CN109606634A - A kind of twin axle wingfold mechanism - Google Patents
A kind of twin axle wingfold mechanism Download PDFInfo
- Publication number
- CN109606634A CN109606634A CN201811399745.4A CN201811399745A CN109606634A CN 109606634 A CN109606634 A CN 109606634A CN 201811399745 A CN201811399745 A CN 201811399745A CN 109606634 A CN109606634 A CN 109606634A
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- Prior art keywords
- wing
- crank
- wingfold
- outer wing
- connecting rod
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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)
- Toys (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses a kind of twin axle wingfold mechanisms, including inner wing crank, outer wing crank, be arranged between inner wing crank and outer wing crank and simultaneously bi-directionally the rotary actuator, the inner wing fold mechanism for being mounted on inner wing crank and connecting with inner wing, the outer wing fold mechanism, the multiple inside and outside wingfold connectors being mounted on inner wing crank and outer wing crank that are mounted on outer wing crank and connect with outer wing that rotate, each inside and outside wingfold connector are hinged respectively at inner wing, outer wing.Invention uses two-way reverse rotation actuator, is folded and unfolded, is occupied little space using rotation drive form realization；The present invention can effectively realize that wing outer wing carries out wide-angle folding under limited folding space, and folding angles are up to 130 ° or more；This invention ensures that the substantivity of inside and outside wing load transmitting, reduces the intensity limitation to fold mechanism；The present invention can be entirely disposed in wing aerodynamic external surface, without arranging pneumatic bulge, not influence wing aerodynamic shape.
Description
Technical field
The present invention relates to aircraft wing folding fields, are a kind of twin axle wingfold mechanisms specifically.
Background technique
Chinese first aircraft carrier has equipped naval, and the aircraft carrier of the entirely autonomous design production of China is moving forward steadily, compeling
The carrier-borne aircraft for equipping respective model will be researched and developed by, which being essential, forms complete aircraft carrier fleet.In order to empty in limited type aircraft carrier deck and hangar
Between under the conditions of carry more carrier-borne aircrafts, carrier-borne aircraft need to have wing-folding function, in execution task at wing expansion shape
State, and when being put in storage and being tethered at deck in folded state at wing.
Carrier-borne aircraft have exhibition to width limit, need to carry out wing-folding, simultaneously because aircraft carrier hangar height also have it is winged
Machine height limitation, it is desirable that machine height is no more than hangar height limitation under wing-folding state.The outer span of carrier-borne aircraft wing is to accounting
About big, carrier-borne aircraft is opened up about small to width after folding, to meet the limitation of machine height at this time, and the folding angles that bigger outer wing needs are also more
Greatly.Therefore, modern carrier-borne aircraft requires the wing-folding function of wide-angle, and folding angles often reach 130 ° or more.
Modern opportunity of combat requires to be continuously improved to Aerodynamic Configuration of Aireraft, and especially wing is the main next of aircraft aerodynamic lift
Source, to wing aerodynamic shape requirement highest.Therefore, structure, mechanism and the equipment on carrier-borne aircraft wing are arranged in without specifically limited
Under cannot influence wing aerodynamic shape, such as avoid the occurrence of as far as possible bulge influence wing aerodynamic shape the case where.Modern carrier-borne aircraft
It is required that wingfold mechanism cannot influence wing aerodynamic shape, fold mechanism will be arranged in wing aerodynamic shape.
Carrier-borne aircraft wingfold mechanism is mostly uniaxial hinge-type fold mechanism at present, and folding angles are small, and often to be dashed forward
Wing shape could increase folding angles out.External carrier-borne aircraft model is relatively more, and the country only destroys -15 carrier-borne aircrafts, and wing
Fold mechanism is uniaxial hinge-type fold mechanism, and the requirement of modern carrier-borne aircraft is met there is an urgent need to new wingfold mechanism.
Summary of the invention
It provides a kind of practical the purpose of the present invention is to provide a kind of, meets aircraft folding angles and do not influence wing
The twin axle wingfold mechanism that aerodynamic configuration requires.
