CN103963958B - Unmanned plane wingfold mechanism - Google Patents
Unmanned plane wingfold mechanism Download PDFInfo
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- CN103963958B CN103963958B CN201410161334.7A CN201410161334A CN103963958B CN 103963958 B CN103963958 B CN 103963958B CN 201410161334 A CN201410161334 A CN 201410161334A CN 103963958 B CN103963958 B CN 103963958B
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Abstract
The present invention relates to a kind of unmanned plane wingfold mechanism, it comprises the first sleeve and the second sleeve, and the first described sleeve has the first cavity, and the second described sleeve has the second cavity; Pivot shaft, is slidably arranged in the first cavity; Locking part, is installed on the side of the first sleeve, and it has the locking and unlocking two states; Tractive unit, described tractive unit to be fixed in the second cavity and can to move around along the first sleeve direction of axis line; Pipe link, for connecting pivot shaft and tractive unit; Described unmanned plane wingfold mechanism has expansion and folding two states.Enter partially into the pivot shaft of the second cavity on the one hand, it is made to be in deployed condition, under the effect of tractive unit, the first sleeve is made to rotate relative to the end face of the second sleeve by pipe link on the other hand, it is made to be in folded state, thus achieve expansion and fold, do not need gear as drive disk assembly; And compact conformation, to motor torque require little, stable movement.
Description
Technical field
The present invention relates to a kind of parts of unmanned plane wing, be specifically related to a kind of unmanned plane wingfold mechanism.
Background technology
Unmanned plane is the general designation of unmanned vehicle, and it is provided with the equipment such as autopilot, process controller.On ground, naval vessels or machine tool command and control station personnel by equipment such as radars, it is followed the tracks of, locates, remote control, remote measurement and digital communication.Compared with manned aircraft, it has the advantages such as volume is little, cost is low, easy to use.Wing-folding formula unmanned plane can change wing shapes by folding mode under different flight demands: wing all launches to be beneficial to take off or cruise, and wing shrinks and is beneficial to high speed or maneuvering flight and deposits save space.
At present, the domestic unmanned plane wingfold mechanism researched and developed uses a kind of gear engagement mechanism mostly: the Dual-motors Driving miniature gears be connected with movable wing section, miniature gears and the canine tooth crop rotation gears meshing be connected in fixed wing part move, and realize the folding of the relative fixed wing of movable wing and launch to move.This gear engagement mechanism exists that kinematic mechanism is not compact, between cog contact force is comparatively large, higher to motor torque requirement, wing-folding time the problem such as mechanism bumpy motion.
Summary of the invention
The present invention seeks to provide a kind of wingfold mechanism for unmanned plane to overcome the deficiencies in the prior art.
For achieving the above object, the technical solution adopted in the present invention is: a kind of unmanned plane wingfold mechanism, it comprises
First sleeve and the second sleeve, the first described sleeve has the first cavity, and the second described sleeve has the second cavity;
Pivot shaft, is arranged in the first cavity;
Locking part, is installed on the side of the first sleeve, and for being fixed in the first cavity by pivot shaft, it has the locking and unlocking two states, when locking part is in the lock state, pivot shaft be locked in the first cavity with second adjacent one end of cavity; When locking part is in released state, pivot shaft and the second sleeve can relative slidings;
Tractive unit, to be fixed in the second cavity and can to move around along the first sleeve direction of axis line;
Pipe link, for connecting pivot shaft and tractive unit;
Described unmanned plane wingfold mechanism has expansion and folding two states, and when in the expanded state, the end face of the first sleeve and the second sleeve is bonded to each other, and locking part is in released state, and the pivot shaft part in the first cavity enters the second cavity; When positioned in the folded position, locking part is in the lock state, and described first sleeve is rotated relative to the end face of the second sleeve under the effect of tractive unit by pipe link.
Optimally, described tractive unit comprise driven by motor leading screw, be set in the sleeve that described leading screw can move around along leading screw.
