CN203767065U - Wing folding mechanism of unmanned aerial vehicle - Google Patents
Wing folding mechanism of unmanned aerial vehicle Download PDFInfo
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- CN203767065U CN203767065U CN201420195473.7U CN201420195473U CN203767065U CN 203767065 U CN203767065 U CN 203767065U CN 201420195473 U CN201420195473 U CN 201420195473U CN 203767065 U CN203767065 U CN 203767065U
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- sleeve
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- locking part
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Abstract
The utility model relates to a wing folding mechanism of an unmanned aerial vehicle. The wing folding mechanism comprises a first sleeve and a second sleeve, a support shaft, a locking part, a traction part and a connecting rod, wherein the first sleeve is provided with a first cavity, the second sleeve is provided with a second cavity; the support shaft is arranged in the first cavity in a slidable manner; the locking part is arranged on the side surface of the first sleeve, and has two states of locking and unlocking; the traction part is fixed in the second cavity and is capable of moving along the axial lead direction of the first sleeve backwards and forwards; the connecting rod is used for connecting the support shaft and the traction part; the wing folding mechanism of the unmanned aerial vehicle has the two states of unfolding and folding. On one hand, the wing folding mechanism is in the unfolding state when part of the support shaft enters the second cavity, on the other hand, the first sleeve rotates relative to the end face of the second sleeve through the connecting rod under the action of the traction part, and thus the wing folding mechanism is in the folding state, the unfolding and the folding are realized without using a gear as a transmission part; the wing folding mechanism is compact in structure, small in requirement on torque of a motor, and stable to move.
Description
Technical field
The utility model relates to a kind of parts of unmanned plane wing, is 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, to its follow the tracks of, location, remote control, remote measurement and digital communication.Compare 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 and save space.
At present, the domestic unmanned plane wingfold mechanism of researching and developing is mostly used a kind of gear engagement mechanism: the Dual-motors Driving miniature gears being connected with movable wing section, miniature gears be connected in the canine tooth crop rotation gear gear motion in fixed wing part, realize the folding of the relative fixed wing of movable wing and launch motion.This gear engagement mechanism exists that kinematic mechanism is not compact, between cog contact force is large, to motor torque have relatively high expectations, the problem such as mechanism's bumpy motion during wing-folding.
Summary of the invention
The utility model object is that a kind of wingfold mechanism for unmanned plane is provided in order to overcome the deficiencies in the prior art.
For achieving the above object, the technical solution adopted in the utility model is: a kind of unmanned plane wingfold mechanism, it comprises
The 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 pivot shaft is fixed in the first cavity, 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 during in released state, pivot shaft and the second sleeve can relative slidings;
Tractive unit, is fixed in the second cavity and can moves 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 deployed condition, 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 in the first cavity partly enters the second cavity; When in folded state, locking part is in the lock state, and described the first sleeve rotates 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 can move around along leading screw on described leading screw.
Further, in described the second cavity, offer the first groove, described leading screw is arranged in the first groove.
Further, described screw set is with the first auricle, and described pivot shaft end is fixed with 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 being arranged on the first sleeve, the spring that withstands on pin-and-hole outer end, the pin supporting with pin-and-hole and is corresponding and be fixed on the pin post on the second sleeve with pin, when locking part is in the lock state, described pin-and-hole is partial insertion pivot shaft, partial insertion the first sleeve under action of the spring; When locking part is during in released state, pin inserts pin-and-hole and makes pin-and-hole depart from pivot shaft by depressing at pin post.
Optimally, described the first sleeve side opening is provided with the second groove, and the bearing of trend of described the second groove and its length consistent with the first sleeve direction of axis line is less than the first sleeve side length, is fixed with the engagement section corresponding with the second groove on described pivot shaft.
Because technique scheme is used, the utility model compared with prior art has following advantages: the utility model unmanned plane wingfold mechanism, by part, enter on the one hand the pivot shaft of the second cavity, make it in deployed condition, by pipe link, under the effect of tractive unit, make on the other hand the first sleeve rotate relative to the end face of the second sleeve, make it in folded state, thereby realized, launch and fold, do not need gear as drive disk assembly; And compact conformation, to motor torque, require little, motion steadily.
Accompanying drawing explanation
Accompanying drawing 1 is common wing-folding formula unmanned plane structural representation;
Accompanying drawing 2 is the structural representation of unmanned plane alar part in different conditions;
Accompanying drawing 3 is the utility model unmanned plane wingfold mechanism structural representation;
Accompanying drawing 4 is the part block construction schematic diagram of the utility model unmanned plane wingfold mechanism;
Accompanying drawing 5 is the three-view diagram of the utility model unmanned plane wingfold mechanism pipe link;
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.