The present invention is achieved through the following technical solutions: a kind of twin axle wingfold mechanism, including inner wing crank, outer wing are bent
Handle, be arranged between inner wing crank and outer wing crank and simultaneously bi-directionally rotate rotary actuator, be mounted on inner wing crank
And the inner wing fold mechanism being connect with inner wing, the outer wing fold mechanism, the Duo Gean that are mounted on outer wing crank and are connect with outer wing
Inside and outside wingfold connector on inner wing crank and outer wing crank, each inside and outside wingfold connector is respectively at inner wing, outer
The wing is hinged.
Further, in order to preferably realize the present invention, the outer wing fold mechanism includes being fixedly mounted on outer wing crank
On A connecting rod, with the hinged outer wing connecting rod of A connecting rod；One end and outer wing far from A connecting rod of the outer wing connecting rod are hinged.
Further, in order to preferably realize the present invention, the outer wing fold mechanism further includes setting in A connecting rod and outer
Outer wingfold auricle between the wing, the outer wingfold auricle and A connecting rod are hinged.
Further, in order to preferably realize the present invention, the inner wing fold mechanism includes being fixedly mounted on inner wing crank
On B connecting rod, with the hinged inner wing connecting rod of B connecting rod；One end and inner wing far from B connecting rod of the inner wing connecting rod are hinged.
Further, in order to preferably realize the present invention, the inner wing fold mechanism further include setting B connecting rod with it is interior
Interior wingfold auricle between the wing, the interior wingfold auricle and B connecting rod are hinged.
Further, in order to preferably realize the present invention, the inside and outside wingfold connector includes folding joint ontology, difference
It is hingedly mounted on inner wing connector auricle and outer wing connector auricle on folding joint ontology；The inner wing connector auricle setting is folding
Folding joint ontology is arranged in close to the side of outer wing close to the side of inner wing, the outer wing connector auricle in joint body.
Further, in order to preferably realize the present invention, the inside and outside wingfold connector is in triangular prism structure, one of them
End is mounted on inner wing crank or outer wing crank；Other two end and inner wing connector auricle/outer wing connector auricle are hinged.
Further, in order to preferably realize the present invention, the outer wing fold mechanism is identical as inner wing fold mechanism structure；
Outer wing crank is arranged in close to the side of rotary actuator in the outer wing fold mechanism, and inner wing fold mechanism is arranged in inner wing crank
Close to the side of rotary actuator.
Further, in order to preferably realize the present invention, the quantity of the inside and outside wingfold connector is three, one of them
The one end of outer wing crank far from rotary actuator is set, and other two is arranged on inner wing crank；It is adjacent and be mounted on outer wing
The inside and outside wingfold connector of crank is connect with the inside and outside wingfold connector for being mounted on inner wing crank by shaft.
It further, further include that the inside and outside wingfold of adjacent outer wing crank is arranged in connect in order to preferably realize the present invention
Shaft between head and the inside and outside wingfold connector of outer wing crank；Interconnecting piece, the interconnecting piece and rotation are installed in the shaft
Turn actuator connection.
Compared with prior art, the present invention have the following advantages that and the utility model has the advantages that
(1) present invention uses two-way reverse rotation actuator, is folded and unfolded using rotation drive form realization, occupied space
It is small；
(2) present invention can effectively realize that wing outer wing carries out wide-angle folding under limited folding space, and folding angles can
Up to 130 ° or more；
(3) this invention ensures that the substantivity of inside and outside wing load transmitting, reduces the intensity limitation to fold mechanism；
(4) present invention can be entirely disposed in wing aerodynamic external surface, without arranging pneumatic bulge, not influenced outside wing aerodynamic
Shape.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention；
Structural schematic diagram when Fig. 2 is present invention expansion；
Fig. 3 is the structural schematic diagram when present invention folds；
Fig. 4 is fold mechanism arrangement schematic diagram in the present invention；
Wherein 1- inner wing connector auricle, 2- outer wing connector auricle, wingfold auricle in 3-, wingfold auricle in 4-, outer wing in 5-
Folding joint, 8- outer wing connecting rod, 9- inner wing connecting rod, 10- rotary actuator, 11- outer wing crank, 12- inner wing crank, 13- outer wing
Rotary shaft, 14- inner wing rotary shaft.
Specific embodiment
The present invention is described in further detail below with reference to embodiment, embodiments of the present invention are not limited thereto.
