-01 | 2017-11-01 | Aircraft wing folding mechanism and flap mechanism based on same |
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| Publication Number | Publication Date |
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| CN107972847A CN107972847A (en) | 2018-05-01 |
| CN107972847B true CN107972847B (en) | 2021-08-31 |
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| CN201711056080.2A Active CN107972847B (en) | 2017-11-01 | 2017-11-01 | Aircraft wing folding mechanism and flap mechanism based on same |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109204775A (en) * | 2018-08-06 | 2019-01-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of three axis two-stages overturning fold mechanism |
| CN109606633B (en) * | 2018-11-22 | 2022-04-08 | 成都飞机工业（集团）有限责任公司 | Single-shaft wing folding mechanism |
| CN109606632B (en) * | 2018-11-22 | 2022-04-08 | 成都飞机工业（集团）有限责任公司 | Follow-up mechanism of folding flap of carrier-based aircraft wing |
| GB2584409A (en) * | 2019-05-16 | 2020-12-09 | Airbus Operations Ltd | A moveable panel arrangement for a folding wing tip |
| GB2583959A (en) * | 2019-05-16 | 2020-11-18 | Airbus Operations Ltd | An arrangement for avoiding clashing on a folding wing tip |
| CN112478133B (en) * | 2020-12-02 | 2023-07-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Coupling connecting rod driving mechanism and wing folding rectifying cover plate opening and closing structure thereof |
| CN114379767B (en) * | 2022-01-14 | 2023-11-10 | 成都飞机工业（集团）有限责任公司 | Double-hinge mechanism based on middle-large unmanned aerial vehicle wing and angle indication method |
| GB2615748A (en) * | 2022-02-11 | 2023-08-23 | Airbus Operations Ltd | Aircraft Wing |
| CN115367098B (en) * | 2022-07-29 | 2024-10-18 | 成都飞机工业（集团）有限责任公司 | Double-connecting-rod flip type folding wing movable flap mechanism and folding movable flap |
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| US4039162A (en) * | 1976-02-05 | 1977-08-02 | Calhoun John T | Spoiler control system |
| US7243881B2 (en) * | 2003-06-03 | 2007-07-17 | The Boeing Company | Multi-function trailing edge devices and associated methods |
| DE102009039967A1 (en) * | 2009-09-03 | 2011-03-10 | Airbus Operations Gmbh | Adjustment mechanism for the kinematic guidance of an adjusting body when it is adjusted to a supporting structural part, adjusting mechanism for kinematic adjustment of a high-lift body and high-lift system with such adjustment mechanism |
| US9061753B2 (en) * | 2012-11-29 | 2015-06-23 | The Boeing Company | Hinged panel operation systems and methods |
| CN103963958B (en) * | 2014-04-21 | 2015-12-09 | 西工大常熟研究院有限公司 | Unmanned plane wingfold mechanism |
| CN104260876B (en) * | 2014-09-30 | 2016-07-06 | 浙江水利水电学院 | The outer wing folding and unfolding mechanism of a kind of morphing aircraft |
| CN106184711B (en) * | 2016-09-28 | 2018-04-03 | 西北工业大学 | The wingfold mechanism of variant aircraft |
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Effective date of registration: 20211111 Address after: 100089 building 4, zone 4, Xishan Creative Park, Haidian District, Beijing Patentee after: Beijing Xinxing Oriental aviation equipment Co., Ltd Address before: No. 480, north section of Jinxiu Avenue, Chengdu cross strait science and Technology Industrial Development Park, Wenjiang District, Chengdu, Sichuan 610000 Patentee before: Chengdu Feiya Aviation Equipment Application Research Institute Co., Ltd |
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