Further, offer the first groove in described second cavity, described leading screw is arranged in the first groove.
Further, described screw set is with the first auricle, and described pivot shaft end winding support has the second auricle, and the two ends of described pipe link are hinged with the first auricle, the second auricle respectively.
Optimally, described locking part comprises the pin-and-hole be arranged on the first sleeve, the spring withstanding on pin-and-hole outer end, the pin supporting with pin-and-hole and and the pin post that be fixed on second sleeve on corresponding with pin, when locking part is in the lock state, described pin-and-hole is partial insertion pivot shaft, partial insertion first sleeve under the action of the spring; When locking part is in released state, pin inserts pin-and-hole at pin post by pressure makes pin-and-hole depart from pivot shaft.
Optimally, described first sleeve side opening is provided with the second groove, and the bearing of trend of described second groove is consistent with the first sleeve direction of axis line and its length is less than the first sleeve side length, and described pivot shaft is fixed with the engagement section corresponding with the second groove.
Because technique scheme is used, the present invention compared with prior art has following advantages: unmanned plane wingfold mechanism of the present invention, enter partially into the pivot shaft of the second cavity on the one hand, it is made to be in deployed condition, under the effect of tractive unit, the first sleeve is made to rotate relative to the end face of the second sleeve by pipe link on the other hand, make it be in folded state, thus achieve expansion and fold, do not need gear as drive disk assembly; And compact conformation, to motor torque require little, stable movement.
Accompanying drawing explanation
Accompanying drawing 1 is common wing-folding formula unmanned plane structural representation;
Accompanying drawing 2 is in the structural representation of different conditions for unmanned plane alar part;
Accompanying drawing 3 is unmanned plane wingfold mechanism structural representation of the present invention;
Accompanying drawing 4 is the section components structural representation of unmanned plane wingfold mechanism of the present invention;
Accompanying drawing 5 is the three-view diagram of unmanned plane wingfold mechanism pipe link of the present invention;
Wherein, 1 ', fuselage; 2 ', alar part; 21 ', outer wing; 22 ', inner wing; 1, the first sleeve; 11, the first cavity; 12, the second groove; 2, the second sleeve; 21, the second cavity; 22, the first groove; 3, pivot shaft; 31, engagement section; 32, the second auricle; 4, tractive unit; 41, leading screw; 42, screw set; 421, the first auricle; 5, pipe link; 6, locking part; 61, pin-and-hole; 62, pin; 63, spring; 64, pin post.
Detailed description of the invention
Wing-folding formula unmanned plane as shown in Figure 1, comprises fuselage 1 ' and alar part 2 ' two large divisions.Wherein, alar part 2 ' symmetry is installed on the both sides of fuselage 1 ', and it is made up of interconnective two sections of wings, and the wing that definition and fuselage 1 ' fix is inner wing 22 ', and the wing away from fuselage 1 ' is outer wing 21 '.The outer wing 21 ' of this wing-folding formula unmanned plane can be that axial line rotates with the junction of outer wing 21 ' and inner wing 22 ', and as shown in Figure 2, this axis parallel is in the unmanned plane wing string of a musical instrument.Have that kinematic mechanism is not compact, between cog contact force is comparatively large, higher to motor torque requirement to solve unmanned plane gear engagement mechanism, wing-folding time the problem such as mechanism bumpy motion, the invention provides a kind of unmanned plane wingfold mechanism of novelty, at least arrange two along airfoil chord to the junction being distributed in outer wing 21 ' and inner wing 22 '.
Below in conjunction with accompanying drawing, the preferred embodiment of the invention is described in detail:
Unmanned plane wingfold mechanism as shown in Figure 3 and Figure 4, mainly comprises the first sleeve 1, second sleeve 2, pivot shaft 3, locking part 6 and tractive unit 4.
