CN112918659A - Folding structure and folding method of airplane wing - Google Patents
Folding structure and folding method of airplane wing Download PDFInfo
- Publication number
- CN112918659A CN112918659A CN202110273463.5A CN202110273463A CN112918659A CN 112918659 A CN112918659 A CN 112918659A CN 202110273463 A CN202110273463 A CN 202110273463A CN 112918659 A CN112918659 A CN 112918659A
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- wing
- folding
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- wings
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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
Abstract
A folding structure and a folding method of an airplane wing are provided, the airplane wing comprises a central wing and a folding wing, a folding mechanism is arranged between the central wing and the folding wing, the folding mechanism comprises a Z-shaped rotating shaft and a hydraulic telescopic rod, two ends of the Z-shaped rotating shaft and two ends of the hydraulic telescopic rod are respectively connected with the central wing and the folding wing, the Z-shaped rotating shaft is provided with a first rotating surface and a second rotating surface which are perpendicular to each other, the first rotating surface is parallel to a back beam of the folding wing, the second rotating surface is perpendicular to the back beam of the central wing, and the hydraulic telescopic rod can push the folding wing to rotate around the first rotating surface and the second rotating surface, so that the folding wing is folded in the downward and backward directions relative to the central wing.
Description
Technical Field
The invention relates to the technical field of airplane structure design, in particular to a folding structure and a folding method of airplane wings.
Background
On the aircraft carrier, as the deck needs to stop more fighters and other types of military carrier-based aircrafts, the carrier-based aircrafts mostly adopt upwards folded wings so as to save the space of the deck and stop more fighters. However, the disc-shaped carrier-based radar is mounted at the top of the aircraft body of the carrier-based early warning aircraft, so that the aircraft cannot use the upward folding wings, the radar can be collided when the wings are folded too much, the folding quantity is small, and the occupied area is reduced. Due to the large size of the non-folding carrier-based early warning aircraft, the deck vacancy of at least two carrier-based aircraft can be occupied, and therefore the total number of the carrier-based aircraft is reduced.
Disclosure of Invention
The application aims to provide a folding structure and a folding method of an airplane wing. The folding mode of the wings is back folding, so that the situation that the wings collide with the top radar cabin after being folded is avoided.
The utility model provides a beta structure of aircraft wing, the aircraft wing contain central wing and folding wing, its characterized in that has a folding mechanism between central wing and folding wing, and this folding mechanism contains Z shape pivot and hydraulic telescoping rod, and the both ends of Z shape pivot and hydraulic telescoping rod are connected with central wing and folding wing respectively, the Z shape pivot on have two mutually perpendicular's first plane of rotation and second plane of rotation, first plane of rotation is parallel with the back beam of folding wing, the second plane of rotation is perpendicular with the back beam of central wing, hydraulic telescoping rod can promote folding wing and rotate around first plane of rotation and second plane of rotation, makes folding wing folding relative central wing down the rear to.
A folding cabin is arranged between the central wing and the folding wings, the folding cabin is an inclined gap cavity with the upper surface far away from the central wing and the lower surface close to the central wing, the inner cabin wall of the folding cabin is a butt joint surface of the central wing, the outer cabin wall of the folding cabin is a butt joint surface of the folding wings, and the shape wall plate of the central wing extends to be the shape wall plate of the folding cabin.
The front end of the Z-shaped rotating shaft is connected to the outer side of the back beam of the folding wing, the first rotating surface of the Z-shaped rotating shaft is parallel to the back beam of the folding wing, the rear end of the Z-shaped rotating shaft is connected to the outer side of the back beam of the central wing through a cantilever joint, and the second rotating surface of the Z-shaped rotating shaft is perpendicular to the back beam of the central wing.
