CN107972847A - A kind of aircraft wing fold mechanism and the lid mechanism based on it - Google Patents
A kind of aircraft wing fold mechanism and the lid mechanism based on it Download PDFInfo
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- CN107972847A CN107972847A CN201711056080.2A CN201711056080A CN107972847A CN 107972847 A CN107972847 A CN 107972847A CN 201711056080 A CN201711056080 A CN 201711056080A CN 107972847 A CN107972847 A CN 107972847A
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- wing
- lid
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- folding
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- 230000007246 mechanism Effects 0.000 title claims abstract description 34
- 230000001737 promoting effect Effects 0.000 claims abstract description 4
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- FGRBYDKOBBBPOI-UHFFFAOYSA-N 10,10-dioxo-2-[4-(N-phenylanilino)phenyl]thioxanthen-9-one Chemical compound O=C1c2ccccc2S(=O)(=O)c2ccc(cc12)-c1ccc(cc1)N(c1ccccc1)c1ccccc1 FGRBYDKOBBBPOI-UHFFFAOYSA-N 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
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
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses a kind of aircraft wing fold mechanism and the lid mechanism based on it, the problem of mainly solving existing wing-folding existing in the prior art causes wing faying face out-of-flatness, no lid or complicated port cover structure.A kind of aircraft wing fold mechanism includes inner wing, outer wing and folds actuator；Actuator is folded between inner wing and outer wing, it is respectively articulated between the top of inner wing and outer wing end face；Folding actuator has two output terminals, and two output terminals are hinged with first stage revolute pair and second stage revolute pair between inner wing and the end face lower part of outer wing respectively.Through the above scheme, invention achieves the smooth purpose of wing faying face, there is very high practical value and promotional value.
Description
Technical field
The present invention relates to aviation airborne equipment technical field, specifically, be related to a kind of aircraft wing fold mechanism and
Based on its lid mechanism.
Background technology
Aircraft wing, which folds, to be folded by being overturn after a part for wing is rotated by a certain angle, and reduces the wing of aircraft
Exhibition, reduces aircraft and parks required space.Wing-folding technology can not only meet that ship-board aircraft saves the purpose of deck space,
Increase the demand of lift-launch amount.The space occupied when can also effectively reduce aircraft dispatch and hangar storage, to various middle-size and small-size aircrafts
Use have certain meaning.
The wingfold mechanism of the aircraft of the prior art all uses simple chain form, and the rotating shaft of outer section of wing is perpendicular to the wing
Direction is opened up, positioned at wing cover top, in order not to produce the movement interference of folded portion, the revolution of this simple chain folding mode
Axis would generally protrude aerofoil surface, cause wing faying face out-of-flatness；On the other hand, since wingfold mechanism is easy to cause production
Movement interference between raw part, folding position, which has, after wing expansion stays larger gap, these are all to the wing knot of aircraft
Structure and aerodynamic characteristic have undesirable influence.
The prior art can also design lid to fill up the aerofoil surface gap of fold mechanism generation, but lid can increase
The protrusion of folded portion, while the folding and unfolding campaign of lid component needs special actuator and linkage driving, not only structure
Complexity, and the movement of lid must cooperate with fold mechanism, therefore the movement of associated mechanisms is difficult to control.
The content of the invention
It is existing to solve it is an object of the invention to provide a kind of aircraft wing fold mechanism and the lid mechanism based on it
Wing-folding technology causes wing-folding position to tie surface bulge, and interstitial site is complicated without lid or lid driving structure, movement
The problem of controlling difficulty big.
To solve the above-mentioned problems, the present invention provides following technical solution：
A kind of aircraft wing fold mechanism includes inner wing, outer wing and folds actuator；Fold actuator be located at inner wing and outside
Between the wing, it is respectively articulated between the top of inner wing and outer wing end face；Folding actuator has two output terminals, two outputs
End is hinged with first stage revolute pair and second stage revolute pair between inner wing and the end face lower part of outer wing respectively.
Specifically, the first revolute pair includes the first stage driving lever being connected with folding actuator output terminal, first stage
The free end of driving lever is hinged with the first rocking arm；First rocking arm and inner wing end face lower hinge.
Specifically, the second revolute pair includes the second stage driving lever being connected with folding actuator output terminal, second stage
The free end of driving lever is hinged with the second rocking arm；Second rocking arm and outer wing end face lower hinge.
A kind of lid mechanism based on aircraft wing fold mechanism includes being arranged at the lid folded above actuator；Fold
There is external part in the middle part of actuator, the revolute pair for promoting lid to be opened and closed is hinged between external part and lid.
Specifically, revolute pair includes the connecting rod hinged with folding actuator external part one end, and the other end of connecting rod is hinged with
Ear type rocking arm；Ear type rocking arm is fixedly connected with lid.
Specifically, lid surface is flushed with the top airfoil of inner wing and outer wing.
Compared with prior art, the invention has the advantages that：, can after structure of the present invention using double-strand chain folding
To avoid being folded using simple chain rotating shaft can be made to protrude aerofoil surface, raised situation is formed in folding position, reduces flight
During aerodynamic drag, and while actuator completes first stage wing-folding, drive lid upset, realize servo-actuated
The requirement of movement, while solve outer wing and interior interplane clearance issues and the interference problem of lid and inner wing, using linkage
Mode, avoids using unnecessary actuator, has the characteristics that simple in structure, motion control is reliable, light-weight.
Brief description of the drawings
Fig. 1 is the structure diagram of the present invention.
Fig. 2 is the structure diagram that the present invention realizes first stage folding.
In above-mentioned attached drawing, the corresponding component names of reference numeral are as follows：
1- inner wings, 2- ear type rocking arms, 3- connecting rods, 4- lids, 5- fold actuator, 6- outer wings, the second rocking arms of 7-, 8- second
Stage driving lever, 9- external parts, the first rocking arms of 10-, 11- first stage driving levers.
Embodiment
The invention will be further described with reference to the accompanying drawings and examples, and embodiments of the present invention include but not limited to
The following example.
As depicted in figs. 1 and 2, a kind of aircraft wing fold mechanism includes inner wing 1, outer wing 6 and folds actuator 5；Fold
Between inner wing 1 and outer wing 6, it is respectively articulated with actuator 5 between the top of 6 end face of inner wing 1 and outer wing；Fold actuator
5 have two output terminals, and two output terminals are hinged with first stage rotation between inner wing 1 and the end face lower part of outer wing 6 respectively
Secondary and second stage revolute pair；Said structure forms double-strand chain revolving structure, can effectively avoid folding rotating shaft protrusion machine
The situation of wing surface, ensures that the wing faying face after expansion is smooth, reduces aerodynamic drag in flight course.
As in preferred embodiments of the present invention, the first revolute pair includes first be connected with folding 5 output terminal of actuator
Stage driving lever 11, the free end of first stage driving lever 11 are hinged with the first rocking arm 10；Under first rocking arm 10 and 1 end face of inner wing
Portion is hinged.
As in preferred embodiments of the present invention, the second revolute pair includes second be connected with folding 5 output terminal of actuator
Stage driving lever 8, the free end of second stage driving lever 8 are hinged with the second rocking arm 7；Second rocking arm 7 is cut with scissors with 6 end face lower part of outer wing
Connect.
A kind of 4 mechanism of lid based on aircraft wing fold mechanism includes being arranged at the lid 4 for folding the top of actuator 5；
Folding the middle part of actuator 5 has external part 9, and the revolute pair for promoting lid 4 to be opened and closed is hinged between external part 9 and lid 4；
The driving of lid 4 is by the way of linkage, it is not necessary to uses special actuator, functional reliability is high, while reduces folding
The overall weight of system；While folding the completion first stage wing-folding of actuator 5, drive lid 4 to overturn, realize servo-actuated fortune
Dynamic requirement, while solve clearance issues and lid 4 and the interference problem of inner wing 1 between outer wing 6 and inner wing 1, using linkage
Mode, avoid using unnecessary actuator, have the characteristics that simple in structure, reliability is high, light-weight.
As in preferred embodiments of the present invention, revolute pair includes the connecting rod hinged with folding 5 external part of actuator, 9 one end
3, the other end of connecting rod 3 is hinged with ear type rocking arm 2；Ear type rocking arm 2 is fixedly connected with lid 4.
As in preferred embodiments of the present invention, 4 surface of lid is flushed with the top airfoil of inner wing 1 and outer wing 6；Lid 4
Aerodynamic drag in flight course can be reduced with situation of the aerofoil without difference in height.
When the present invention folds in the first stage, turned round by 5 first stage of folding actuator driving lever 11 around actuator 5 is folded
Central rotation drive, fold actuator 5 can on inner wing 1 along fixed hinge end rotate, at this time outer wing 6 with fold actuator 5 it
Between rotation be lockable, fold actuator 5 rotate while drive lid 4 overturn around its fixed hinge end, realize lid 4
It is the effect for completing linkage upset in the wing-folding first stage；Start second stage folding afterwards, keep inner wing 1 to make with folding
Rotation between dynamic device 5 is pinned, and by 5 second stage driving lever 8 of folding actuator around actuator centre of gyration rotation driving, is made outer
The wing 6 rotates on outer wing 6 along fixed hinge end, completes second stage and folds, realizes the increase of folding angles.
The principle of the present invention is as follows：
Actuator 5 is folded when driving lever 11 rotates clockwise in the first stage, second stage driving lever 8 does not rotate, and keeps
Second stage driving lever 8 and the relative position of the second rocking arm 7 are constant, and first stage driving lever 11 drives the first rocking arm 10, around interior
Rotated counterclockwise along hinged end under the wing 1, realize that fold actuator 5 rotates counterclockwise on inner wing 1 along hinged end, outer wing 6 and folding
Rotation between folded actuator 5 is lockable, and at this time, outer wing 6 is synchronous with folding actuator 5 counterclockwise along hinged end on inner wing 1
Rotate；Due to folding the rotation counterclockwise of actuator 5, fold 5 external part 9 of actuator by connecting rod 3 drive ear type rocking arm 2 and
Lid 4, is rotated counterclockwise around fixed hinge end, so as to fulfill the servo-actuated of lid 4.When first stage driving lever 11 and first
When rocking arm 10 moves to same straight line, the rotated counterclockwise by angle of first stage driving lever 11 reaches maximum, and the first stage folds
Complete, while servo-actuated lid 4 reaches maximum flip angle；
Start second stage to fold, first stage driving lever 11 does not rotate, and keeps first stage driving lever 11 to shake with first
The relative position of arm 10 is constant, and inner wing 1 and the rotation folded between actuator 5 are lockable, and folds 5 second stage of actuator actively
When bar 8 rotates counterclockwise, second stage driving lever 8 drives the second rocking arm 7 to be rotated under outer wing 6 along hinged end, at this time, outer wing 6
Rotated counterclockwise on outer wing 6 along hinged end.When 8 and second rocking arm 7 of second stage driving lever moves to same straight line, wing
Folding reaches maximum flip angle.
The present invention replaces single swing hinge and two groups of four-bar mechanisms to realize wing double-strand chain with dual AC power hinge
The folding in two stages, using the dead-centre position of mechanism, realizes that wing is held in the good of folding position；With one group of four-bar mechanism
Realize the linkage effect of lid 4, reliability has higher guarantee.
According to above-described embodiment, the present invention can be realized well.What deserves to be explained is before based on said structure design
Put, to solve same technical problem, some made in the present invention are used without substantive change or polishing
Technical solution essence still as the present invention, therefore it should also be as within the scope of the present invention.