The specific embodiment
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 comprised of interconnective two sections of wings, and the wing that definition fixes with fuselage 1 ' is inner wing 22 ', away from the wing of fuselage 1 ', is outer wing 21 '.It is that axial line rotates that the outer wing 21 ' of this wing-folding formula unmanned plane can be take 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.In order to solve unmanned plane gear engagement mechanism, have that kinematic mechanism is not compact, between cog contact force is large, to motor torque have relatively high expectations, the problem such as mechanism's bumpy motion during wing-folding, the invention provides a kind of unmanned plane wingfold mechanism of novelty, at least arrange two along airfoil chord to the junction that is distributed in outer wing 21 ' and inner wing 22 '.
Below in conjunction with embodiment shown in the drawings, the utility model is further described.
Unmanned plane wingfold mechanism, mainly comprises the first sleeve 1, the second sleeve 2, pivot shaft 3, locking part 6 and tractive unit 4 as shown in Figure 3 and Figure 4.
Wherein, the first sleeve 1 and the adjacent setting of the second sleeve 2, and the first sleeve 1 has the first cavity 11, the second sleeves 2 and 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 pivot shaft 3 is fixed at the first cavity 11, it has the locking and unlocking two states, and when being in the lock state, 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 during in released state, pivot shaft 3 and the second sleeve 2 can relative slidings; Tractive unit 4 is fixed in the second cavity 21 and can moves around along the first sleeve 1 direction of axis line, for providing folding power to unmanned plane wingfold mechanism; Pipe link 5 is connected between pivot shaft 3 and tractive unit 4.In order to realize the folding and tiling of outer wing 21 ', unmanned plane wingfold mechanism of the present invention has expansion and folding two states, when in deployed condition, the end face of the first sleeve 1 and the second sleeve 2 is bonded to each other, the axial line of the axial line of the first cavity 11 and the second cavity 21 is overlapping, locking part 6 is in released state, pivot shaft 3 parts in the first cavity 11 enter the second cavity 21, pivot shaft 3 will have higher intensity and hardness, be used for supporting on the one hand the first sleeve 1, the weight of the second sleeve 2 and outer wing 21 ', can bear larger wind tunnel on the other hand, guaranteed the intensity that folded wing should have as a complete integral body, complete air maneuver demand simultaneously, do not affect the due performance of original design, when in folded state, locking part 6 is in the lock state, and the first sleeve 1 rotates relative to the end face of the second sleeve 2 under the effect of tractive unit 4 by pipe link 5, thereby realizes the folding of unmanned plane wing.
In the present embodiment, locking part 6 comprises the pin-and-hole 61 being arranged on the first sleeve 1, the spring 63 that withstands on pin-and-hole 61 outer ends, the pin 62 supporting with pin-and-hole 61 and is corresponding and be fixed on the pin post 64 on the second sleeve 2 with pin 62.The axis of pin 62 is parallel with the axis of pin-and-hole 61, the axis of spring 63 and pin-and-hole 61 axis quadratures, pin 62 is an inclined-plane near one end of pin-and-hole 61, can, by pin 62 along the moving of its axis, 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 is partial insertion pivot shaft 3, partial insertion the first sleeve 1 under the elastic force effect of spring 63, and pivot shaft 3 and the first sleeve 1 are synchronized with the movement; When locking part 6 is during in released state, pin 62 inserts pin-and-hole 61 and makes pin-and-hole 61 depart from pivot shafts 3 by depressing at pin post 64, 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 can move around along leading screw 41 on leading screw 41, and in the second cavity 21, be provided with one and the first isometric groove 22 of leading screw 41, leading screw 41 is just arranged on the first groove 22 and uses; And screw set 42 is with the first auricle 421, and pivot shaft 3 ends are fixed with the second auricle 32, with the two ends of pipe link 5, be hinged with the first auricle 421, the second auricle 32 respectively.Adopt monomotor to drive leading screw 41, by leading screw 41, rotate and drive the screw set 42 of engagement 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 ', can realize outer wing 21 ' rotating relative to inner wing 22 '.Motor can be fixed on inner wing 22 ' part like this, transmits easyly, and efficiency improves greatly.While adopting this kind of wingfold mechanism, wing aerofoil is seamless all the time, has so just guaranteed the integraty of wing aerofoil, has met the original aeroperformance requirement of aircraft.
In the present embodiment, the side of the first sleeve 1 also offers the second groove 12, its bearing of trend and its length consistent with the first sleeve 1 direction of axis line is less than the first sleeve side length, on pivot shaft 3, be fixed with the engagement section 31 corresponding with the second groove 12, when pivot shaft 3 stretches into the second cavity 21 when interior gradually, engagement section 31 is in the interior movement of the second groove 12, can prevent that like this pivot shaft 3 from, in the interior rolling of the first cavity 11, can avoid again pivot shaft 3 all to enter the first cavity 11.