Embodiment 1:
The present invention is achieved through the following technical solutions, as shown in Figure 1, a kind of twin axle wingfold mechanism, including inner wing crank
12, outer wing crank 11, be arranged between inner wing crank 12 and outer wing crank 11 and simultaneously bi-directionally rotate rotary actuator 10,
Be mounted on inner wing crank 12 and connect with inner wing inner wing fold mechanism, be mounted on outer wing crank 11 and connect with outer wing
Outer wing fold mechanism, multiple inside and outside wingfold connectors 5 being mounted on inner wing crank 12 and outer wing crank 11, it is each described inside and outside
Wingfold connector 5 is hinged respectively at inner wing, outer wing.
It should be noted that by above-mentioned improvement, by the present invention be mounted on inner wing separation end face and outer wing separation end face it
Between folding opening space in.
The inner wing crank 12 and the one end close to each other of outer wing crank 11 shaft with 10 both ends of rotary actuator respectively
Connection.
Expansion is in use, control rotary actuator 10 works, so that the reversed rotation simultaneously of the shaft at 10 both ends of rotary actuator
Turn, what is connect with outer wing crank 11 turn rotates axially away from the direction of outer wing so that with outer wing fold mechanism with outer wing
Under the drive for the shaft that crank 11 connects, so that outer flapwise is moved far from the side of outer wing crank 11, to realize that outer wing is opposite
It is unfolded in inner wing.Otherwise to realize folding.
The central axes of the shaft of the outer wing crank 11, inner wing crank 12, rotary actuator 10 are on the same line.
The other parts of the present embodiment are same as the previously described embodiments, and so it will not be repeated.
Embodiment 2:
The present embodiment advanced optimizes on the basis of the above embodiments, as shown in Figure 1, further, in order to preferably real
The existing present invention, the outer wing fold mechanism include that the A connecting rod being fixedly mounted on outer wing crank 11 and A connecting rod are hinged
Outer wing connecting rod 8；One end and outer wing far from A connecting rod of the outer wing connecting rod 8 are hinged.
Further, in order to preferably realize the present invention, the outer wing fold mechanism further includes setting in A connecting rod and outer
Outer wingfold auricle 3 between the wing, the outer wingfold auricle 3 and A connecting rod are hinged.Outer wingfold auricle 3 is fixed with outer wing
Connection.
Further, in order to preferably realize the present invention, the inner wing fold mechanism includes being fixedly mounted on inner wing crank
B connecting rod and the hinged inner wing connecting rod 9 of B connecting rod on 12；The one end of the inner wing connecting rod 9 far from B connecting rod and inner wing are cut with scissors
It connects.
Further, in order to preferably realize the present invention, the inner wing fold mechanism further include setting B connecting rod with it is interior
Interior wingfold auricle 4 between the wing, the interior wingfold auricle 4 and B connecting rod are hinged.Interior wingfold auricle 4 is fixed with inner wing
Connection.
It should be noted that the one end of A connecting rod far from outer wing crank 11 is close simultaneously to inner wing side by above-mentioned improvement
Hinged with outer wing connecting rod 8, one end outer wing pleated sheet of the outer wing connecting rod 8 far from A connecting rod is hinged；B connecting rod is far from inner wing crank
12 one end is close to the side of outer wing and hinged with inner wing connecting rod 9, wingfold in the one end of inner wing connecting rod 9 far from B connecting rod
Piece is hinged；In the case where rotary actuator 10 drives, outer wing crank 11 and inner wing crank 12 carry out rotation and direction of rotation phase
Instead, fold when, outer wing crank 11 rotate so that be mounted on outer wing crank 11 A connecting rod, outer wing connecting rod 8, outer wingfold
Piece is rotated around the axis of 10 shaft of rotary actuator and makes outer wing pleated sheet close to 11 side of outer wing crank, thus real
The folding of existing outer wing；Due to outer wing crank 11, inner wing crank 12, rotary actuator 10 shaft central axes on the same line
So that central axes of the outer wing with inner wing to the shaft of rotary actuator 10 are close, to realize the folding of outer wing and inner wing.
The other parts of the present embodiment are same as the previously described embodiments, and so it will not be repeated.