Claims (6)
1. a kind of aircraft wing fold mechanism, including inner wing (1), outer wing (6) and folding actuator (5), it is characterised in that：Fold
Actuator (5) is located between inner wing (1) and outer wing (6), it is respectively articulated between the top of inner wing (1) and outer wing (6) end face；
Folding actuator (5) has two output terminals, and two output terminals between the end face lower part of inner wing (1) and outer wing (6) respectively with cutting with scissors
It is connected to first stage revolute pair and second stage revolute pair.
A kind of 2. aircraft wing fold mechanism according to claim 1, it is characterised in that：First revolute pair includes and folding
The first stage driving lever (11) of actuator (5) output terminal connection, the free end of first stage driving lever (11) is hinged with first
Rocking arm (10)；First rocking arm (10) and inner wing (1) end face lower hinge.
A kind of 3. aircraft wing fold mechanism according to claim 1 or 2, it is characterised in that：Second revolute pair include with
Fold the second stage driving lever (8) of actuator (5) output terminal connection, the free end of second stage driving lever (8) is hinged with the
Two rocking arms (7)；Second rocking arm (7) and outer wing (6) end face lower hinge.
A kind of 4. lid (4) mechanism based on aircraft wing fold mechanism, it is characterised in that：Including being arranged at folding actuator
(5) lid (4) above；Folding in the middle part of actuator (5) has external part (9), is hinged between external part (9) and lid (4)
For the revolute pair for promoting lid (4) to be opened and closed.
5. lid (4) mechanism according to claim 4 based on aircraft wing fold mechanism, it is characterised in that：Revolute pair
Including the connecting rod (3) hinged with folding actuator (5) external part (9) one end, the other end of connecting rod (3) is hinged with ear type rocking arm
(2)；Ear type rocking arm (2) is fixedly connected with lid (4).
6. lid (4) mechanism based on aircraft wing fold mechanism according to right wants 4 or 5, it is characterised in that：Lid
(4) surface is flushed with the top airfoil of inner wing (1) and 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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107972847A true CN107972847A (en) | 2018-05-01 |
| CN107972847B CN107972847B (en) | 2021-08-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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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Cited By (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 |
| CN109606632A (en) * | 2018-11-22 | 2019-04-12 | 成都飞机工业（集团）有限责任公司 | A kind of follower of carrier-borne aircraft wing-folding lid |
| CN109606633A (en) * | 2018-11-22 | 2019-04-12 | 成都飞机工业（集团）有限责任公司 | A kind of single axle wingfold mechanism |
| GB2583959A (en) * | 2019-05-16 | 2020-11-18 | Airbus Operations Ltd | An arrangement for avoiding clashing on a folding wing tip |
| GB2584409A (en) * | 2019-05-16 | 2020-12-09 | Airbus Operations Ltd | A moveable panel arrangement for a folding wing tip |
| CN112478133A (en) * | 2020-12-02 | 2021-03-12 | 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 |
| CN114379767A (en) * | 2022-01-14 | 2022-04-22 | 成都飞机工业（集团）有限责任公司 | Double-hinge mechanism based on wings of medium-large unmanned aerial vehicle and angle indication method |
| CN115367098A (en) * | 2022-07-29 | 2022-11-22 | 成都飞机工业（集团）有限责任公司 | Double-connecting-rod flip type folding wing movable opening cover mechanism and folding movable opening cover |
| EP4227212A1 (en) * | 2022-02-11 | 2023-08-16 | Airbus Operations Limited | Aircraft wing |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4039162A (en) * | 1976-02-05 | 1977-08-02 | Calhoun John T | Spoiler control system |
| US20050011994A1 (en) * | 2003-06-03 | 2005-01-20 | Seiya Sakurai | Multi-function trailing edge devices and associated methods |
| CN102574574A (en) * | 2009-09-03 | 2012-07-11 | 空中客车运营有限公司 | Adjusting mechanism for kinematically guiding an adjusting body during displacement on a supporting structural part, adjusting mechanism for kinematically adjusting a vertically lifting body and vertical lift system comprising said type of adjusting |
| CN103847956A (en) * | 2012-11-29 | 2014-06-11 | 波音公司 | Hinged Panel Operation Systems and Methods |
| CN103963958A (en) * | 2014-04-21 | 2014-08-06 | 西工大常熟研究院有限公司 | Wing folding mechanism for unmanned plane |
| CN104260876A (en) * | 2014-09-30 | 2015-01-07 | 浙江水利水电学院 | Outer wing folding and unfolding mechanism for morphing aircraft |
| CN106184711A (en) * | 2016-09-28 | 2016-12-07 | 西北工业大学 | The wingfold mechanism of variant aircraft |
-
2017
- 2017-11-01 CN CN201711056080.2A patent/CN107972847B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4039162A (en) * | 1976-02-05 | 1977-08-02 | Calhoun John T | Spoiler control system |
| US20050011994A1 (en) * | 2003-06-03 | 2005-01-20 | Seiya Sakurai | Multi-function trailing edge devices and associated methods |
| CN102574574A (en) * | 2009-09-03 | 2012-07-11 | 空中客车运营有限公司 | Adjusting mechanism for kinematically guiding an adjusting body during displacement on a supporting structural part, adjusting mechanism for kinematically adjusting a vertically lifting body and vertical lift system comprising said type of adjusting |
| CN103847956A (en) * | 2012-11-29 | 2014-06-11 | 波音公司 | Hinged Panel Operation Systems and Methods |
| CN103963958A (en) * | 2014-04-21 | 2014-08-06 | 西工大常熟研究院有限公司 | Wing folding mechanism for unmanned plane |
| CN104260876A (en) * | 2014-09-30 | 2015-01-07 | 浙江水利水电学院 | Outer wing folding and unfolding mechanism for morphing aircraft |
| CN106184711A (en) * | 2016-09-28 | 2016-12-07 | 西北工业大学 | The wingfold mechanism of variant aircraft |
Cited By (17)
| 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 |
| CN109606632A (en) * | 2018-11-22 | 2019-04-12 | 成都飞机工业（集团）有限责任公司 | A kind of follower of carrier-borne aircraft wing-folding lid |
| CN109606633A (en) * | 2018-11-22 | 2019-04-12 | 成都飞机工业（集团）有限责任公司 | A kind of single axle wingfold mechanism |
| US11772776B2 (en) | 2019-05-16 | 2023-10-03 | Airbus Operations Limited | Arrangement for avoiding clashing on 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 |
| GB2584409A (en) * | 2019-05-16 | 2020-12-09 | Airbus Operations Ltd | A moveable panel arrangement for a folding wing tip |
| CN113226922A (en) * | 2019-05-16 | 2021-08-06 | 空中客车营运有限公司 | Device for avoiding collision on folding wing tips |
| CN113226922B (en) * | 2019-05-16 | 2024-10-18 | 空中客车营运有限公司 | Device for avoiding collisions on a folding wing tip |
| WO2020229630A1 (en) * | 2019-05-16 | 2020-11-19 | Airbus Operations Limited | An arrangement for avoiding clashing on a folding wing tip |
| CN112478133A (en) * | 2020-12-02 | 2021-03-12 | 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 |
| CN114379767A (en) * | 2022-01-14 | 2022-04-22 | 成都飞机工业（集团）有限责任公司 | Double-hinge mechanism based on wings of medium-large unmanned aerial vehicle and angle indication method |
| GB2615748A (en) * | 2022-02-11 | 2023-08-23 | Airbus Operations Ltd | Aircraft Wing |
| EP4227212A1 (en) * | 2022-02-11 | 2023-08-16 | Airbus Operations Limited | Aircraft wing |
| US12179915B2 (en) | 2022-02-11 | 2024-12-31 | Airbus Operations Limited | Aircraft wing with wing tip seal panel assembly |
| CN115367098A (en) * | 2022-07-29 | 2022-11-22 | 成都飞机工业（集团）有限责任公司 | Double-connecting-rod flip type folding wing movable opening cover mechanism and folding movable opening cover |
| 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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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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