CN109606634B - Double-shaft wing folding mechanism - Google Patents
Double-shaft wing folding mechanism Download PDFInfo
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- CN109606634B CN109606634B CN201811399745.4A CN201811399745A CN109606634B CN 109606634 B CN109606634 B CN 109606634B CN 201811399745 A CN201811399745 A CN 201811399745A CN 109606634 B CN109606634 B CN 109606634B
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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 a double-shaft wing folding mechanism which comprises an inner wing crank, an outer wing crank, a rotary actuator, an inner wing folding mechanism, an outer wing folding mechanism and a plurality of inner and outer wing folding joints, wherein the rotary actuator is arranged between the inner wing crank and the outer wing crank and rotates bidirectionally at the same time, the inner wing folding mechanism is installed on the inner wing crank and is connected with an inner wing, the outer wing folding mechanism is installed on the outer wing crank and is connected with an outer wing, the inner and outer wing folding joints are installed on the inner wing crank and the outer wing crank, and each inner and outer wing folding joint is hinged to the inner wing and the outer wing respectively. The invention adopts the bidirectional reverse rotation actuator, adopts the rotation driving form to realize folding and unfolding, and has small occupied space; the invention can effectively realize the large-angle folding of the outer wing of the wing in a limited folding space, and the folding angle can reach more than 130 degrees; the invention ensures the load transmission directness of the inner wing and the outer wing, and reduces the strength limit of the folding mechanism; the invention can be completely arranged in the aerodynamic profile surface of the wing without arranging an aerodynamic bulge, and does not influence the aerodynamic profile of the wing.
Description
Technical Field
The invention relates to the technical field of airplane wing folding, in particular to a double-shaft type wing folding mechanism.
Background
The first aircraft carrier in China already trains navy, and the aircraft carrier which is designed and produced completely and autonomously in China is steadily advancing, so that the development of a complete aircraft carrier fleet which is formed by train-mounted carrier-based aircraft with corresponding models is urgently needed. In order to carry more shipboard aircrafts under the condition of limited space of an aircraft carrier deck and an aircraft garage, the shipboard aircrafts need to have a wing folding function, wherein wings are in an unfolded state in the task of execution, and wings are in a folded state in the process of warehousing and mooring the deck.
The shipboard aircraft has the limitation of the width in the unfolding direction, the wings are required to be folded, and meanwhile, the height of the aircraft hangar of the aircraft carrier is also limited by the height of the aircraft, so that the aircraft height is required to be not more than the height limit of the hangar in the folded state of the wings. The outer wing span-wise ratio of the carrier-based aircraft wing is large, the folded carrier-based aircraft span-wise width is small, the aircraft height limit is met, and the folding angle required by the larger outer wing is larger. Therefore, modern shipboard aircraft require a large-angle wing folding function, and the folding angle is often up to 130 degrees or more.
The requirements of modern fighters on the aerodynamic shape of an airplane are continuously improved, particularly, wings are the main sources of the aerodynamic lift force of the airplane, and the requirements on the aerodynamic shape of the wings are highest. Therefore, the structure, the mechanism and the equipment on the carrier-based aircraft wing can not influence the aerodynamic shape of the wing without special limitation, such as avoiding the situation that the aerodynamic shape of the wing is influenced by bulge and the like as much as possible. Modern shipboard aircrafts require that the wing folding mechanism cannot influence the aerodynamic shape of the wing, and the folding mechanism is arranged in the aerodynamic shape of the wing.
At present, most of wing folding mechanisms of carrier-based aircrafts are single-shaft hinge type folding mechanisms, the folding angle is small, and the folding angle can be increased only by protruding the appearance of the wings. The number of the carrier-based aircraft is more abroad, but only the fighter-15 carrier-based aircraft is available at home, and the wing folding mechanism is a single-shaft hinge type folding mechanism, so that a new wing folding mechanism is urgently needed to meet the requirements of the modern carrier-based aircraft.
Disclosure of Invention
The invention aims to provide a double-shaft wing folding mechanism which is high in practicability, meets the requirements of an airplane folding angle and does not influence the aerodynamic appearance of wings.
The invention is realized by the following technical scheme: the utility model provides a double-axle wing folding mechanism, includes interior wing crank, outer wing crank, sets up including between wing crank and the outer wing crank and two-way rotatory rotary actuator simultaneously, install on the inner wing crank and with the interior wing folding mechanism of being connected, install on the outer wing crank and with the outer wing folding mechanism of being connected, a plurality of interior wing folding joint of installing on inner wing crank and outer wing crank, every interior wing folding joint is articulated in interior wing, outer wing respectively.