Embodiment 3:
The present embodiment advanced optimizes on the basis of the above embodiments, as shown in Figure 1,
Further, in order to preferably realize the present invention, the inside and outside wingfold connector 5 includes folding joint ontology, cuts with scissors respectively
Connect the inner wing connector auricle 1 and outer wing connector auricle 2 being mounted on folding joint ontology；The setting of inner wing connector auricle 1 exists
Folding joint ontology is arranged in close to the side of outer wing close to the side of inner wing, the outer wing connector auricle 2 in folding joint ontology.
It should be noted that inside and outside wingfold connector 5 connects with inner wing connector auricle 1 and outer wing respectively by above-mentioned improvement
Head auricle 2 is hinged, is primarily involved in the load transmission of inner wing, outer interplane, when realizing that carrier-borne aircraft is folded or actuation is unfolded, outside
The wing and inner wing carry out dual-axis rotation movement around outer wing crank 11, inner wing crank 12.
The other parts of the present embodiment are same as the previously described embodiments, and so it will not be repeated.
Embodiment 4:
The present embodiment advanced optimizes on the basis of the above embodiments, as shown in Figure 1, further, in order to preferably real
The existing present invention, the inside and outside wingfold connector 5 is in triangular prism structure, and one of end is mounted on inner wing crank 12 or outer wing is bent
On handle 11；Other two end and 1/ outer wing connector auricle 2 of inner wing connector auricle are hinged.
It should be noted that triangular prism structure reduces occupied space, so that the folding in folding process by above-mentioned improvement
Folded angle is bigger.
The other parts of the present embodiment are same as the previously described embodiments, and so it will not be repeated.
Embodiment 5:
The present embodiment advanced optimizes on the basis of the above embodiments, as shown in Figure 1, further, in order to preferably real
The existing present invention, the outer wing fold mechanism are identical as inner wing fold mechanism structure；The outer wing fold mechanism setting is in outer wing song
For handle 11 close to the side of rotary actuator 10, inner wing crank 12 is arranged in close to the one of rotary actuator 10 in inner wing fold mechanism
Side.
The other parts of the present embodiment are same as the previously described embodiments, and so it will not be repeated.
Embodiment 6:
The present embodiment advanced optimizes on the basis of the above embodiments, as shown in Figure 1, further, in order to preferably real
The quantity of the existing present invention, the inside and outside wingfold connector 5 are three, and one of setting is in outer wing crank 11 far from rotation actuation
One end of device 10, other two are arranged on inner wing crank 12；Inside and outside wingfold connector 5 that is adjacent and being mounted on outer wing crank 11
It is connect with the inside and outside wingfold connector 5 for being mounted on inner wing crank 12 by shaft.
It further, further include the inside and outside wingfold that adjacent outer wing crank 11 is set in order to preferably realize the present invention
Shaft between connector 5 and the inside and outside wingfold connector 5 of outer wing crank 11；Interconnecting piece, the connection are installed in the shaft
Portion is connect with rotary actuator 10.
Outer wing rotary shaft 13, inside and outside wingfold connector 5 are provided between inside and outside wingfold connector 5 and outer wing connector auricle 1
Outer wing rotary shaft 14 is provided between inner wing connector auricle 2.
The inside and outside wingfold connector 5 is hinged by outer wing rotary shaft 13 and outer wing connector auricle 1, the inside and outside wingfold
Connector is hinged by inner wing rotary shaft 14 and inner wing connector auricle.Outer wing rotary shaft 13, the length direction of inner wing rotary shaft 14 and outer
The length direction of wing crank 11 is parallel.
It should be noted that the present invention is connected interior using the inside and outside wingfold connector 5 of triangular prism structure by above-mentioned improvement
The wing and outer wing, in wing-folding and expansion actuation, outer wing carries out bispin around inner wing rotary shaft 14 around outer wing rotary shaft 13, inner wing
Shaft foldable realizes that outer wing carries out wide-angle folding under limited folding space, and folding angles are up to 130 ° or more.
In the case where carrier-borne aircraft is in wing unfolded state, inside and outside wingfold connector 5 participates in the transmitting of inside and outside wing load, Qi Taling
Component is not involved in inside and outside wing load transmitting, ensure that the substantivity of inside and outside wing load transmitting, reduces the intensity to fold mechanism
Limitation.
