CN102556336A - Wing fast unfolding device for folding-wing unmanned plane - Google Patents
Wing fast unfolding device for folding-wing unmanned plane Download PDFInfo
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- CN102556336A CN102556336A CN201110456520XA CN201110456520A CN102556336A CN 102556336 A CN102556336 A CN 102556336A CN 201110456520X A CN201110456520X A CN 201110456520XA CN 201110456520 A CN201110456520 A CN 201110456520A CN 102556336 A CN102556336 A CN 102556336A
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Abstract
The invention discloses a wing fast unfolding device for a folding-wing unmanned plane, belonging to the technical field of structures of folding-wing unmanned planes. The wing fast unfolding device comprises a fixing plate, a left wing, a right wing, rotating shafts of wings, a bearing, a bearing seat, a bearing cover, a rocker arm, a connecting rod and an actuator, wherein the two rotating shafts of the wings are vertically fixed below a horizontal fixing plate inside a plane body through the bearing seat, the bearing and the bearing cover; the two rotating shafts of the wings are respectively positioned on the left and right sides of the central axis of the plane body; the left and right wings are fixed above the fixing plate through the upper ends of the two rotating shafts of the wings; and the lower ends of the rotating shafts of the wings are fixedly connected with one end of the rocker arm respectively which is horizontally arranged, the other end of the rocker arm is hinged with two connecting ends of the connecting rod, and the other end of the connecting rod is hinged with the actuator arranged along the axis of the plane body. With the adoption of the wing fast unfolding device, the folding wings can be fast unfolded effectively, and the wing fast unfolding device is simple in structure, convenient to realize, fast in unfolding, and good in synchronism.
Description
Technical field
The present invention relates to a kind of wing expanding unit, be specifically related to a kind of folding wings unmanned plane wing rapid deployment device, belong to folding wings unmanned vehicle technical field of structures.
Background technology
Unmanned vehicle is the not manned craft of controlling through radio robot or airborne computer stored program controlled.Unmanned vehicle is simple in structure, use cost is low, not only can accomplish the task that manned aircraft is carried out, and more is applicable to the task that people's aircraft should not be carried out, like scouting, air rescue commander and the remote sensing monitoring of hazardous location.
Mainly on the market now use following three kinds: fixedly aerofoil profile unmanned plane, pilotless helicopter and driverless operation dirigible; Compare with these ripe unmanned planes, the largest benefit of folding wings unmanned vehicle is saved the space exactly, and is easy to carry and transport; Improved the convenience of unmanned vehicle greatly; But because evening is wanted in its research starting, and technology is comparatively complicated, hereat in use present commercial market, also is in space state basically.
Summary of the invention
In view of this, the invention provides a kind of folding wings unmanned plane wing rapid deployment device, can make wing realize quick, synchronous expansion.
A kind of folding wings unmanned plane wing rapid deployment device comprises adapter plate, port wing, starboard wing, wing rotating shaft, bearing, bearing seat, bearing cap shim, rocking arm, connecting rod and actuator; Its annexation is following: two wing rotating shafts vertically are fixed on the below of the horizontal fixed plate of fuselage interior respectively through bearing seat, bearing and bearing cap shim; Two wing rotating shafts lay respectively at the left and right sides of fuselage central axis; Port wing and starboard wing are fixed on the top of adapter plate through the upper end of two wing rotating shafts; The lower end of wing rotating shaft is an end of the horizontally disposed rocking arm of captive joint separately; a coupling end of the rocking arm other end and connecting rod is hinged, and another coupling end and the rod assembly on the actuator of connecting rod are hinged, and actuator is fixedly connected on the below of adapter plate along the fuselage axis.
Working process: before the unmanned plane emission, port wing and starboard wing are close to the upper surface of adapter plate and are fixed and spacing by actuator and connecting rod and rocking arm; The height that flies to and set after the unmanned plane emission; Actuator starts and the pulling connecting rod moves along fuselage axis alignment tail direction fast; Connecting rod pulling rocking arm; the rotating shaft of rocking arm pulling wing is rotated back rapid deployment thereby drive port wing with starboard wing around its rotational is automatically locked after the actuator work completion after port wing and starboard wing horizontally rotate an angle of 90 degrees; The span of wing rotating shaft rotating band motivation is opened required power and is provided by actuator and control.