Furthermore, in order to better realize the invention, the outer wing folding mechanism comprises an A connecting rod fixedly arranged on the outer wing crank and an outer wing connecting rod hinged with the A connecting rod; and one end of the outer wing connecting rod, which is far away from the connecting rod A, is hinged with the outer wing.
Further, in order to better implement the present invention, the outer wing folding mechanism further includes an outer wing folding tab disposed between the a connecting rod and the outer wing, and the outer wing folding tab is hinged to the a connecting rod.
Furthermore, in order to better realize the invention, the inner wing folding mechanism comprises a connecting rod B fixedly arranged on the inner wing crank and an inner wing connecting rod hinged with the connecting rod B; and one end of the inner wing connecting rod, which is far away from the B connecting rod, is hinged with the inner wing.
Further, in order to better implement the present invention, the inner wing folding mechanism further includes an inner wing folding tab disposed between the B connecting rod and the inner wing, and the inner wing folding tab is hinged to the B connecting rod.
Furthermore, in order to better realize the invention, the inner and outer wing folding joints comprise folding joint bodies, and inner wing joint lugs and outer wing joint lugs which are respectively hinged on the folding joint bodies; the inner wing joint lug is arranged on one side, close to the inner wing, of the folding joint body, and the outer wing joint lug is arranged on one side, close to the outer wing, of the folding joint body.
Further, in order to better implement the present invention, the inner and outer wing folding joints have a triangular prism structure, wherein one end is mounted on the inner wing crank or the outer wing crank; the other two ends are hinged with the inner wing joint lug/the outer wing joint lug.
Furthermore, in order to better realize the invention, the structure of the outer wing folding mechanism is the same as that of the inner wing folding mechanism; the outer wing folding mechanism is arranged on one side, close to the rotary actuator, of the outer wing crank, and the inner wing folding mechanism is arranged on one side, close to the rotary actuator, of the inner wing crank.
Furthermore, in order to better realize the invention, the number of the inner wing folding joints and the outer wing folding joints is three, one of the inner wing folding joints and the outer wing folding joints is arranged at one end of the outer wing crank, which is far away from the rotary actuator, and the other two inner wing folding joints are arranged on the inner wing crank; the inner and outer wing folding joints which are adjacent and arranged on the outer wing crank are connected with the inner and outer wing folding joints arranged on the inner wing crank through rotating shafts.
Furthermore, in order to better realize the invention, the invention also comprises a rotating shaft arranged between the inner and outer wing folding joints of the adjacent outer wing crank and the inner and outer wing folding joints of the outer wing crank; the rotating shaft is provided with a connecting part, and the connecting part is connected with the rotary actuator.
Compared with the prior art, the invention has the following advantages and beneficial effects:
(1) the invention adopts the bidirectional reverse rotation actuator, adopts the rotation driving form to realize folding and unfolding, and has small occupied space;
(2) the invention can effectively realize the large-angle folding of the outer wing of the wing in a limited folding space, and the folding angle can reach more than 130 degrees;
(3) the invention ensures the load transmission directness of the inner wing and the outer wing, and reduces the strength limit of the folding mechanism;
(4) the invention can be completely arranged in the aerodynamic profile surface of the wing without arranging an aerodynamic bulge, and does not influence the aerodynamic profile of the wing.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the present invention in its expanded configuration;
FIG. 3 is a schematic view of the folded structure of the present invention;
FIG. 4 is a schematic view of the folding mechanism arrangement of the present invention;
wherein 1-inner wing joint lug, 2-outer wing joint lug, 3-outer wing folding lug, 4-inner wing folding lug, 5-inner and outer wing 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 rotating shaft, 14-inner wing rotating shaft.
Detailed Description
The present invention will be described in further detail with reference to examples, but the embodiments of the present invention are not limited thereto.
Example 1:
the invention is realized by the following technical scheme, as shown in fig. 1, the biaxial wing folding mechanism comprises an inner wing crank 12, an outer wing crank 11, a rotary actuator 10 which is arranged between the inner wing crank 12 and the outer wing crank 11 and rotates bidirectionally at the same time, an inner wing folding mechanism which is arranged on the inner wing crank 12 and is connected with an inner wing, an outer wing folding mechanism which is arranged on the outer wing crank 11 and is connected with an outer wing, and a plurality of inner and outer wing folding joints 5 which are arranged on the inner wing crank 12 and the outer wing crank 11, wherein each inner and outer wing folding joint 5 is respectively hinged with the inner wing and the outer wing.