Using rotation drive form, rotary actuator 10 reversely rotates driving using electric double-way, occupies little space, electronic
Drive form is easily controllable, is easy to carry out modularized design, is easy to carry out maintenance replacement.
Mechanism integrally uses the double double leval jib driving outer wings of concurrent to complete to fold, and the double double leval jibs of concurrent realize outer wing around two
The function that rotary shaft is folded, and occupy little space, the space outside inside and outside wingfold separation end face is not influenced.
A whole set of fold mechanism can be entirely disposed in wing aerodynamic external surface, without arranging pneumatic bulge, not influence wing
Aerodynamic configuration.
Rotary actuator 10 in the present invention uses the two-way rotary actuator 10 reversely exported, including electric motor and anti-
To retarder, two reversed rotary motions can be exported simultaneously, and outer wing crank 11 and inner wing crank 12 is driven to carry out opposite direction
Rotary motion.
Preferably, outer wing crank 11 and inner wing crank 12 there is mechanical external interface, it can be achieved that external hand-held driver into
The manual wing-folding of row or expansion actuation.
The other parts of the present embodiment are same as the previously described embodiments, and so it will not be repeated.
The above is only presently preferred embodiments of the present invention, not does limitation in any form to the present invention, it is all according to
According to technical spirit any simple modification to the above embodiments of the invention, equivalent variations, protection of the invention is each fallen within
Within the scope of.
Claims (10)
1. a kind of twin axle wingfold mechanism, it is characterised in that: exist including inner wing crank (12), outer wing crank (11), setting
Rotary actuator (10) that is between inner wing crank (12) and outer wing crank (11) and simultaneously bi-directionally rotating is mounted on inner wing crank
(12) the inner wing fold mechanism that connect on and with inner wing is mounted on the outer wing folding machine connecting on outer wing crank (11) and with outer wing
Structure, multiple inside and outside wingfold connectors (5) being mounted on inner wing crank (12) and outer wing crank (11), each interior outer wing folding
The head (5) that splices is hinged respectively at inner wing, outer wing.
2. a kind of twin axle wingfold mechanism according to claim 1, it is characterised in that: the outer wing fold mechanism packet
Include the A connecting rod being fixedly mounted on outer wing crank (11) and the hinged outer wing connecting rod (8) of A connecting rod；The outer wing connecting rod
(8) one end far from A connecting rod and outer wing are hinged.
3. a kind of twin axle wingfold mechanism according to claim 2, it is characterised in that: the outer wing fold mechanism is also
Including the outer wingfold auricle (3) being arranged between A connecting rod and outer wing, the outer wingfold auricle (3) and A connecting rod are cut with scissors
It connects.
4. a kind of twin axle wingfold mechanism according to claim 3, it is characterised in that: the inner wing fold mechanism packet
Include the B connecting rod being fixedly mounted on inner wing crank (12) and the hinged inner wing connecting rod (9) of B connecting rod；The inner wing connecting rod
(9) one end far from B connecting rod and inner wing are hinged.
5. a kind of twin axle wingfold mechanism according to claim 4, it is characterised in that: the inner wing fold mechanism is also
Including the interior wingfold auricle (4) being arranged between B connecting rod and inner wing, the interior wingfold auricle (4) and B connecting rod are cut with scissors
It connects.
6. a kind of twin axle wingfold mechanism according to claim 1-5, it is characterised in that: the interior outer wing
Folding joint (5) includes folding joint ontology, is respectively articulated with and is mounted on inner wing connector auricle (1) and outer wing on folding joint ontology
Connector auricle (2)；Folding joint ontology is arranged in close to the side of inner wing, the outer wing connector in the inner wing connector auricle (1)
Folding joint ontology is arranged in close to the side of outer wing in auricle (2).
7. a kind of twin axle wingfold mechanism according to claim 6, it is characterised in that: the inside and outside wingfold connector
It (5) is in triangular prism structure, one of end is mounted on inner wing crank (12) or outer wing crank (11)；Other two end with
Inner wing connector auricle (1)/outer wing connector auricle (2) is hinged.