In the folding cabin, a first support is arranged on the butt joint face of the central wing, a through hole is formed in the butt joint face of the folding wing, the fixed end of the hydraulic telescopic rod is connected in the folding wing box, and the telescopic end of the hydraulic telescopic rod penetrates through the through hole in the butt joint face of the folding wing and is hinged to the first support on the butt joint face of the central wing.
The fixed end of the hydraulic telescopic rod is hinged with a second support through a universal joint, and the second support is positioned on a rib plate of the folding wing box.
In the folding cabin, an electromagnetic lock structure is also arranged to connect the central wing butt joint surface and the folding wing butt joint surface.
The electromagnetic lock structure comprises a first lock body and a second lock body, wherein the first lock body is provided with an electromagnetic valve, the first lock body is fixed on the wall of one side of the folding cabin, and the second lock body is fixed on the wall of the other side of the folding cabin.
The application also provides a folding method of the airplane wing, which is characterized by comprising the following steps: 1) the aircraft wing comprises a folding structure of the aircraft wing; 2) when the aircraft wings are folded from an unfolded state, firstly, an electromagnetic lock structure between a central wing butt joint surface and a folding wing butt joint surface is opened through a controller, a hydraulic telescopic rod is operated to extend, the hydraulic telescopic rod pushes the folding wings to rotate around a first rotating surface and a second rotating surface of a Z-shaped rotating shaft, so that the folding wings are folded downwards and backwards relative to the central wings, and after the folding wings are folded in place, the controller locks the state of the hydraulic telescopic rod; 3) when the aircraft wings are unfolded from the folded state, firstly, the hydraulic telescopic rod is unlocked through the controller, then the hydraulic telescopic rod is operated to retract, the hydraulic telescopic rod pulls the folding wings to reversely rotate around the first rotating surface and the second rotating surface of the Z-shaped rotating shaft, so that the folding wings return to the positions of the unfolded state of the aircraft wings, the controller locks the state of the hydraulic telescopic rod, and then the electromagnetic lock structure between the butt joint surface of the central wing and the butt joint surface of the folding wings is locked.
The beneficial effect of this application lies in: the folding wing is driven by the hydraulic telescopic rod, and the rotating shaft device rotates the folding wing to fold the folding wing backwards, so that the situation that the wing collides with a radar on the top of an airplane in the folding process and after folding is avoided. The folding wing reduces the occupied area of the carrier-based early warning aircraft when the large-scale top radar cabin is installed and the wing cannot be folded, so that more airplanes can be parked on a deck.
The present application will be described in further detail with reference to the accompanying drawings.
Drawings
Fig. 1 is a schematic view showing the unfolded state of the center wing and the folding wings.
FIG. 2 is a schematic view of the center wing and folding wing folding mechanism.
FIG. 3 is a schematic view of the center wing butt joint surface structure.
Fig. 4 is a schematic view of the structure of the butt-joint surface of the folding wing.
Fig. 5 is a schematic view showing the folded state of the folding wings downward and rearward relative to the central wing.
The numbering in the figures illustrates: the device comprises a central wing 1, a folding wing 2, a folding cabin 3, a Z-shaped rotating shaft 4, a first rotating surface 5, a second rotating surface 6, a central wing rear beam 7, a folding wing rear beam 8, a cantilever joint 9, a hydraulic telescopic rod 10, a first support 11, a universal joint 12, a second support 13, a rib plate 14, an electromagnetic lock structure 15, an electromagnetic valve 16, a first lock body 17, a central wing butting surface 18, a folding wing butting surface 19, a hole 20 and a second lock body 21.