It is noted that, with the above-described modification, the present invention is installed in the folded open space between the inner wing separated end face and the outer wing separated end face.
And one ends of the inner wing crank 12 and the outer wing crank 11, which are close to each other, are respectively connected with rotating shafts at two ends of the rotary actuator 10.
When the outer wing is unfolded for use, the rotary actuator 10 is controlled to work, so that the rotating shafts at the two ends of the rotary actuator 10 rotate in the opposite directions simultaneously, the rotating shaft connected with the outer wing crank 11 rotates towards the direction far away from the outer wing, the outer wing folding mechanism is driven by the rotating shaft connected with the outer wing crank 11 to move towards one side far away from the outer wing crank 11, and the outer wing is unfolded relative to the inner wing. And vice versa to achieve folding.
The central axes of the rotating shafts of the outer wing crank 11, the inner wing crank 12 and the rotary actuator 10 are on the same straight line.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
Example 2:
the embodiment is further optimized on the basis of the above embodiment, as shown in fig. 1, and further, in order to better implement the present invention, the outer wing folding mechanism includes an a connecting rod fixedly installed on the outer wing crank 11, and an outer wing connecting rod 8 hinged to the a connecting rod; and one end of the outer wing connecting rod 8, which is far away from the connecting rod A, is hinged with the outer wing.
Further, in order to better implement the present invention, the outer wing folding mechanism further includes an outer wing folding tab 3 disposed between the a connecting rod and the outer wing, and the outer wing folding tab 3 is hinged to the a connecting rod. The outer wing folding lug 3 is fixedly connected with the outer wing.
Further, in order to better realize the invention, the inner wing folding mechanism comprises a B connecting rod fixedly arranged on the inner wing crank 12 and an inner wing connecting rod 9 hinged with the B connecting rod; and one end of the inner wing connecting rod 9, which is far away from the B connecting rod, is hinged with the inner wing.
Further, in order to better implement the present invention, the inner wing folding mechanism further comprises an inner wing folding ear 4 disposed between the B connecting rod and the inner wing, and the inner wing folding ear 4 is hinged to the B connecting rod. The inner wing folding ear piece 4 is fixedly connected with the inner wing.
It should be noted that, through the above improvement, one end of the connecting rod a, which is far away from the outer wing crank 11, is close to the inner wing side and hinged to the outer wing connecting rod 8, and one end of the outer wing connecting rod 8, which is far away from the connecting rod a, is hinged to the outer wing folding piece; one end of the B connecting rod, which is far away from the inner wing crank 12, is close to one side of the outer wing and is hinged with the inner wing connecting rod 9, and one end of the inner wing connecting rod 9, which is far away from the B connecting rod, is hinged with the inner wing folding sheet; under the condition of driving of the rotary actuator 10, the outer wing crank 11 and the inner wing crank 12 rotate and have opposite rotation directions, and when the outer wing crank 11 is folded, the outer wing crank 11 rotates to enable the connecting rod A, the outer wing connecting rod 8 and the outer wing folding piece which are installed on the outer wing crank 11 to rotate around the axis of the rotating shaft of the rotary actuator 10 and enable the outer wing folding piece to approach to one side of the outer wing crank 11, so that the outer wing is folded; the central axes of the rotating shafts of the outer wing crank 11, the inner wing crank 12 and the rotary actuator 10 are on the same straight line, so that the outer wing and the inner wing are both close to the central axis of the rotating shaft of the rotary actuator 10, and the outer wing and the inner wing are folded.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
Example 3:
the present embodiment is further optimized based on the above-mentioned embodiments, as shown in fig. 1,
further, in order to better implement the present invention, the inner and outer wing folding joints 5 comprise a folding joint body, and an inner wing joint lug 1 and an outer wing joint lug 2 respectively hinged to the folding joint body; the inner wing joint lug 1 is arranged on one side, close to the inner wing, of the folding joint body, and the outer wing joint lug 2 is arranged on one side, close to the outer wing, of the folding joint body.
It should be noted that, through the above improvement, the inner and outer wing folding joints 5 are respectively hinged with the inner wing joint lug 1 and the outer wing joint lug 2, and mainly participate in load transfer between the inner wing and the outer wing, so that when the carrier-based aircraft is folded or unfolded, the outer wing and the inner wing both perform biaxial rotation motion around the outer wing crank 11 and the inner wing crank 12.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
Example 4:
the present embodiment is further optimized on the basis of the above-mentioned embodiment, as shown in fig. 1, and further, in order to better implement the present invention, the inner and outer wing folding joints 5 have a triangular prism structure, wherein one end is mounted on the inner wing crank 12 or the outer wing crank 11; the other two ends are hinged with the inner wing joint lug 1/the outer wing joint lug 2.