The above-mentioned structure to the utility model unmanned plane wingfold mechanism is illustrated, and its principle of work is done to brief description below:
In use, in the junction of outer wing 21 ' and inner wing 22 ', along wing chordwise direction, at least two personal-machine wingfold mechanisms are installed, 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 coordinating 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 with respect to inner wing 22 ', approaches vertical (as shown in phantom in Figure 2) with inner wing 22 '; When driven by motor leading screw 41 rotates along a direction, and then drive the screw set 42 on leading screw 41 to the inner, to be moved by leading screw outer end along leading screw 41, and then by pipe link 5, drive pivot shafts 3 to take the string of a musical instrument of outer wing 21 ' and inner wing 22 ' junction to rotate as axle, realize and drive 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 with inner wing 22 ' in same plane, the end face of the first sleeve 1 and the second sleeve 2 is bonded to each other, the axial line of the axial line of the first cavity 11 and the second cavity 21 is overlapping, at this moment screw set 42 stops operating, pin 62 ends are subject to the compressing of pin post 64 and are inserted in pin-and-hole 61, pin-and-hole 61 just departs from pivot shaft 3, pivot shaft 3 and the first sleeve 1 release, along with the continuation of screw set 42 is moved, drive pivot shaft 3 to the interior movement of the second sleeve 2.When pivot shaft 3 nearly half while being positioned at the second sleeve 2, screw set 42 moves to leading screw 41 the inners just, motor stops, corresponding a series of motions all stop, wing has launched.
When needs get up wing-folding, electric machine rotation, drives leading screw 41 to rotate in the opposite direction, and screw set 42 is just moved outward by leading screw 41 the inners, and then drives pivot shaft 3 outwards to move.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 is because the elastic force of spring 63 inserts pivot shaft 3, and now pivot shaft 3 and the first sleeve 1 lock.The continuation of screw set 42 moves outward, and driving the first sleeve 1 to take the string of a musical instrument of outer wing 21 ' and inner wing 22 ' junction is axial upper rotation, and then drives upwards rotation of outer wing 21 '.When screw set 42 moves to leading screw outer end, motor stops, and corresponding a series of motions stop, and outer wing 21 ' turns to maximum position, and wing-folding completes.
Above-described embodiment is only explanation technical conceive of the present utility model and feature, and its object is to allow person skilled in the art can understand content of the present utility model and implement according to this, can not limit protection domain of the present utility model with this.All equivalences of doing according to the utility model Spirit Essence change or modify, within all should being encompassed in protection domain of the present utility model.
Claims (6)
1. a unmanned plane wingfold mechanism, is characterized in that: it comprises
The 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 pivot shaft is fixed in the first cavity, 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 during in released state, pivot shaft and the second sleeve can relative slidings;
Tractive unit, is fixed in the second cavity and can moves 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 deployed condition, 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 in the first cavity partly enters the second cavity; When in folded state, locking part is in the lock state, and described the first sleeve rotates 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 can move around along leading screw on described leading screw.
3. unmanned plane wingfold mechanism according to claim 2, is characterized in that: in described the second cavity, offer the first groove, 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 is fixed with 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 being arranged on the first sleeve, the spring that withstands on pin-and-hole outer end, the pin supporting with pin-and-hole and be corresponding and be fixed on the pin post on the second sleeve with pin, when locking part is in the lock state, described pin-and-hole is partial insertion pivot shaft, partial insertion the first sleeve under action of the spring; When locking part is during in released state, pin inserts pin-and-hole and makes pin-and-hole depart from pivot shaft by depressing at pin post.
6. unmanned plane wingfold mechanism according to claim 1, it is characterized in that: described the first sleeve side opening is provided with the second groove, the bearing of trend of described the second groove and its length consistent with the first sleeve direction of axis line is less than the first sleeve side length, is fixed with the engagement section corresponding with the second groove on described pivot shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420195473.7U CN203767065U (en) | 2014-04-21 | 2014-04-21 | Wing folding mechanism of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420195473.7U CN203767065U (en) | 2014-04-21 | 2014-04-21 | Wing folding mechanism of unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203767065U true CN203767065U (en) | 2014-08-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420195473.7U Withdrawn - After Issue CN203767065U (en) | 2014-04-21 | 2014-04-21 | Wing folding mechanism of unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN203767065U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103963958A (en) * | 2014-04-21 | 2014-08-06 | 西工大常熟研究院有限公司 | Wing folding mechanism for unmanned plane |
| WO2017008706A1 (en) * | 2015-07-15 | 2017-01-19 | 广州天翔航空科技有限公司 | Rotary locking mechanism and plant protection unmanned aerial vehicle having same |
| CN110466740A (en) * | 2019-08-26 | 2019-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of fold mechanism |
-
2014
- 2014-04-21 CN CN201420195473.7U patent/CN203767065U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103963958A (en) * | 2014-04-21 | 2014-08-06 | 西工大常熟研究院有限公司 | Wing folding mechanism for unmanned plane |
| WO2017008706A1 (en) * | 2015-07-15 | 2017-01-19 | 广州天翔航空科技有限公司 | Rotary locking mechanism and plant protection unmanned aerial vehicle having same |
| CN110466740A (en) * | 2019-08-26 | 2019-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of fold mechanism |
| CN110466740B (en) * | 2019-08-26 | 2022-11-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Folding mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140813 Effective date of abandoning: 20151209 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |