CN103010453A - Unmanned plane folded wing unfolding and locking device - Google Patents
Unmanned plane folded wing unfolding and locking device Download PDFInfo
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- CN103010453A CN103010453A CN2012105814971A CN201210581497A CN103010453A CN 103010453 A CN103010453 A CN 103010453A CN 2012105814971 A CN2012105814971 A CN 2012105814971A CN 201210581497 A CN201210581497 A CN 201210581497A CN 103010453 A CN103010453 A CN 103010453A
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Abstract
The invention belongs to the technical field of aircrafts, and in particular relates to an unmanned plane folded wing unfolding and locking device which is installed inside a shell below a folded wing. The technical scheme is as follows: two wing rotating shafts (9) are respectively and vertically fixed inside the plane body; the right wing (1) and the left wing (5) are respectively fixed with the upper ends of the two wing rotating shafts (9); the lower ends of the wing rotating shafts (9) are respectively and fixedly connected with one end of a horizontally arranged rocker arm (8); the other end of the rocker arm (8) is hinged with one connecting end of a connecting rod (3); the other connecting end of the connecting rod (3) is fixedly connected with the moving end of an actuator (6); the actuator (6) is fixed along the axis of the plane body; and two groups of locking devices are respectively installed inside the plane body below the right wing (1) and the left wing (5). By utilizing the device, the wings can be rapidly unfolded in an unmanned plane trajectory section and are locked when reaching the complete unfolding position, so that the device is simple in structure, convenient to realize, rapid and good in synchronization.
Description
Technical field
The invention belongs to the vehicle technology field, be specifically related to a kind of unmanned plane folded wing and launch locking device.
Background technology
Unmanned vehicle is the not manned craft of controlling by radio robot or airborne computer stored program controlled.Unmanned vehicle is simple in structure, use cost is low, not only can finish the task that manned aircraft is carried out, and more is applicable to the task that people's aircraft should not be carried out, such as 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 unmanned airship, with these ripe unmanned plane compare, the largest benefit of folding wings unmanned vehicle is saved the space exactly, easy to carry and transport, improved greatly the convenience of unmanned vehicle, but because evening is wanted in its research starting, and technology is comparatively complicated, hereat basically also is in space state in use present commercial market.Application number discloses a kind of unmanned plane wing fast unfolding device for the Chinese patent application of " 201110456520.X ", can make wing realize quick, synchronous expansion, its piston that utilizes actuator is to the rotating shaft of the wing below connection of conflicting, but use discovery through reality, the method can not actv. realizes the locking to wing, so need the large blocking device of another coupling mechanism force.
Summary of the invention
The objective of the invention is: provide a kind of unmanned plane folded wing to launch locking device, can quick locked expansion wing, actv. has solved the unmanned plane wing and has launched the poor problem of rear stability;
Technical scheme of the present invention is: the unmanned plane folded wing launches locking device,
The unmanned plane folded wing launches locking device, and it comprises: starboard wing, lock pin, connecting rod, port wing, actuator, locking pin seat, rocking arm, wing rotating shaft, lock pin spring, bayonet lock;
Locking pin seat has lockpin hole, be provided with the position-limited trough that runs through lockpin hole in locking pin seat along the axis direction of lockpin hole, lock pin is positioned at the lockpin hole of locking pin seat, and the bottom of lock pin is equipped with lock pin spring, and vertical notch that bayonet lock is horizontally through on the locking pin seat is captiveed joint with lock pin; Locking pin seat, lock pin, lock pin spring and bayonet lock form locking device;
Starboard wing and port wing respectively have a groove on its lower surface, when starboard wing and port wing launched fully, groove was over against the lock pin head of locking device;
Its annexation is as follows: two wing rotating shafts vertically are fixed on respectively fuselage interior, lay respectively at the left and right sides of fuselage central axis, starboard wing and port wing are fixed with the upper end of two wing rotating shafts respectively, 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; another coupling end of connecting rod is captiveed joint with the movable end of actuator; actuator is fixed along the fuselage axis, and two groups of locking devices are installed on respectively the fuselage interior of the below of starboard wing and port wing.
Before the unmanned plane emission, port wing and starboard wing are close to fuselage upper surface and fixing and spacing by actuator and connecting rod and rocking arm; Flight is to the height of setting 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 around its axis; thus rapid deployment after driving port wing and starboard wing and rotating, when port wing and starboard wing horizontally rotate until actuator work is automatically locked after finishing; Simultaneously, because the wing position changes, the lock pin that originally is compressed on the wing below outwards ejects under the elastic force effect of lock pin spring, after port wing and starboard wing launch fully, the lock pin head puts in the prefabricated groove of wing, and the top that the while bayonet lock moves to the locking pin seat upper limit position groove stops to continue upward movement.
The invention has the beneficial effects as follows: (1) utilizes the present invention can be at unmanned plane folded wing rapid deployment, and wing is locked, simple in structure when arriving complete expanded position, realize conveniently, the time is fast, synchronism is good.
(2) lock pin of the present invention and actuator have dual locking function, so that wing keeps deployed condition more reliable.
Description of drawings
Fig. 1 is structural representation of the present invention;
Fig. 2 is locking device schematic diagram among the present invention;
Fig. 3 is that the A-A of Fig. 2 is to view;
Wherein, 1-starboard wing, 2-lock pin, 3-connecting rod, 5-port wing, 6-actuator, 7-locking pin seat, 8-rocking arm, the rotating shaft of 9-wing, 10-lock pin spring, 11-bayonet lock.
The specific embodiment
Referring to accompanying drawing 1, the unmanned plane folded wing launches locking device, and it comprises: starboard wing 1, lock pin 2, connecting rod 3, port wing 5, actuator 6, locking pin seat 7, rocking arm 8, wing rotating shaft 9, lock pin spring 10, bayonet lock 11;
Referring to accompanying drawing 2,3, locking pin seat 7 has lockpin hole, be provided with the position-limited trough that runs through lockpin hole in locking pin seat 7 along the axis direction of lockpin hole, lock pin 2 is positioned at the lockpin hole of locking pin seat 7, the bottom of lock pin 2 is equipped with lock pin spring 10, and vertical notch that bayonet lock 11 is horizontally through on the locking pin seat 7 is captiveed joint with lock pin 2; Locking pin seat 7, lock pin 2, lock pin spring 10 form locking device with bayonet lock 11;
Starboard wing 1 respectively has a groove with port wing 5 on its lower surface, when starboard wing 1 and port wing 5 launched fully, groove was over against lock pin 2 heads of locking device;
High strength alloy steel is adopted in described wing rotating shaft 9, and described actuator 6 adopts priming system actuator, motor-driven cylinder or hydraulic actuator;
Its annexation is as follows: two wing rotating shafts 9 vertically are fixed on respectively fuselage interior, lay respectively at the left and right sides of fuselage central axis, starboard wing 1 is fixed with the upper end of two wing rotating shafts 9 respectively with port wing 5, the lower end of wing rotating shaft 9 is an end of the horizontally disposed rocking arm 8 of captive joint separately; a coupling end of rocking arm 8 other ends and connecting rod 3 is hinged; another coupling end of connecting rod 3 is captiveed joint with the movable end of actuator 6; actuator 6 is fixed along the fuselage axis, and two groups of locking devices are installed on respectively the fuselage interior of the below of starboard wing 1 and port wing 5.
Claims (3)
1. the unmanned plane folded wing launches locking device, it is characterized in that, it comprises: starboard wing (1), lock pin (2), connecting rod (3), port wing (5), actuator (6), locking pin seat (7), rocking arm (8), wing rotating shaft (9), lock pin spring (10), bayonet lock (11);
Locking pin seat (7) has lockpin hole, be provided with the position-limited trough that runs through lockpin hole in locking pin seat (7) along the axis direction of lockpin hole, lock pin (2) is positioned at the lockpin hole of locking pin seat (7), the bottom of lock pin (2) is equipped with lock pin spring (10), and vertical notch that bayonet lock (11) is horizontally through on the locking pin seat (7) is captiveed joint with lock pin (2); Locking pin seat (7), lock pin (2), lock pin spring (10) form locking device with bayonet lock (11);
Starboard wing (1) and port wing (5) respectively have a groove on its lower surface, when starboard wing (1) and port wing (5) when launching fully, groove is over against lock pin (2) head of locking device;
Its annexation is as follows: two wing rotating shafts (9) vertically are fixed on respectively fuselage interior, lay respectively at the left and right sides of fuselage central axis, starboard wing (1) is fixed with the upper end of two wing rotating shafts (9) respectively with port wing (5), the lower end of wing rotating shaft (9) is an end of the horizontally disposed rocking arm of captive joint (8) separately; a coupling end of rocking arm (8) other end and connecting rod (3) is hinged; another coupling end of connecting rod (3) is captiveed joint with the movable end of actuator (6); actuator (6) is fixed along the fuselage axis, and two groups of locking devices are installed on respectively the fuselage interior of the below of starboard wing (1) and port wing (5).
2. unmanned plane folded wing as claimed in claim 1 launches locking device, it is characterized in that, high strength alloy steel is adopted in described wing rotating shaft (9).
3. unmanned plane folded wing as claimed in claim 1 or 2 launches locking device, it is characterized in that, described actuator (6) adopts priming system actuator, motor-driven cylinder or hydraulic actuator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105814971A CN103010453A (en) | 2012-12-27 | 2012-12-27 | Unmanned plane folded wing unfolding and locking device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105814971A CN103010453A (en) | 2012-12-27 | 2012-12-27 | Unmanned plane folded wing unfolding and locking device |
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| CN103010453A true CN103010453A (en) | 2013-04-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2012105814971A Pending CN103010453A (en) | 2012-12-27 | 2012-12-27 | Unmanned plane folded wing unfolding and locking device |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103287570A (en) * | 2013-05-31 | 2013-09-11 | 西北工业大学 | Z-shaped folding wing mechanism |
| CN103322868A (en) * | 2013-06-28 | 2013-09-25 | 上海新跃仪表厂 | Small combined spring type quick unfolding mechanism |
| CN103968002A (en) * | 2014-04-18 | 2014-08-06 | 江西洪都航空工业集团有限责任公司 | Missile wing gear transmission folding mechanism |
| 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 |
| CN105799915A (en) * | 2016-03-18 | 2016-07-27 | 北京理工大学 | Synchronous folding and unfolding mechanism of wings of unmanned aerial vehicle |
| 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 |
| 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 |
| CN109436297A (en) * | 2018-12-28 | 2019-03-08 | 太原科技大学 | A kind of folding unmanned plane wing |
| WO2019061473A1 (en) * | 2017-09-30 | 2019-04-04 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle frame assembly, and unmanned aerial vehicle |
| 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 |
| CN114961440A (en) * | 2022-03-25 | 2022-08-30 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Actuator capable of automatically locking and unlocking |
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| US5615846A (en) * | 1994-11-04 | 1997-04-01 | Gec Marconi Dynamics Inc. | Extendable wing for guided missles and munitions |
| CN201895770U (en) * | 2010-09-29 | 2011-07-13 | 贵州航天控制技术有限公司 | Locking and unlocking mechanism for aircraft airfoil |
| CN102530239A (en) * | 2011-12-30 | 2012-07-04 | 北京理工大学 | Double torsional spring folding-type maneuverable empennage mechanism |
| CN102556336A (en) * | 2011-12-30 | 2012-07-11 | 北京理工大学 | Wing fast unfolding device for folding-wing unmanned plane |
| CN102602529A (en) * | 2011-12-30 | 2012-07-25 | 北京理工大学 | Folding full-motion horizontal tail mechanism |
-
2012
- 2012-12-27 CN CN2012105814971A patent/CN103010453A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5615846A (en) * | 1994-11-04 | 1997-04-01 | Gec Marconi Dynamics Inc. | Extendable wing for guided missles and munitions |
| CN201895770U (en) * | 2010-09-29 | 2011-07-13 | 贵州航天控制技术有限公司 | Locking and unlocking mechanism for aircraft airfoil |
| CN102530239A (en) * | 2011-12-30 | 2012-07-04 | 北京理工大学 | Double torsional spring folding-type maneuverable empennage mechanism |
| CN102556336A (en) * | 2011-12-30 | 2012-07-11 | 北京理工大学 | Wing fast unfolding device for folding-wing unmanned plane |
| CN102602529A (en) * | 2011-12-30 | 2012-07-25 | 北京理工大学 | Folding full-motion horizontal tail mechanism |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103287570A (en) * | 2013-05-31 | 2013-09-11 | 西北工业大学 | Z-shaped folding wing mechanism |
| CN103322868A (en) * | 2013-06-28 | 2013-09-25 | 上海新跃仪表厂 | Small combined spring type quick unfolding mechanism |
| CN103322868B (en) * | 2013-06-28 | 2015-09-30 | 上海新跃仪表厂 | A kind of packaged combination spring rapid unfolding mechanism |
| 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 |
| CN103968002A (en) * | 2014-04-18 | 2014-08-06 | 江西洪都航空工业集团有限责任公司 | Missile wing gear transmission folding mechanism |
| CN105799915A (en) * | 2016-03-18 | 2016-07-27 | 北京理工大学 | Synchronous folding and unfolding mechanism of wings of unmanned aerial vehicle |
| WO2019061473A1 (en) * | 2017-09-30 | 2019-04-04 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle frame assembly, and unmanned aerial vehicle |
| 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 |
| 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 |
| 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 |
| CN109436297A (en) * | 2018-12-28 | 2019-03-08 | 太原科技大学 | A kind of folding unmanned plane wing |
| CN109436297B (en) * | 2018-12-28 | 2024-01-16 | 太原科技大学 | Folding unmanned aerial vehicle wing |
| CN114961440A (en) * | 2022-03-25 | 2022-08-30 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Actuator capable of automatically locking and unlocking |
| CN114961440B (en) * | 2022-03-25 | 2023-11-07 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Automatic locking-unlocking actuator |
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Application publication date: 20130403 |