8. a kind of twin axle wingfold mechanism according to claim 7, it is characterised in that: the outer wing fold mechanism with
Inner wing fold mechanism structure is identical；The outer wing fold mechanism setting is in outer wing crank (11) close to the one of rotary actuator (10)
Side, the setting of inner wing fold mechanism is in inner wing crank (12) close to the side of rotary actuator (10).
9. a kind of twin axle wingfold mechanism according to claim 8, it is characterised in that: the inside and outside wingfold connector
(5) quantity is three, and one of setting is set in the one end of outer wing crank (11) far from rotary actuator (10), other two
It sets on inner wing crank (12)；Inside and outside wingfold connector (5) that is adjacent and being mounted on outer wing crank (11) and be mounted on inner wing song
The inside and outside wingfold connector (5) of handle (12) is connected by shaft.
10. a kind of twin axle wingfold mechanism according to claim 9, it is characterised in that: further include being arranged adjacent
Shaft between the inside and outside wingfold connector (5) of outer wing crank (11) and the inside and outside wingfold connector (5) of outer wing crank (11)；Institute
It states and interconnecting piece is installed in shaft, the interconnecting piece is connect with rotary actuator (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811399745.4A CN109606634B (en) | 2018-11-22 | 2018-11-22 | Double-shaft wing folding mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811399745.4A CN109606634B (en) | 2018-11-22 | 2018-11-22 | Double-shaft wing folding mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109606634A true CN109606634A (en) | 2019-04-12 |
| CN109606634B CN109606634B (en) | 2022-04-08 |
Family
ID=66003810
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811399745.4A Active CN109606634B (en) | 2018-11-22 | 2018-11-22 | Double-shaft wing folding mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109606634B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104165A (en) * | 2019-05-14 | 2019-08-09 | 三亚学院 | It is fitted in longitudinal folding fixed wing in vertical take-off and landing drone |
| CN110294101A (en) * | 2019-05-20 | 2019-10-01 | 南京航空航天大学 | A kind of auxiliary drive mechanism and its application method for folded wing |
| 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 |
| 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 |
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| GB534106A (en) * | 1939-12-20 | 1941-02-27 | Fairey Aviat Co Ltd | Improvements in or relating to means for aligning folding wings for aircraft |
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| US20100108801A1 (en) * | 2008-08-22 | 2010-05-06 | Orville Olm | Dual rotor helicopter with tilted rotational axes |
| CN103287570A (en) * | 2013-05-31 | 2013-09-11 | 西北工业大学 | Z-shaped folding wing mechanism |
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| CN207536116U (en) * | 2017-11-01 | 2018-06-26 | 成都飞亚航空设备应用研究所有限公司 | A kind of aircraft wing fold mechanism |
| CN207595236U (en) * | 2017-11-17 | 2018-07-10 | 西安云骋电子科技有限公司 | A kind of electric screw empennage for folding wings unmanned plane |
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| GB496003A (en) * | 1937-11-30 | 1938-11-23 | Fairey Aviat Co Ltd | Improvements in or relating to folding wing aircraft |
| GB534106A (en) * | 1939-12-20 | 1941-02-27 | Fairey Aviat Co Ltd | Improvements in or relating to means for aligning folding wings for aircraft |
| US6260799B1 (en) * | 2000-04-24 | 2001-07-17 | Hamilton Sunstrand Corporation | Aircraft wing fold actuation system |
| US20100044499A1 (en) * | 2008-08-22 | 2010-02-25 | Draganfly Innovations Inc. | Six rotor helicopter |
| US20100108801A1 (en) * | 2008-08-22 | 2010-05-06 | Orville Olm | Dual rotor helicopter with tilted rotational axes |
| CN103287570A (en) * | 2013-05-31 | 2013-09-11 | 西北工业大学 | Z-shaped folding wing mechanism |
| CN105882939A (en) * | 2015-02-17 | 2016-08-24 | 空中客车营运有限公司 | Actuation assembly for moving a wing tip device on an aircraft wing |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104165A (en) * | 2019-05-14 | 2019-08-09 | 三亚学院 | It is fitted in longitudinal folding fixed wing in vertical take-off and landing drone |
| CN110294101A (en) * | 2019-05-20 | 2019-10-01 | 南京航空航天大学 | A kind of auxiliary drive mechanism and its application method for folded wing |
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109606634B (en) | 2022-04-08 |
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