It should be noted that, with the above improvement, the triangular prism structure reduces the occupied space, so that the folding angle during the folding process is larger.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
Example 5:
the present embodiment is further optimized on the basis of the above embodiment, as shown in fig. 1, and further, in order to better implement the present invention, the structure of the outer wing folding mechanism is the same as that of the inner wing folding mechanism; the outer wing folding mechanism is arranged on one side of the outer wing crank 11 close to the rotary actuator 10, and the inner wing folding mechanism is arranged on one side of the inner wing crank 12 close to the rotary actuator 10.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
Example 6:
the present embodiment is further optimized on the basis of the above-mentioned embodiment, as shown in fig. 1, and further, in order to better implement the present invention, the number of the inner and outer wing folding joints 5 is three, one of which is arranged at the end of the outer wing crank 11 far away from the rotary actuator 10, and the other two are arranged on the inner wing crank 12; the inner and outer wing folding joints 5 which are adjacent and arranged on the outer wing crank 11 are connected with the inner and outer wing folding joints 5 arranged on the inner wing crank 12 through rotating shafts.
Furthermore, in order to better realize the invention, the invention also comprises a rotating shaft arranged between the inner and outer wing folding joints 5 of the adjacent outer wing crank 11 and the inner and outer wing folding joints 5 of the outer wing crank 11; the rotating shaft is provided with a connecting part, and the connecting part is connected with a rotary actuator 10.
An outer wing rotating shaft 13 is arranged between the inner and outer wing folding joints 5 and the outer wing joint lug 1, and an outer wing rotating shaft 14 is arranged between the inner and outer wing folding joints 5 and the inner wing joint lug 2.
The inner and outer wing folding joints 5 are hinged with the outer wing joint lug 1 through an outer wing rotating shaft 13, and the inner and outer wing folding joints are hinged with the inner wing joint lug through an inner wing rotating shaft 14. The longitudinal directions of the outer blade rotation shaft 13 and the inner blade rotation shaft 14 are parallel to the longitudinal direction of the outer blade crank 11.
It should be noted that, through the above improvement, the present invention adopts the folding joint 5 of the inner wing and the outer wing with the triangular prism structure to connect the inner wing and the outer wing, and when the wing is folded and unfolded, the outer wing performs double-rotation-axis folding around the outer wing rotation axis 13 and the inner wing performs double-rotation-axis folding around the inner wing rotation axis 14, so as to realize large-angle folding of the outer wing in a limited folding space, and the folding angle can reach more than 130 degrees.
When the carrier-based aircraft is in the wing unfolding state, the inner and outer wing folding joints 5 participate in the load transmission of the inner and outer wings, and other parts do not participate in the load transmission of the inner and outer wings, so that the load transmission directness of the inner and outer wings is ensured, and the strength limitation on the folding mechanism is reduced.
The rotary actuator 10 adopts a rotary driving mode and electric bidirectional reverse rotary driving, so that the occupied space is small, the electric driving mode is easy to control, the modular design is easy, and the maintenance and the replacement are easy.
The mechanism integrally adopts a concurrent double four-bar linkage to drive the outer wing to complete folding, the concurrent double four-bar linkage realizes the function of folding the outer wing around two rotating shafts, the occupied space is small, and the space outside the folding and separating end surface of the inner wing and the outer wing is not influenced.
The whole set of folding mechanism can be completely arranged in the aerodynamic profile of the wing without arranging an aerodynamic bulge, and the aerodynamic profile of the wing is not influenced.
The rotary actuator 10 of the present invention adopts a bidirectional reverse output rotary actuator 10, which includes a motor and a reverse speed reducer, and can output two reverse rotary motions at the same time to drive the outer wing crank 11 and the inner wing crank 12 to perform the rotary motions in opposite directions.