Detailed Description
Referring to the drawings, the present application relates to a folding structure of an aircraft wing, which includes a central wing 1 fixed to a fuselage and a folding wing 2 movable relative to the central wing by a folding mechanism. Folding mechanism is located between central wing 1 and the folding wing 2, and this folding mechanism contains Z shape pivot 4 and hydraulic telescoping rod 10 and electromagnetic lock 15, and Z shape pivot 4 and hydraulic telescoping rod 10's both ends are connected with central wing 1 and folding wing 2 respectively, Z shape pivot 4 on have two mutually perpendicular's first plane of rotation 5 and second plane of rotation 6, first plane of rotation 5 is parallel with folding wing back beam 8, second plane of rotation 6 is perpendicular with central wing back beam 7, hydraulic telescoping rod 10 can push folding wing 2 and rotate around first plane of rotation 5 and second plane of rotation 6, makes folding wing 2 folding relative central wing 1 backward direction down.
In order to install a folding mechanism of the folding wing and ensure the aerodynamic shape of the folding wing in an unfolded state, a folding cabin 3 is designed between a central wing 1 and the folding wing 2, the folding cabin 3 is an inclined gap cavity with an upper surface far away from the central wing 1 and a lower surface close to the central wing 2, the inner cabin wall of the folding cabin 3 is a central wing butt joint surface 18, the outer cabin wall of the folding cabin is a folding wing butt joint surface 19, and the shape wall plate of the central wing extends to be the shape wall plate of the folding cabin 3. The first support 11 is arranged on the central wing butt-joint surface 18 in the folding cabin 3, the through hole 20 is arranged on the folding wing butt-joint surface 19, the fixed end of the hydraulic telescopic rod 10 is connected in the wing box of the folding wing 2, and the telescopic end of the hydraulic telescopic rod 10 penetrates through the through hole 20 on the folding wing butt-joint surface 19 and is hinged with the first support 11 on the central wing butt-joint surface 18. In order to ensure the posture change of the hydraulic telescopic rod 10 in the folding wing folding process, the fixed end of the hydraulic telescopic rod 10 is hinged with a second support 13 through a universal joint 12, and the second support 13 is positioned on a folding wing box rib plate 14.
The front end of the Z-shaped rotating shaft 4 is connected to the outer side of the folding wing back beam 8, the first rotating surface 5 of the Z-shaped rotating shaft 4 is parallel to the folding wing back beam 8, the rear end of the Z-shaped rotating shaft 4 is connected to the outer side of the central wing back beam 7 through the cantilever joint 9, and the second rotating surface 6 of the Z-shaped rotating shaft 4 is perpendicular to the central wing back beam 7.
In the embodiment, the electromagnetic lock structure 15 in the folding chamber 3 comprises a first lock body 17 and a second lock body 21 with an electromagnetic valve 16, the electromagnetic valve 16 and the first lock body 16 are fixed on one side wall of the folding chamber 3 on the butt surface of the central wing, the second lock body 21 is fixed on the other side wall of the folding chamber, if the electromagnetic valve 16 and the first lock body 16 are arranged on the butt surface of the central wing, the second lock body 21 is fixed on the butt surface of the folding wing, and vice versa.
When the aircraft wing is folded from an unfolding state, firstly, the electromagnetic lock structure 15 between the central wing butt joint surface 18 and the folding wing butt joint surface 19 is opened through the controller, the connection and locking of the electromagnetic lock structure 15 on the central wing butt joint surface 18 and the folding wing butt joint surface 19 are released, then the hydraulic telescopic rod 10 is operated to extend, the hydraulic telescopic rod 10 pushes the folding wing 2 to rotate around the first rotating surface 5 and the second rotating surface 6 of the Z-shaped rotating shaft 4, the folding wing 2 is folded downwards and backwards relative to the central wing 1, and after the folding wing 2 is folded in place, the controller locks the state of the hydraulic telescopic rod 10; when the aircraft wings are unfolded from the folded state, firstly, the hydraulic telescopic rod 10 is unlocked through the controller, then the hydraulic telescopic rod 10 is operated to retract, the hydraulic telescopic rod 10 pulls the folding wings 2 to reversely rotate around the first rotating surface 5 and the second rotating surface 6 of the Z-shaped rotating shaft 4, so that the folding wings 2 return to the positions of the unfolded state of the aircraft wings, the controller locks the state of the hydraulic telescopic rod 10, and then the electromagnetic lock structure 15 between the butt joint surface of the central wing and the butt joint surface of the folding wings is locked.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (8)
1. The utility model provides a beta structure of aircraft wing, the aircraft wing contain central wing and folding wing, its characterized in that has a folding mechanism between central wing and folding wing, and this folding mechanism contains Z shape pivot and hydraulic telescoping rod, and the both ends of Z shape pivot and hydraulic telescoping rod are connected with central wing and folding wing respectively, the Z shape pivot on have two mutually perpendicular's first plane of rotation and second plane of rotation, first plane of rotation is parallel with the back beam of folding wing, the second plane of rotation is perpendicular with the back beam of central wing, hydraulic telescoping rod can promote folding wing and rotate around first plane of rotation and second plane of rotation, makes folding wing folding relative central wing down the rear to.