Wherein, the first sleeve 1 and the second sleeve 2 are disposed adjacent, and the first sleeve 1 has the first cavity 11, second sleeve 2 has the second cavity 21; Pivot shaft 3 is arranged in the first cavity 11; Locking part 6 is installed on the side of the first sleeve 1, and for being fixed in the first cavity 11 by pivot shaft 3, it has the locking and unlocking two states, and when in a locked condition, pivot shaft 3 is locked in one end of the first cavity 11, and this end is adjacent with the second cavity 21; When locking part is in released state, pivot shaft 3 and the second sleeve 2 can relative slidings; Tractive unit 4 to be fixed in the second cavity 21 and can to move around, for providing folding power to unmanned plane wingfold mechanism along the first sleeve 1 direction of axis line; Pipe link 5 is connected between pivot shaft 3 and tractive unit 4.In order to realize the folding of outer wing 21 ' and tiling, unmanned plane wingfold mechanism of the present invention has expansion and folding two states, when in the expanded state, the end face of the first sleeve 1 and the second sleeve 2 is bonded to each other, the axial line of the first cavity 11 is overlapping with the axial line of the second cavity 21, locking part 6 is in released state, pivot shaft 3 part in first cavity 11 enters the second cavity 21, pivot shaft 3 will have higher intensity and hardness, on the one hand for supporting the first sleeve 1, the weight of the second sleeve 2 and outer wing 21 ', larger wind tunnel can be born on the other hand, ensure that the intensity that folded wing should have as a whole, namely air maneuver demand is completed simultaneously, do not affect the due performance of original design, when positioned in the folded position, locking part 6 is in the lock state, and the first sleeve 1 is rotated relative to the end face of the second sleeve 2 under the effect of tractive unit 4 by pipe link 5, thus realizes the folding of unmanned plane wing.
In the present embodiment, locking part 6 comprises the pin-and-hole 61 be arranged on the first sleeve 1, the spring 63 withstanding on pin-and-hole 61 outer end, the pin 62 supporting with pin-and-hole 61 and and the pin post 64 that be fixed on second sleeve 2 on corresponding with pin 62.The axis of pin 62 and the axis being parallel of pin-and-hole 61, the axis of spring 63 and pin-and-hole 61 axis vertical take-off, pin 62 is an inclined-plane near one end of pin-and-hole 61, by pin 62 moving along its axis, can control pin-and-hole 61 and move along the direction perpendicular to its axis.When locking part 6 is in the lock state, pin-and-hole 61 inserts pivot shaft 3, partial insertion first sleeve 1 in the elastic force effect lower part of spring 63, and pivot shaft 3 and the first sleeve 1 are synchronized with the movement; When locking part 6 is in released state, pin 62 inserts pin-and-hole 61 at pin post 64 by pressure makes pin-and-hole 61 depart from pivot shaft 3, and pivot shaft 3 and the first sleeve 1 can relative motions.
Tractive unit 4 comprise driven by motor leading screw 41, be set in the screw set 42 that leading screw 41 can move around along leading screw 41, and be provided with one and isometric the first groove 22 of leading screw 41 in the second cavity 21, leading screw 41 is just arranged on the first groove 22 and uses; And screw set 42 is with the first auricle 421, pivot shaft 3 end winding support has the second auricle 32, is hinged respectively with the two ends of pipe link 5 with the first auricle 421, second auricle 32.Monomotor is adopted to drive leading screw 41, rotate by leading screw 41 screw set 42 that drive engages therewith to move, because now pivot shaft 3 and the first sleeve 1 are synchronized with the movement, by pipe link 5(as shown in Figure 5) control pivot shaft 3, thus drive the first sleeve 1 to rotate relative to the end face of the second sleeve 2.When the first sleeve 1 and the second sleeve 2 are separately fixed in outer wing 21 ', inner wing 22 ', outer wing 21 ' rotating relative to inner wing 22 ' can be realized.Such motor can be fixed on inner wing 22 ' part, and transmit easy, efficiency improves greatly.When adopting this kind of wingfold mechanism, aerofoil surface is seamless all the time, this ensures that theres the integraty of aerofoil surface, meets the original aerodynamic performance requirements of aircraft.