Preferably, the outer wing crank 11 and the inner wing crank 12 have mechanical external interfaces, so that an external handheld driver can be used for manual wing folding or unfolding.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (8)
1. A twin axle wing folding mechanism which characterized in that: the wing folding device comprises an inner wing crank (12), an outer wing crank (11), a rotary actuator (10) which is arranged between the inner wing crank (12) and the outer wing crank (11) and rotates bidirectionally at the same time, an inner wing folding mechanism which is arranged on the inner wing crank (12) and is connected with an inner wing, an outer wing folding mechanism which is arranged on the outer wing crank (11) and is connected with an outer wing, and a plurality of inner and outer wing folding joints (5) which are arranged on the inner wing crank (12) and the outer wing crank (11), wherein each inner and outer wing folding joint (5) is respectively hinged with the inner wing and the outer wing; the inner and outer wing folding joints (5) comprise folding joint bodies, and inner wing joint lugs (1) and outer wing joint lugs (2) which are respectively hinged on the folding joint bodies; the inner wing joint lug (1) is arranged on one side of the folding joint body close to the inner wing, and the outer wing joint lug (2) is arranged on one side of the folding joint body close to the outer wing; the inner and outer wing folding joints (5) are in a triangular prism structure, and one end part of each folding joint is arranged on the inner wing crank (12) or the outer wing crank (11); the other two ends are hinged with the inner wing joint lug (1)/the outer wing joint lug (2).
2. A twin axle wing folding mechanism as in claim 1, wherein: the outer wing folding mechanism comprises a connecting rod A fixedly arranged on an outer wing crank (11) and an outer wing connecting rod (8) hinged with the connecting rod A; and one end of the outer wing connecting rod (8) far away from the connecting rod A is hinged with the outer wing.
3. A twin-axle wing folding mechanism as in claim 2, wherein: the outer wing folding mechanism further comprises outer wing folding lugs (3) arranged between the connecting rod A and the outer wings, and the outer wing folding lugs (3) are hinged to the connecting rod A.
4. A twin axle wing folding mechanism as in claim 3, wherein: the inner wing folding mechanism comprises a connecting rod B fixedly arranged on an inner wing crank (12) and an inner wing connecting rod (9) hinged with the connecting rod B; and one end of the inner wing connecting rod (9) far away from the B connecting rod is hinged with the inner wing.
5. A twin axle wing folding mechanism as in claim 4 wherein: the inner wing folding mechanism further comprises an inner wing folding lug (4) arranged between the connecting rod B and the inner wing, and the inner wing folding lug (4) is hinged to the connecting rod B.
6. A twin axle wing folding mechanism as in claim 1, wherein: the outer wing folding mechanism and the inner wing folding mechanism have the same structure; the outer wing folding mechanism is arranged on one side, close to the rotary actuator (10), of the outer wing crank (11), and the inner wing folding mechanism is arranged on one side, close to the rotary actuator (10), of the inner wing crank (12).
7. A twin axle wing folding mechanism as in claim 6, wherein: the number of the inner wing folding joints and the outer wing folding joints (5) is three, one of the inner wing folding joints and the outer wing folding joints is arranged at one end of the outer wing crank (11) far away from the rotary actuator (10), and the other two of the inner wing folding joints and the outer wing folding joints are arranged on the inner wing crank (12); the inner and outer wing folding joints (5) which are adjacent and arranged on the outer wing crank (11) are connected with the inner and outer wing folding joints (5) arranged on the inner wing crank (12) through a rotating shaft.
8. A twin axle wing folding mechanism as in claim 7, wherein: the wing-shaped structure also comprises a rotating shaft arranged between the inner and outer wing folding joints (5) of the adjacent outer wing cranks (11) and the inner and outer wing folding joints (5) of the outer wing cranks (11); the rotating shaft is provided with a connecting part, and the connecting part is connected with a 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 |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811399745.4A CN109606634B (en) | 2018-11-22 | 2018-11-22 | Double-shaft wing folding mechanism |
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| CN109606634A CN109606634A (en) | 2019-04-12 |
| CN109606634B true CN109606634B (en) | 2022-04-08 |
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| CN201811399745.4A Active CN109606634B (en) | 2018-11-22 | 2018-11-22 | Double-shaft wing folding mechanism |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN110294101B (en) * | 2019-05-20 | 2022-06-10 | 南京航空航天大学 | Auxiliary driving mechanism for folding wing and using method 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 |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN106697260A (en) * | 2016-06-15 | 2017-05-24 | 陈昌志 | Supersonic helicopter |
| 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 |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8052081B2 (en) * | 2008-08-22 | 2011-11-08 | Draganfly Innovations Inc. | Dual rotor helicopter with tilted rotational axes |
| US20100044499A1 (en) * | 2008-08-22 | 2010-02-25 | Draganfly Innovations Inc. | Six rotor helicopter |
-
2018
- 2018-11-22 CN CN201811399745.4A patent/CN109606634B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN106697260A (en) * | 2016-06-15 | 2017-05-24 | 陈昌志 | Supersonic helicopter |
| 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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| CN109606634A (en) | 2019-04-12 |
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