2. A wing collapse structure according to claim 1 wherein the central wing and the folding wing define a folding chamber therebetween, the folding chamber being a canted slot cavity having an upper surface remote from the central wing and a lower surface adjacent the central wing, the inner wall of the folding chamber defining the interface surface of the central wing, the outer wall of the folding chamber defining the interface surface of the folding wing, and the profile wall of the central wing extending as the profile wall of the folding chamber.
3. A folding structure of an airplane wing according to claim 1 or 2, wherein the front end of the Z-shaped rotating shaft is connected to the outside of the back beam of the folding wing, the first rotating surface of the Z-shaped rotating shaft is parallel to the back beam of the folding wing, the rear end of the Z-shaped rotating shaft is connected to the outside of the back beam of the central wing through a cantilever joint, and the second rotating surface of the Z-shaped rotating shaft is perpendicular to the back beam of the central wing.
4. A wing folding structure for an aircraft as claimed in claim 1 or 2, wherein the folding chamber has a first seat on the abutting surface of the central wing, a through hole on the abutting surface of the folding wing, the fixed end of the hydraulic telescopic rod is connected to the wing box of the folding wing, and the telescopic end of the hydraulic telescopic rod passes through the through hole on the abutting surface of the folding wing and is hinged to the first seat on the abutting surface of the central wing.
5. An aircraft wing folding structure as claimed in claim 4, wherein the fixed end of said hydraulic telescoping rod is articulated to a second support via a universal joint, said second support being located on the rib of the wing box.
6. A wing folding structure for an aircraft as claimed in claim 1 or 2, wherein an electromagnetic lock structure is provided in the folding chamber to connect the central wing abutment surface and the folding wing abutment surface.
7. A wing fold arrangement according to claim 6, wherein the electromagnetic lock arrangement comprises a first lock body having an electromagnetic valve and a second lock body, the first lock body being secured to one side of the folding bay wall and the second lock body being secured to the other side of the folding bay wall.
8. A method of folding an aircraft wing, comprising: 1) the aircraft wing comprises a folded structure of the aircraft wing according to any one of claims 1 to 7; 2) when the aircraft wings are folded from an unfolded state, firstly, an electromagnetic lock structure between a central wing butt joint surface and a folding wing butt joint surface is opened through a controller, a hydraulic telescopic rod is operated to extend, the hydraulic telescopic rod pushes the folding wings to rotate around a first rotating surface and a second rotating surface of a Z-shaped rotating shaft, so that the folding wings are folded downwards and backwards relative to the central wings, and after the folding wings are folded in place, the controller locks the state of the hydraulic telescopic rod; 3) when the aircraft wings are unfolded from the folded state, firstly, the hydraulic telescopic rod is unlocked through the controller, then the hydraulic telescopic rod is operated to retract, the hydraulic telescopic rod pulls the folding wings to reversely rotate around the first rotating surface and the second rotating surface of the Z-shaped rotating shaft, so that the folding wings return to the positions of the unfolded state of the aircraft wings, the controller locks the state of the hydraulic telescopic rod, and then the electromagnetic lock structure between the butt joint surface of the central wing and the butt joint surface of the folding wings is locked.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110273463.5A CN112918659A (en) | 2021-03-12 | 2021-03-12 | Folding structure and folding method of airplane wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110273463.5A CN112918659A (en) | 2021-03-12 | 2021-03-12 | Folding structure and folding method of airplane wing |
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| Publication Number | Publication Date |
|---|---|
| CN112918659A true CN112918659A (en) | 2021-06-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110273463.5A Pending CN112918659A (en) | 2021-03-12 | 2021-03-12 | Folding structure and folding method of airplane wing |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114348238A (en) * | 2021-12-23 | 2022-04-15 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Pull rod type airplane folding wing tip and operation method thereof |
| CN114802706A (en) * | 2022-05-12 | 2022-07-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle wing flattening control method and system |
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| CN105711811A (en) * | 2016-01-27 | 2016-06-29 | 北京航空航天大学 | Wing folding mechanism |
| CN106741849A (en) * | 2017-03-09 | 2017-05-31 | 北京奇正数元科技股份有限公司 | A kind of foldable folding and unfolding wing of SUAV |
| CN107757273A (en) * | 2017-09-27 | 2018-03-06 | 北京航空航天大学 | A kind of hovercar |
| CN109878697A (en) * | 2019-04-10 | 2019-06-14 | 王继华 | Folding wing and fixed-wing Multi-axis aircraft |
| CN110282117A (en) * | 2019-07-10 | 2019-09-27 | 黄山鲸鲨飞行器科技有限公司 | A kind of city VTOL aircraft having wing-folding storage function |
| CN111232185A (en) * | 2018-11-28 | 2020-06-05 | 海鹰航空通用装备有限责任公司 | Wing surface folding and unfolding mechanism |
| CN112061376A (en) * | 2020-08-24 | 2020-12-11 | 西北工业大学 | Independently fix a position collapsible freight transportation glider |
| CN212332952U (en) * | 2020-05-08 | 2021-01-12 | 新乡市永安机械设备有限公司 | Space folding wing structure |
-
2021
- 2021-03-12 CN CN202110273463.5A patent/CN112918659A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105711811A (en) * | 2016-01-27 | 2016-06-29 | 北京航空航天大学 | Wing folding mechanism |
| CN106741849A (en) * | 2017-03-09 | 2017-05-31 | 北京奇正数元科技股份有限公司 | A kind of foldable folding and unfolding wing of SUAV |
| CN107757273A (en) * | 2017-09-27 | 2018-03-06 | 北京航空航天大学 | A kind of hovercar |
| CN111232185A (en) * | 2018-11-28 | 2020-06-05 | 海鹰航空通用装备有限责任公司 | Wing surface folding and unfolding mechanism |
| CN109878697A (en) * | 2019-04-10 | 2019-06-14 | 王继华 | Folding wing and fixed-wing Multi-axis aircraft |
| CN110282117A (en) * | 2019-07-10 | 2019-09-27 | 黄山鲸鲨飞行器科技有限公司 | A kind of city VTOL aircraft having wing-folding storage function |
| CN212332952U (en) * | 2020-05-08 | 2021-01-12 | 新乡市永安机械设备有限公司 | Space folding wing structure |
| CN112061376A (en) * | 2020-08-24 | 2020-12-11 | 西北工业大学 | Independently fix a position collapsible freight transportation glider |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114348238A (en) * | 2021-12-23 | 2022-04-15 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Pull rod type airplane folding wing tip and operation method thereof |
| CN114348238B (en) * | 2021-12-23 | 2024-01-16 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Pull rod type aircraft folding wing tip and operation method thereof |
| CN114802706A (en) * | 2022-05-12 | 2022-07-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle wing flattening control method and system |
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