In the present embodiment, the side of the first sleeve 1 also offers the second groove 12, its bearing of trend is consistent with the first sleeve 1 direction of axis line and its length is less than the first sleeve side length, pivot shaft 3 is fixed with the engagement section 31 corresponding with the second groove 12, when pivot shaft 3 stretches in the second cavity 21 gradually, engagement section 31 is mobile in the second groove 12, can prevent pivot shaft 3 from rolling in the first cavity 11 like this, pivot shaft 3 can be avoided again all to enter the first cavity 11.
The above-mentioned structure to unmanned plane wingfold mechanism of the present invention is illustrated, and does brief description below to its principle of work:
In use, install at least two personal-machine wingfold mechanisms in the junction of outer wing 21 ' and inner wing 22 ' along wing chordwise direction, wherein the first sleeve 1 is arranged in outer wing 21 ', and the second sleeve 2 is arranged in inner wing 22 '.
For convenience of description, definition leading screw 41 is inner near one end of fuselage 1 ', and the other end is outer end.When the screw set 4 coordinated with leading screw 41 is positioned at leading screw 41 outer end, pivot shaft 3 is all positioned at the first sleeve 1, pin 62 does not insert pin-and-hole 61, pivot shaft 3 and the first sleeve 1 lock together, now outer wing 21 ' is turned up relative to inner wing 22 ', with inner wing 22 ' close to vertical (as shown in phantom in Figure 2); When driven by motor leading screw 41 rotates along a direction, and then drive the screw set 42 on leading screw 41 to be moved to the inner along leading screw 41 by leading screw outer end, and then drive pivot shaft 3 to be that axle rotates with the string of a musical instrument of outer wing 21 ' and inner wing 22 ' junction by pipe link 5, namely realize driving outer wing 21 ' to rotate around same axle.When screw set 42 moves to a certain position on leading screw 41, outer wing 21 ' turns to gradually and is in same plane with inner wing 22 ', namely the end face of the first sleeve 1 and the second sleeve 2 is bonded to each other, the axial line of the first cavity 11 is overlapping with the axial line of the second cavity 21, at this moment screw set 42 stops operating, pin 62 end is subject to the compressing of pin post 64 and is inserted in pin-and-hole 61, pin-and-hole 61 just departs from pivot shaft 3, pivot shaft 3 and the first sleeve 1 unlock, along with the continuation of screw set 42 is moved, pivot shaft 3 is driven to move in the second sleeve 2.When the nearly half of pivot shaft 3 is positioned at the second sleeve 2, it is inner that screw set 42 moves to leading screw 41 just, and motor stops, and corresponding range of motion all stops, and wing has launched.
When wing-folding gets up by needs, electric machine rotation, drive leading screw 41 to rotate in the opposite direction, screw set 42 is just moved outward by leading screw 41 the inner, and then drives pivot shaft 3 outwards movement.When pivot shaft 3 shifts out the second sleeve 2 completely, pin 62 is no longer subject to External Force Acting, and pin-and-hole 61 inserts pivot shaft 3 due to the elastic force of spring 63, and now pivot shaft 3 and the first sleeve 1 lock.Move outside the continuation of screw set 42, drive the first sleeve 1 with the string of a musical instrument of outer wing 21 ' and inner wing 22 ' junction for axially to rotate, and then drive outer wing 21 ' upwards rotates.When screw set 42 moves to leading screw outer end, motor stops, and corresponding range of motion stops, and outer wing 21 ' turns to maximum position, and wing-folding completes.
Above-described embodiment is only for illustrating technical conceive of the present invention and feature; its object is to person skilled in the art can be understood content of the present invention and implement according to this; can not limit the scope of the invention with this; all equivalences done according to Spirit Essence of the present invention change or modify, and all should be encompassed within protection scope of the present invention.