Beneficial effect: wing expanding unit of the present invention is simple in structure, realization is convenient, reliable effect; The power that launches is provided by the priming system actuator, has therefore overcome the limited deficiency of operational forces of torsion spring; And the ability rapid deployment, synchronism is good; And then make the range of use of unmanned plane more extensive.
Description of drawings
Fig. 1 is an integral structure scheme drawing of the present invention;
Fig. 2 is a longitudinal profile structural representation of the present invention;
Fig. 3 is the A-A view of Fig. 2.
Wherein, 1-adapter plate, 2-port wing, 3-starboard wing, the rotating shaft of 4-wing, 5-rocking arm, 6-bearing cap shim, 7-bearing, 8-bearing seat, 9-connecting rod, 10-actuator.
The specific embodiment
Describe the present invention below in conjunction with accompanying drawing.
Shown in accompanying drawing 1,2 and 3, the invention provides a kind of folding wings unmanned plane wing rapid deployment device, comprise adapter plate 1, port wing 2, starboard wing 3, wing rotating shaft 4, bearing 7, bearing seat 8, bearing cap shim 6, Rocker arm 5, connecting rod 9 and actuator 10; Its annexation is following: two wing rotating shafts 4 vertically are fixed on the below of the horizontal fixed plate of fuselage interior respectively through bearing seat 8, bearing 7 and bearing cap shim 6; Two wing rotating shafts 4 lay respectively at the left and right sides of fuselage central axis; Port wing 2 and starboard wing 3 are fixed on the top of adapter plate 1 through the upper end of two wing rotating shafts 4; The lower end of wing rotating shaft 4 is an end of the horizontally disposed Rocker arm 5 of captive joint separately; a coupling end of the Rocker arm 5 other end and connecting rod 9 is hinged, and another coupling end and the rod assembly on the actuator 10 of connecting rod 9 are hinged, and actuator 10 is fixedly connected on the below of adapter plate 1 along the fuselage axis.
Wherein, rod assembly is made up of the pull bar of pipe link and actuator 10, and pipe link is connected with the mutual vertical fixing of the pull bar of actuator 10.
Working process: before the unmanned plane emission, port wing 2 is close to the upper surface of adapter plate with starboard wing 3 and is fixed with spacing by actuator 10 and connecting rod 9 and Rocker arm 5; The height that flies to and set after the unmanned plane emission; Actuator 10 starts and pulling connecting rod 9 moves along fuselage axis alignment tail direction fast; Connecting rod 9 pulling Rocker arm 5s; the rotating shaft 4 of Rocker arm 5 pulling wing is rotated back rapid deployment thereby drive port wing 2 with starboard wing 3 around its rotational, automatically locks after actuator 10 work are accomplished after port wing 2 and starboard wing 3 horizontally rotate an angle of 90 degrees; The wing rotating shaft 4 rotating band motivation spanes are opened required power and are provided by actuator 10 and control, and actuator can adopt priming system actuator, motor-driven cylinder, hydraulic actuator.
In sum, more than being merely preferred embodiment of the present invention, is not to be used to limit protection scope of the present invention.All within spirit of the present invention and principle, any modification of being done, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (5)
1. a folding wings unmanned plane wing rapid deployment device is characterized in that comprising adapter plate (1), port wing (2), starboard wing (3), wing rotating shaft (4), bearing (7), bearing seat (8), bearing cap shim (6), rocking arm (5), connecting rod (9) and actuator (10);
Its annexation is following: two wing rotating shafts (4) vertically are fixed on the below of the horizontal fixed plate (1) of fuselage interior respectively through bearing seat (8), bearing (7) and bearing cap shim (6); Two wing rotating shafts (4) lay respectively at the left and right sides of fuselage central axis; Port wing (2) and starboard wing (3) are fixed on the top of adapter plate (1) through the upper end of two wing rotating shafts (4); The lower end of wing rotating shaft (4) is an end of the horizontally disposed rocking arm of captive joint (5) separately; a coupling end of rocking arm (5) other end and connecting rod (9) is hinged; the rod assembly on another coupling end of connecting rod (9) and the actuator (10) is hinged, and actuator (10) is fixedly connected on the below of adapter plate (1) along the fuselage axis.
