CN105799915A - Synchronous folding and unfolding mechanism of wings of unmanned aerial vehicle - Google Patents
Synchronous folding and unfolding mechanism of wings of unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105799915A CN105799915A CN201610157671.8A CN201610157671A CN105799915A CN 105799915 A CN105799915 A CN 105799915A CN 201610157671 A CN201610157671 A CN 201610157671A CN 105799915 A CN105799915 A CN 105799915A
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- wing
- sheet
- boss
- driving spring
- annular boss
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention relates to wings of an unmanned aerial vehicle, in particular to a synchronous folding and unfolding mechanism of the wings of the unmanned aerial vehicle. According to the technical scheme, the unmanned aerial vehicle is restrained by a launching barrel before being launched, the wings are in a folded state, a rack, a wing sheet A and a wing sheet B are stacked together in a vertically parallel mode, an unfolding driving spring is subjected to torsion, and a locking driving spring is pressed; when the unmanned aerial vehicle is launched and separated from the barrel, the wing sheet A and the wing sheet B are unfolded towards the left side and the right side around an annular boss under the action of the unfolding driving spring, and meanwhile a tenon A and a tenon B are kept synchronous under restraint of an unfolding synchronization sheet and a limiting strip; after the wing sheet A and the wing sheet B are unfolded to the set position, the locking driving spring drives the lower wing to move upwards, a lower wing boss and an upper wing gap are clamped, an upper wing boss and a lower wing gap are clamped, and locking in the rotating direction is achieved. According to the synchronous folding and unfolding mechanism, it can be guaranteed that the wings are in the same plane after being unfolded, and asymmetry of the pneumatic appearance is avoided.
Description
Technical field
The present invention relates to unmanned plane wing, particularly to a kind of unmanned plane wing-folding development mechanism.
Background technology
Unmanned plane is a kind of advanced technological arms high-effect, low-risk in modern war.In order to improve the unmanned plane Local Adaptation in battlefield, maneuverability, shortens the response time of armament systems, improves the reliability of the use of armament systems, often adopt the cartridge type transmitting form of packaging, accumulating, transmitting integration.
Cartridge type is launched unmanned plane and is adopted the mode of wing-folding to be loaded by the unmanned plane with Foldable exhibition opening mechanism in the launching tube of corresponding bore, liquid/gas pressure energy is converted to mechanical kinetic energy by launching tube, makes unmanned plane accelerate to safe take-off speed in the launching tube of certain length.
For SUAV, often adopt the energy-storage travelling wave tube that flexible member launches as wing, for having the expansion of relatively high aspect ratio wing, require to launch energy on the one hand enough, enable wing to open rapidly；Requiring that wing launches to have certain synchronicity on the other hand, will not there is excessive change in the attitude to ensure unmanned plane.Wing unfolding mechanism widely used at present or lack expansion lazy-tongs, or the lazy-tongs adopted are excessively complicated, and these are all unfavorable for development mechanism application on SUAV.
Summary of the invention
It is an object of the invention to: be directed to the deficiencies in the prior art, it is provided that a kind of unmanned plane wing synchronous folding development mechanism；
The technical scheme is that a kind of unmanned plane wing synchronous folding development mechanism, it includes: launch synchronize sheet, locking driving spring, frame, top wing, lower wing and launch driving spring；
Launch to synchronize sheet and be provided with two yi word pattern chutes；
Frame is provided with the annular boss of concave downward, and annular boss center is provided with installing hole, is provided with two arcuate grooves in left and right in the both sides of annular boss, is provided with parallel positive stop strip in the both sides of arcuate groove；
Top wing includes: fin A and the rotating disk A being connected with fin A；Rotating disk A is provided with trip A, rotary shaft hole and lower wing loose slot；The lower surface of rotating disk A is provided with the top wing boss of arc and the arc top wing breach corresponding with top wing boss；
Lower wing includes: fin B and the rotating disk B being connected with fin B；Rotating disk B is provided with trip B, rotating shaft；The upper surface of rotating disk B is provided with the lower wing boss of arc and the arc lower wing breach corresponding with top wing boss；
Lower wing, top wing, frame are placed from bottom to top, launch to synchronize between two positive stop strips that sheet is arranged on frame, and wherein, rotating shaft is positioned at annular boss after rotary shaft hole；Trip B sequentially passes through an arcuate groove on lower wing loose slot, annular boss, launches to synchronize a yi word pattern chute of sheet；Trip A sequentially passes through another arcuate groove on annular boss, launches to synchronize another yi word pattern chute of sheet；Launching driving spring between top wing and lower wing, its two ends are hooked on trip A, trip B respectively；Locking driving spring is arranged in annular boss, connection rotating shaft, and locked by screw.
Beneficial effect: 1, compare conventional machine wingfold development mechanism, overall structure of the present invention is simple, and mechanism is small and exquisite, takies space in machine few.
2, the present invention adopts lamellar lazy-tongs, processes simple and convenient, ensure that on the one hand the synchronicity that high aspect ratio wing launches, avoids the lazy-tongs processed complexs such as conventionally employed gear, connecting rod on the other hand, and greatly, take up room quality big shortcoming.
3, the wing rotating shaft of the present invention is positioned in the middle of fuselage, and wing root stress is more reasonable.
4, present invention two panels wing when folded state is stacked together, it is to avoid owing to wing chord length is excessive beyond fuselage width, increase wing area；In ensure that after expansion that wing is in the same plane, it is to avoid aerodynamic configuration asymmetric.
Accompanying drawing explanation
Fig. 1 is the explosive view of the present invention；
Fig. 2 is the sectional view of the present invention；
Fig. 3 is the sectional view of frame in the present invention；
Fig. 4 is the structural representation of top wing in the present invention；
Fig. 5 is the structural representation of lower wing in the present invention；
Fig. 6 is the structural representation launching to synchronize sheet in the present invention；
Fig. 7 be the present invention folding time structural representation.
Detailed description of the invention
Referring to accompanying drawing, a kind of unmanned plane wing synchronous folding development mechanism, it includes: launch synchronize sheet 1, locking driving spring 3, frame 4, top wing 5, lower wing 6 and launch driving spring 7；
Launch to synchronize sheet 1 and be provided with two yi word pattern chutes；
Frame 4 is provided with the annular boss 4-3 of concave downward, annular boss 4-3 center and is provided with installing hole 4-4, is provided with two arcuate grooves in left and right in the both sides of annular boss 4-3, is provided with parallel positive stop strip 4-1 in the both sides of arcuate groove；
Top wing 5 includes: fin A5-6 and the rotating disk A5-7 being connected with fin A5-6；Rotating disk A5-7 is provided with trip A5-2, rotary shaft hole 5-1 and lower wing loose slot 5-4；The lower surface of rotating disk A5-7 is provided with the top wing boss 5-3 of arc and the arc top wing breach 5-5 corresponding with top wing boss 5-3；
Lower wing 6 includes: fin B6-5 and the rotating disk B6-6 being connected with fin B6-5；Rotating disk B6-6 is provided with trip B6-1, rotating shaft 6-2；The upper surface of rotating disk B6-6 is provided with the lower wing boss 6-4 of arc and the arc lower wing breach 6-3 corresponding with top wing boss 5-3；
Lower wing 6, top wing 5, frame 4 are placed from bottom to top, launch to synchronize between two positive stop strip 4-1 that sheet 1 is arranged on frame 4, and wherein, rotating shaft 6-2 is positioned at annular boss 4-3 after rotary shaft hole 5-1；Trip B6-1 sequentially passes through an arcuate groove on lower wing loose slot 5-4, annular boss 4-3, launches to synchronize a yi word pattern chute of sheet 1；Trip A5-2 sequentially passes through another arcuate groove on annular boss 4-3, launches to synchronize another yi word pattern chute of sheet 1；Launching driving spring 7 between top wing 5 and lower wing 6, its two ends are hooked on trip A5-2, trip B6-1 respectively；Locking driving spring 3 is arranged in annular boss 4-3, connection rotating shaft 6-2, and locked by screw 2.
Unmanned plane is in folded state by the constraint wing of launching tube before transmission, and frame 4 is parallel up and down with fin A5-6, fin B6-5 to be stacked together, and now launches driving spring 7 and is turned round, locks driving spring 3 pressurized；When unmanned plane is launched after cylinder, fin A5-6, fin B6-5 launch around annular boss 4-3 both sides to the left and right under the effect launching driving spring 7, trip A5-2, trip B6-1 motion in the yi word pattern groove launching synchronization sheet 1 simultaneously, and order about described synchronization sheet 1 and move along fuselage datum direction, it is ensured that both wings expanded angle is identical；After fin A5-6, fin B6-5 are deployed into setting position, locking driving spring 3 drives lower wing 6 to move upward, lower wing boss 6-4 engages with top wing breach 5-5, top wing boss 5-3 engages with lower wing breach 6-3 so that two aerofoils are in same plane and realize the locking of direction of rotation.
Claims (1)
1. a unmanned plane wing synchronous folding development mechanism, it is characterized in that, it includes: launch synchronize sheet (1), locking driving spring (3), frame (4), top wing (5), lower wing (6) and launch driving spring (7)；
Described expansion synchronizes sheet (1) and is provided with two yi word pattern chutes；
Described frame (4) is provided with the annular boss (4-3) of concave downward, described annular boss (4-3) center is provided with installing hole (4-4), it is provided with two arcuate grooves in left and right in the both sides of described annular boss (4-3), is provided with parallel positive stop strip (4-1) in the both sides of described arcuate groove；
Described top wing (5) including: fin A (5-6) and the rotating disk A (5-7) being connected with described fin A (5-6)；Described rotating disk A (5-7) is provided with trip A (5-2), rotary shaft hole (5-1) and lower wing loose slot (5-4)；The lower surface of described rotating disk A (5-7) is provided with the top wing boss (5-3) of arc and arc top wing breach (5-5) corresponding with described top wing boss (5-3)；
Described lower wing (6) including: fin B (6-5) and the rotating disk B (6-6) being connected with described fin B (6-5)；Described rotating disk B (6-6) is provided with trip B (6-1), rotating shaft (6-2)；The upper surface of described rotating disk B (6-6) is provided with the lower wing boss (6-4) of arc and arc lower wing breach (6-3) corresponding with described top wing boss (5-3)；
Described lower wing (6), described top wing (5), described frame (4) are placed from bottom to top, described expansion synchronizes between two described positive stop strips (4-1) that sheet (1) is arranged on described frame (4), wherein, described rotating shaft (6-2) is positioned at described annular boss (4-3) after described rotary shaft hole (5-1)；Described trip B (6-1) sequentially passes through a yi word pattern chute of an arcuate groove on described lower wing loose slot (5-4), described annular boss (4-3), described expansion synchronization sheet (1)；Described trip A (5-2) sequentially passes through another yi word pattern chute of another arcuate groove on described annular boss (4-3), described expansion synchronization sheet (1)；Described expansion driving spring (7) is positioned between described top wing (5) and described lower wing (6), and its two ends are hooked on described trip A (5-2), described trip B (6-1) respectively；Described locking driving spring (3) is arranged in described annular boss (4-3), connects described rotating shaft (6-2), and locked by screw (2).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610157671.8A CN105799915B (en) | 2016-03-18 | 2016-03-18 | Unmanned plane wing synchronous folding development mechanism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610157671.8A CN105799915B (en) | 2016-03-18 | 2016-03-18 | Unmanned plane wing synchronous folding development mechanism |
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| CN105799915A true CN105799915A (en) | 2016-07-27 |
| CN105799915B CN105799915B (en) | 2017-11-14 |
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| CN201610157671.8A Expired - Fee Related CN105799915B (en) | 2016-03-18 | 2016-03-18 | Unmanned plane wing synchronous folding development mechanism |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106114820A (en) * | 2016-07-28 | 2016-11-16 | 北京航空航天大学 | A kind of both wings can synchronize coaxial coplanar and become the unmanned vehicle change wing mechanism at angle of sweep |
| CN107380403A (en) * | 2017-08-31 | 2017-11-24 | 佛山市龙远科技有限公司 | A kind of folding aircraft of wing |
| CN107521662A (en) * | 2017-08-31 | 2017-12-29 | 佛山市龙远科技有限公司 | A kind of folding individual layer wing aircraft of wing |
| CN107741180A (en) * | 2017-09-18 | 2018-02-27 | 西北工业大学 | A kind of wing spreading device of slave carrier |
| CN107776870A (en) * | 2017-10-27 | 2018-03-09 | 成都云鼎智控科技有限公司 | A kind of wing-folding locked component and unmanned plane |
| CN108146613A (en) * | 2017-12-28 | 2018-06-12 | 西安特种飞行器工程研究院有限公司 | A kind of unmanned plane with retaining mechanism |
| CN108190003A (en) * | 2017-12-28 | 2018-06-22 | 陕西中科博亿电子科技有限公司 | A kind of unmanned plane with buffer gear |
| CN108284939A (en) * | 2018-03-19 | 2018-07-17 | 王洪涛 | A kind of folding ejection unmanned plane |
| CN108688793A (en) * | 2018-07-27 | 2018-10-23 | 中国工程物理研究院总体工程研究所 | Cartridge type emits unmanned plane wing-folding unfolding mechanism |
| CN109263858A (en) * | 2018-10-30 | 2019-01-25 | 彩虹无人机科技有限公司 | A kind of coaxial wingfold mechanism |
| CN109367760A (en) * | 2018-09-21 | 2019-02-22 | 北京大翔航空科技有限公司 | A kind of light-duty unmanned plane wing-folding unfolding mechanism |
| CN109502009A (en) * | 2018-12-11 | 2019-03-22 | 湖北航天飞行器研究所 | A kind of aircraft folding wings locking mechanism |
| CN109631684A (en) * | 2018-11-28 | 2019-04-16 | 成都云鼎智控科技有限公司 | A kind of single axle wing structure and the emitter for having the wing structure |
| CN109625242A (en) * | 2018-11-28 | 2019-04-16 | 成都云鼎智控科技有限公司 | A kind of wing structure, a kind of emitter and the method for shortening its axial length |
| WO2020022972A3 (en) * | 2017-12-27 | 2020-02-27 | Roketsan Roket Sanayii Ticaret A.S | Wing deployment mechanism |
| CN112572764A (en) * | 2020-12-24 | 2021-03-30 | 中国航天空气动力技术研究院 | Controllable big aspect ratio unmanned aerial vehicle wing rotary folding mechanism who expandes |
| CN115143845A (en) * | 2022-08-02 | 2022-10-04 | 北京奥航坤宇科技有限公司 | Folding missile wing structure of flying missile |
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| US20120280080A1 (en) * | 2011-05-03 | 2012-11-08 | Stark Aerospace, Inc. | Folding wing for aircraft |
| CN103010453A (en) * | 2012-12-27 | 2013-04-03 | 北京理工大学 | Unmanned plane folded wing unfolding and locking device |
| CN103661919A (en) * | 2013-12-23 | 2014-03-26 | 北京理工大学 | Wing folding mechanism based on flex-wing aircraft |
| CN103837045A (en) * | 2014-02-24 | 2014-06-04 | 中国航天时代电子公司 | Foldable diamond-shaped missile wing spread system |
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| CN105253293A (en) * | 2015-10-22 | 2016-01-20 | 镇江顺宇飞行器有限公司 | Small super-short-range unmanned aerial vehicle system provided with folding wings |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106114820A (en) * | 2016-07-28 | 2016-11-16 | 北京航空航天大学 | A kind of both wings can synchronize coaxial coplanar and become the unmanned vehicle change wing mechanism at angle of sweep |
| CN107380403A (en) * | 2017-08-31 | 2017-11-24 | 佛山市龙远科技有限公司 | A kind of folding aircraft of wing |
| CN107521662A (en) * | 2017-08-31 | 2017-12-29 | 佛山市龙远科技有限公司 | A kind of folding individual layer wing aircraft of wing |
| CN107741180A (en) * | 2017-09-18 | 2018-02-27 | 西北工业大学 | A kind of wing spreading device of slave carrier |
| CN107776870A (en) * | 2017-10-27 | 2018-03-09 | 成都云鼎智控科技有限公司 | A kind of wing-folding locked component and unmanned plane |
| WO2020022972A3 (en) * | 2017-12-27 | 2020-02-27 | Roketsan Roket Sanayii Ticaret A.S | Wing deployment mechanism |
| CN108190003A (en) * | 2017-12-28 | 2018-06-22 | 陕西中科博亿电子科技有限公司 | A kind of unmanned plane with buffer gear |
| CN108146613A (en) * | 2017-12-28 | 2018-06-12 | 西安特种飞行器工程研究院有限公司 | A kind of unmanned plane with retaining mechanism |
| CN108190003B (en) * | 2017-12-28 | 2022-07-15 | 陕西中科博亿电子科技有限公司 | Unmanned aerial vehicle with buffer gear |
| CN108146613B (en) * | 2017-12-28 | 2022-07-15 | 西安特种飞行器工程研究院有限公司 | Unmanned aerial vehicle with locking mechanism |
| CN108284939A (en) * | 2018-03-19 | 2018-07-17 | 王洪涛 | A kind of folding ejection unmanned plane |
| CN108688793A (en) * | 2018-07-27 | 2018-10-23 | 中国工程物理研究院总体工程研究所 | Cartridge type emits unmanned plane wing-folding unfolding mechanism |
| CN108688793B (en) * | 2018-07-27 | 2023-11-24 | 中国工程物理研究院总体工程研究所 | Folding and unfolding mechanism for wings of barrel-type launching unmanned aerial vehicle |
| CN109367760A (en) * | 2018-09-21 | 2019-02-22 | 北京大翔航空科技有限公司 | A kind of light-duty unmanned plane wing-folding unfolding mechanism |
| CN109263858A (en) * | 2018-10-30 | 2019-01-25 | 彩虹无人机科技有限公司 | A kind of coaxial wingfold mechanism |
| CN109625242A (en) * | 2018-11-28 | 2019-04-16 | 成都云鼎智控科技有限公司 | A kind of wing structure, a kind of emitter and the method for shortening its axial length |
| CN109631684A (en) * | 2018-11-28 | 2019-04-16 | 成都云鼎智控科技有限公司 | A kind of single axle wing structure and the emitter for having the wing structure |
| CN109502009B (en) * | 2018-12-11 | 2022-06-07 | 湖北航天飞行器研究所 | Aircraft folding wing locking mechanism |
| CN109502009A (en) * | 2018-12-11 | 2019-03-22 | 湖北航天飞行器研究所 | A kind of aircraft folding wings locking mechanism |
| CN112572764A (en) * | 2020-12-24 | 2021-03-30 | 中国航天空气动力技术研究院 | Controllable big aspect ratio unmanned aerial vehicle wing rotary folding mechanism who expandes |
| CN115143845A (en) * | 2022-08-02 | 2022-10-04 | 北京奥航坤宇科技有限公司 | Folding missile wing structure of flying missile |
| CN115143845B (en) * | 2022-08-02 | 2023-09-12 | 北京奥航坤宇科技有限公司 | Folding missile wing structure of patrol missile |
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| CN105799915B (en) | 2017-11-14 |
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