Claims (6)
1. a unmanned plane wingfold mechanism, is characterized in that: it comprises
First sleeve and the second sleeve, the first described sleeve has the first cavity, and the second described sleeve has the second cavity;
Pivot shaft, is arranged in the first cavity;
Locking part, is installed on the side of the first sleeve, and for being fixed in the first cavity by pivot shaft, it has the locking and unlocking two states, when locking part is in the lock state, pivot shaft be locked in the first cavity with second adjacent one end of cavity; When locking part is in released state, pivot shaft and the second sleeve can relative slidings;
Tractive unit, to be fixed in the second cavity and can to move around along the first sleeve direction of axis line;
Pipe link, for connecting pivot shaft and tractive unit;
Described unmanned plane wingfold mechanism has expansion and folding two states, and when in the expanded state, the end face of the first sleeve and the second sleeve is bonded to each other, and locking part is in released state, and the pivot shaft part in the first cavity enters the second cavity; When positioned in the folded position, locking part is in the lock state, and described first sleeve is rotated relative to the end face of the second sleeve under the effect of tractive unit by pipe link.
2. unmanned plane wingfold mechanism according to claim 1, is characterized in that: described tractive unit comprise driven by motor leading screw, be set in the screw set that described leading screw can move around along leading screw.
3. unmanned plane wingfold mechanism according to claim 2, is characterized in that: offer the first groove in described second cavity, described leading screw is arranged in the first groove.
4. unmanned plane wingfold mechanism according to claim 2, is characterized in that: described screw set is with the first auricle, and described pivot shaft end winding support has the second auricle, and the two ends of described pipe link are hinged with the first auricle, the second auricle respectively.
5. unmanned plane wingfold mechanism according to claim 1, it is characterized in that: described locking part comprises the pin-and-hole be arranged on the first sleeve, the spring withstanding on pin-and-hole outer end, the pin supporting with pin-and-hole and and the pin post that be fixed on second sleeve on corresponding with pin, when locking part is in the lock state, described pin-and-hole is partial insertion pivot shaft under the action of the spring, partial insertion first sleeve; When locking part is in released state, pin inserts pin-and-hole at pin post by pressure makes pin-and-hole depart from pivot shaft.
6. unmanned plane wingfold mechanism according to claim 1, it is characterized in that: described first sleeve side opening is provided with the second groove, the bearing of trend of described second groove is consistent with the first sleeve direction of axis line and its length is less than the first sleeve side length, and described pivot shaft is fixed with the engagement section corresponding with the second groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410161334.7A CN103963958B (en) | 2014-04-21 | 2014-04-21 | Unmanned plane wingfold mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410161334.7A CN103963958B (en) | 2014-04-21 | 2014-04-21 | Unmanned plane wingfold mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103963958A CN103963958A (en) | 2014-08-06 |
| CN103963958B true CN103963958B (en) | 2015-12-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410161334.7A Expired - Fee Related CN103963958B (en) | 2014-04-21 | 2014-04-21 | Unmanned plane wingfold mechanism |
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| CN (1) | CN103963958B (en) |
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| CN104596360B (en) * | 2015-01-12 | 2016-06-22 | 湖北航天技术研究院总体设计所 | A kind of folding wings unlocks Che Shou mechanism |
| GB2539497A (en) * | 2015-06-19 | 2016-12-21 | Airbus Operations Ltd | A Rotational Joint For An Aircraft Folding Wing |
| CN104986324B (en) * | 2015-07-15 | 2017-03-08 | 广州天翔航空科技有限公司 | A kind of rotary locking mechanism and the plant protection unmanned plane with which |
| CN105711812B (en) * | 2016-03-11 | 2017-09-29 | 深圳市国艺园林建设有限公司 | A kind of municipal gardens folding wings unmanned plane |
| CN105691593B (en) * | 2016-03-11 | 2018-01-02 | 国网浙江省电力公司信息通信分公司 | A kind of folding wings unmanned plane |
| CN105799914A (en) * | 2016-03-17 | 2016-07-27 | 北京昆仑凯利科技有限公司 | Rotation unfolding mechanism for aircraft wing |
| CN105905276B (en) * | 2016-05-10 | 2018-02-09 | 吉林省山河艮盛科技有限公司 | A kind of architectural engineering folding wings unmanned plane |
| CN105799911B (en) * | 2016-05-10 | 2017-11-21 | 哈尔滨讯建科技有限公司 | A kind of energy-conserving and environment-protective architectural engineering folding wings unmanned plane |
| CN105947209B (en) * | 2016-05-10 | 2018-04-17 | 菁果国际教育科技（广州）有限公司 | A kind of energy saving and environment friendly building municipal administration unmanned plane |
| CN105857574B (en) * | 2016-05-10 | 2017-12-08 | 江苏福莱尔航空科技有限公司 | One kind building municipal administration unmanned plane |
| CN107458574B (en) * | 2016-06-02 | 2019-11-08 | 比亚迪股份有限公司 | Unmanned plane |
| CN106218857B (en) * | 2016-07-28 | 2018-11-02 | 上海威碳新材料有限公司 | A kind of unmanned plane folding horn of injection molding |
| CN107972847B (en) * | 2017-11-01 | 2021-08-31 | 成都飞亚航空设备应用研究所有限公司 | Aircraft wing folding mechanism and flap mechanism based on same |
| 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 |
| US11613343B1 (en) | 2019-07-12 | 2023-03-28 | Piasecki Aircraft Corporation | Unmanned flying wing aircraft having foldable and stackable wings |
| CN110466753A (en) * | 2019-09-09 | 2019-11-19 | 西安交通大学 | A kind of VTOL fixed-wing unmanned plane that can rapid disassembling folding and case |
| CN112061376B (en) * | 2020-08-24 | 2022-09-09 | 西北工业大学 | Independently fix a position collapsible freight transportation glider |
| CN113415410A (en) * | 2021-07-31 | 2021-09-21 | 重庆交通大学 | Foldable unmanned aerial vehicle wing assembly |
| CN113665791B (en) * | 2021-08-11 | 2023-06-16 | 广东空天科技研究院 | Locking mechanism suitable for energy storage driving thin folding wing |
| CN113665788B (en) * | 2021-08-11 | 2023-04-11 | 广东空天科技研究院 | Synchronous locking mechanism of folding wing |
| CN113665790B (en) * | 2021-08-11 | 2023-03-17 | 广东空天科技研究院 | Locking mechanism for energy storage driving folding wing folding state and folding wing |
| CN114476015B (en) * | 2022-03-28 | 2022-08-16 | 沃飞长空科技(成都)有限公司 | Unmanned aerial vehicle part quick detach mechanism and unmanned aerial vehicle |
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| US4778129A (en) * | 1987-03-12 | 1988-10-18 | The Boeing Company | Control surface drive for folding wing aircraft |
| US5201479A (en) * | 1992-01-30 | 1993-04-13 | The Boeing Company | Self-monitoring latch pin lock for folding wing aircraft |
| US20070018033A1 (en) * | 2005-03-22 | 2007-01-25 | Fanucci Jerome P | Precision aerial delivery of payloads |
| CN101712379B (en) * | 2009-07-14 | 2012-02-01 | 北京航空航天大学 | A small, foldable drone |
| US8733692B2 (en) * | 2012-06-11 | 2014-05-27 | The Boeing Company | Latching apparatus and methods |
| CN203767065U (en) * | 2014-04-21 | 2014-08-13 | 西工大常熟研究院有限公司 | Wing folding mechanism of unmanned aerial vehicle |
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2014
- 2014-04-21 CN CN201410161334.7A patent/CN103963958B/en not_active Expired - Fee Related
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| CN103963958A (en) | 2014-08-06 |
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Granted publication date: 20151209 Termination date: 20200421 |