2. unmanned plane wing rapid deployment device as claimed in claim 1 is characterized in that said rod assembly is made up of the pull bar of pipe link and actuator (10), and pipe link is connected with the mutual vertical fixing of pull bar of actuator (10).
3. unmanned plane wing rapid deployment device as claimed in claim 1, it is characterized in that the emission of cartridge type emission unmanned plane before, port wing (2) and starboard wing (3) are close to the upper surface of adapter plate 1 and are fixed and spacing by actuator (10) and connecting rod (9) and rocking arm (5); Actuator (10) automatically locked after port wing (2) and starboard wing (3) horizontally rotated an angle of 90 degrees.
4. unmanned plane wing rapid deployment device as claimed in claim 1 is characterized in that the span of wing rotating shaft (4) rotating band motivation opens required power and provided by actuator (10) and control.
5. like claim 1,2,3 or 4 described unmanned plane wing rapid deployment devices, it is characterized in that said actuator (10) adopts priming system actuator, motor-driven cylinder or hydraulic actuator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110456520XA CN102556336A (en) | 2011-12-30 | 2011-12-30 | Wing fast unfolding device for folding-wing unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110456520XA CN102556336A (en) | 2011-12-30 | 2011-12-30 | Wing fast unfolding device for folding-wing unmanned plane |
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| CN102556336A true CN102556336A (en) | 2012-07-11 |
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| CN201110456520XA Pending CN102556336A (en) | 2011-12-30 | 2011-12-30 | Wing fast unfolding device for folding-wing unmanned plane |
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Cited By (30)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102849206A (en) * | 2012-10-30 | 2013-01-02 | 河北科技大学 | Wing folding-unfolding mechanism for small unmanned aerial vehicle with folding wings |
| CN103010453A (en) * | 2012-12-27 | 2013-04-03 | 北京理工大学 | Unmanned plane folded wing unfolding and locking device |
| CN103010452A (en) * | 2012-12-10 | 2013-04-03 | 中国飞机强度研究所 | Wing folding control instrument |
| CN103043214A (en) * | 2012-12-19 | 2013-04-17 | 天津全华时代航天科技发展有限公司 | Folding type unmanned plane |
| CN103123293A (en) * | 2012-12-24 | 2013-05-29 | 中国航空工业空气动力研究院 | Drive-embedded dynamic folding morphing wing |
| CN103123292A (en) * | 2013-01-07 | 2013-05-29 | 西北工业大学 | Folding wings pneumatic loading unfolding experiment device |
| CN103991535A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Hydraulic control method of mechanism folding |
| CN103991536A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Hydraulic control system of mechanism folding |
| CN104718133A (en) * | 2012-08-24 | 2015-06-17 | 吉.埃罗公司 | Variable geometry lift fan mechanism |
| CN105857573A (en) * | 2016-04-23 | 2016-08-17 | 董昕武 | Intelligent unmanned aerial vehicle for municipal landscaping |
| CN106143911A (en) * | 2016-07-13 | 2016-11-23 | 西藏长源动力科技有限公司 | A kind of individual soldier carries, can cartridge type storage and the collapsible unmanned plane launched |
| CN106240800A (en) * | 2016-08-17 | 2016-12-21 | 四川精诚至强科技有限公司 | A kind of unmanned plane folding wing |
| US9540103B2 (en) | 2014-06-24 | 2017-01-10 | Kitty Hawk Corporation | Passive deployment mechanism for lift fan |
| CN106542088A (en) * | 2016-04-29 | 2017-03-29 | 上海福昆航空科技有限公司 | Unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system |
| CN107128478A (en) * | 2017-05-23 | 2017-09-05 | 安徽中科中涣防务装备技术有限公司 | A kind of fast unfolding device of folded wing |
| CN108202861A (en) * | 2016-12-16 | 2018-06-26 | 中国航天科工飞航技术研究院 | A kind of fold mechanism and its control method for aircraft |
| CN109070993A (en) * | 2017-09-30 | 2018-12-21 | 深圳市大疆创新科技有限公司 | The rack components and unmanned plane of unmanned plane |
| WO2019015366A1 (en) * | 2017-07-21 | 2019-01-24 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN110127032A (en) * | 2019-06-06 | 2019-08-16 | 湖南文理学院 | A kind of collapsible unmanned plane, remote control method for folding and UAV system |
| 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 |
| CN111348176A (en) * | 2018-12-20 | 2020-06-30 | 中国航空工业集团公司西安飞机设计研究所 | Variable sweepback unmanned aerial vehicle adjusting mechanism |
| CN112520014A (en) * | 2020-11-16 | 2021-03-19 | 北京理工大学 | Folding control integration unmanned aerial vehicle |
| CN112896487A (en) * | 2021-01-28 | 2021-06-04 | 西安电子科技大学 | Unmanned aerial vehicle synchronous unfolding and folding system, method and application |
| CN113044241A (en) * | 2019-12-27 | 2021-06-29 | 北京理工大学 | Gear rack unfolding wing experiment platform and experiment method adopting same |
| CN113120222A (en) * | 2021-05-24 | 2021-07-16 | 中国人民解放军国防科技大学 | Foldable wing structure |
| CN113148107A (en) * | 2021-04-21 | 2021-07-23 | 重庆交通大学 | Rotary folding wing |
| CN113320685A (en) * | 2021-07-13 | 2021-08-31 | 广东汇天航空航天科技有限公司 | Folding structure of aerocar wing |
| CN113865824A (en) * | 2021-12-06 | 2021-12-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | Deformation device for missile wing of hypersonic wind tunnel test model |
| CN114485288A (en) * | 2021-12-27 | 2022-05-13 | 西安现代控制技术研究所 | Unfolding and locking method of small-caliber projectile body-large wingspan space folding tail wing |
| CN114802705A (en) * | 2022-04-18 | 2022-07-29 | 上海电气集团股份有限公司 | Wing folding structure for unmanned aerial vehicle |
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| US9284962B2 (en) | 2012-08-24 | 2016-03-15 | Zee.Aero Inc. | Variable geometry lift fan mechanism |
| CN104718133A (en) * | 2012-08-24 | 2015-06-17 | 吉.埃罗公司 | Variable geometry lift fan mechanism |
| CN102849206A (en) * | 2012-10-30 | 2013-01-02 | 河北科技大学 | Wing folding-unfolding mechanism for small unmanned aerial vehicle with folding wings |
| CN102849206B (en) * | 2012-10-30 | 2014-09-03 | 河北科技大学 | Wing folding-unfolding mechanism for small unmanned aerial vehicle with folding wings |
| CN103010452B (en) * | 2012-12-10 | 2015-05-27 | 中国飞机强度研究所 | Wing folding control instrument |
| CN103010452A (en) * | 2012-12-10 | 2013-04-03 | 中国飞机强度研究所 | Wing folding control instrument |
| CN103043214A (en) * | 2012-12-19 | 2013-04-17 | 天津全华时代航天科技发展有限公司 | Folding type unmanned plane |
| CN103123293A (en) * | 2012-12-24 | 2013-05-29 | 中国航空工业空气动力研究院 | Drive-embedded dynamic folding morphing wing |
| CN103010453A (en) * | 2012-12-27 | 2013-04-03 | 北京理工大学 | Unmanned plane folded wing unfolding and locking device |
| CN103123292A (en) * | 2013-01-07 | 2013-05-29 | 西北工业大学 | Folding wings pneumatic loading unfolding experiment device |
| CN103123292B (en) * | 2013-01-07 | 2015-07-08 | 西北工业大学 | Folding wings pneumatic loading unfolding experiment device |
| CN103991536A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Hydraulic control system of mechanism folding |
| CN103991535A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Hydraulic control method of mechanism folding |
| US9540103B2 (en) | 2014-06-24 | 2017-01-10 | Kitty Hawk Corporation | Passive deployment mechanism for lift fan |
| CN105857573A (en) * | 2016-04-23 | 2016-08-17 | 董昕武 | Intelligent unmanned aerial vehicle for municipal landscaping |
| CN105857573B (en) * | 2016-04-23 | 2017-12-26 | 广州市绿化公司 | A kind of municipal afforestation Intelligent unattended machine |
| CN106542088A (en) * | 2016-04-29 | 2017-03-29 | 上海福昆航空科技有限公司 | Unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system |
| CN106542088B (en) * | 2016-04-29 | 2024-05-28 | 中山福昆航空科技有限公司 | Unmanned aerial vehicle rotor wing retraction control mechanism and unmanned aerial vehicle rotor wing retraction system |
| CN106143911A (en) * | 2016-07-13 | 2016-11-23 | 西藏长源动力科技有限公司 | A kind of individual soldier carries, can cartridge type storage and the collapsible unmanned plane launched |
| CN106240800A (en) * | 2016-08-17 | 2016-12-21 | 四川精诚至强科技有限公司 | A kind of unmanned plane folding wing |
| CN108202861A (en) * | 2016-12-16 | 2018-06-26 | 中国航天科工飞航技术研究院 | A kind of fold mechanism and its control method for aircraft |
| CN107128478A (en) * | 2017-05-23 | 2017-09-05 | 安徽中科中涣防务装备技术有限公司 | A kind of fast unfolding device of folded wing |
| CN107128478B (en) * | 2017-05-23 | 2023-08-04 | 安徽中科中涣智能装备股份有限公司 | Quick unfolding device for folding wing |
| WO2019015366A1 (en) * | 2017-07-21 | 2019-01-24 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| US11492112B2 (en) | 2017-07-21 | 2022-11-08 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| CN109070993B (en) * | 2017-09-30 | 2022-04-26 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle's frame subassembly and unmanned aerial vehicle |
| CN109070993A (en) * | 2017-09-30 | 2018-12-21 | 深圳市大疆创新科技有限公司 | The rack components and unmanned plane of unmanned plane |
| CN111348176A (en) * | 2018-12-20 | 2020-06-30 | 中国航空工业集团公司西安飞机设计研究所 | Variable sweepback unmanned aerial vehicle adjusting mechanism |
| 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 |
| CN110127032A (en) * | 2019-06-06 | 2019-08-16 | 湖南文理学院 | A kind of collapsible unmanned plane, remote control method for folding and UAV system |
| CN113044241A (en) * | 2019-12-27 | 2021-06-29 | 北京理工大学 | Gear rack unfolding wing experiment platform and experiment method adopting same |
| CN112520014A (en) * | 2020-11-16 | 2021-03-19 | 北京理工大学 | Folding control integration unmanned aerial vehicle |
| CN112896487A (en) * | 2021-01-28 | 2021-06-04 | 西安电子科技大学 | Unmanned aerial vehicle synchronous unfolding and folding system, method and application |
| CN113148107A (en) * | 2021-04-21 | 2021-07-23 | 重庆交通大学 | Rotary folding wing |
| CN113120222A (en) * | 2021-05-24 | 2021-07-16 | 中国人民解放军国防科技大学 | Foldable wing structure |
| CN113320685A (en) * | 2021-07-13 | 2021-08-31 | 广东汇天航空航天科技有限公司 | Folding structure of aerocar wing |
| CN113865824A (en) * | 2021-12-06 | 2021-12-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | Deformation device for missile wing of hypersonic wind tunnel test model |
| CN114485288A (en) * | 2021-12-27 | 2022-05-13 | 西安现代控制技术研究所 | Unfolding and locking method of small-caliber projectile body-large wingspan space folding tail wing |
| CN114485288B (en) * | 2021-12-27 | 2024-05-28 | 西安现代控制技术研究所 | Unfolding and locking method for small-caliber projectile body-large-span space folding tail wing |
| CN114802705A (en) * | 2022-04-18 | 2022-07-29 | 上海电气集团股份有限公司 | Wing folding structure for unmanned aerial vehicle |
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Application publication date: 20120711 |