CN203767064U - Wing-folded type unmanned aerial vehicle - Google Patents
Wing-folded type unmanned aerial vehicle Download PDFInfo
- Publication number
- CN203767064U CN203767064U CN201420195341.4U CN201420195341U CN203767064U CN 203767064 U CN203767064 U CN 203767064U CN 201420195341 U CN201420195341 U CN 201420195341U CN 203767064 U CN203767064 U CN 203767064U
- Authority
- CN
- China
- Prior art keywords
- wing
- gear
- rotating shaft
- unmanned plane
- fuselage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Abstract
The utility model relates to a wing-folded type unmanned aerial vehicle. The wing-folded type unmanned aerial vehicle comprises a body and wings which are symmetrically arranged on two sides of the body. Each wing consists of an inner wing and an outer wing which are connected with each other, wherein the inner wing is fixed together with the body; the outer wing is far away from the body. The wing-folded type unmanned aerial vehicle is characterized in that a rotary shaft of which the axis is parallel to the chord line of each wing is arranged at a joint of the corresponding outer wing and the corresponding inner wing; a gear transmission mechanism which is used for driving each outer wing to rotate around the axis of the corresponding rotary shaft is arranged on the corresponding rotary shaft. According to the wing-folded type unmanned aerial vehicle, each wing consists of the inner wing which is fixed together with the body and the outer wing which is far away from the body, the rotary shaft is arranged at the joint of each outer wing and the corresponding inner wing, and the gear transmission mechanism which is used for driving each outer wing to rotate around the axis of the corresponding rotary shaft is arranged on the corresponding rotary shaft, so that friction force applied to the wings is dispersed to the body, and the service life can be prolonged.
Description
Technical field
The utility model belongs to unmanned plane field, be specifically related to that a kind of wing can fold unmanned plane.
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.
Application publication number is that the Chinese invention patent of CN 103043214A discloses a kind of collapsible unmanned plane, comprise fuselage and wing, fuselage bilateral symmetry is provided with wing, described wing one end hinge is contained on the coaxial mounted wing main shaft in the interior middle part of fuselage, in the equal level in the fuselage both sides of wing installation site, is shaped with wing discrepancy groove.Described wing drive to be controlled by the electronic or pneumatics that is arranged on bottom in fuselage and around this wing main shaft rotation.Although that this unmanned plane is used is flexible, of many uses, be convenient to personnel's operation, but its wing one end hinge is contained on the wing main shaft at middle part in fuselage, the unmanned plane friction force that wing is subject to when flight all concentrates on wing main shaft, cause the application force of wing main shaft large, very high to the requirement of strength of wing, wing and wing main shaft are easily impaired, service life is short, and 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 be in order to overcome the deficiencies in the prior art, provide that a kind of wing can fold unmanned plane.
For achieving the above object, the technical solution adopted in the utility model is: a kind of wing-folding formula unmanned plane, comprise fuselage and the symmetrical alar part that is installed on described fuselage both sides, described alar part is comprised of interconnective two sections of wings, the wing that definition fixes with described fuselage is inner wing, away from the wing of described fuselage, is outer wing, it is characterized in that: described outer wing and inner wing junction are provided with axis parallel in the rotating shaft of the wing string of a musical instrument, the gear drive for driving outer wing to rotate around rotating shaft core line is installed in described rotating shaft.
Optimally, described gear drive and rotating shaft are covered with shell.
Optimally, described gear drive comprises the second gear of being installed on the first gear of rotating shaft central authorities, being installed on respectively rotating shaft two ends, be fixed in outer wing and the 3rd gear being meshed with the second gear respectively, be installed in inner wing for driving the motor of the first gear rotation, the axis of described the first gear, the second gear and the 3rd gear and rotating shaft core line parallel.
Further, described gear drive also comprises the helical wheel that is fixed in inner wing and is meshed with the first gear, and four gear that be connected as a single entity coaxial with helical wheel, described motor is meshed with the 4th gear, and described helical gear axis is vertical with rotating shaft core line.
Further, between described motor and the 4th gear, be also engaged with at least one the 5th gear.
Further, described the first gear, the second gear and the 4th gear are as straight gear, and the 3rd gear is fan-shaped straight gear.
Because technique scheme is used, the utility model compared with prior art has following advantages: the utility model wing-folding formula unmanned plane, alar part is arranged to the inner wing that fixes with fuselage and away from the outer wing of fuselage, by rotating shaft being installed at outer wing and inner wing junction, and mounting teeth wheel drive mechanism is used for driving outer wing to rotate around rotating shaft core line in rotating shaft, the friction force that alar part is subject to is scattered on fuselage, can improves service life.
Accompanying drawing explanation
Accompanying drawing 1 is the structural representation of the utility model wing-folding formula unmanned plane;
Accompanying drawing 2 is the structural representation of the utility model wing-folding formula unmanned plane gear drive;
Accompanying drawing 3 is the alar part of the utility model wing-folding formula unmanned plane structural representation in different conditions;
Wherein, 1 ', fuselage; 2 ', alar part; 21 ', outer wing; 22 ', inner wing; 1, rotating shaft; 2, gear drive; 21, the first gear; 22, the second gear; 23, the 3rd gear; 24, helical wheel; 25, the 4th gear; 26, the 5th gear; 27, motor; 3, shell.
The specific embodiment
Below in conjunction with embodiment shown in the drawings, the utility model is further described.
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 '; Rotating shaft 1 is installed on outer wing 21 ' and inner wing 22 ' junction, and its axis parallel is in the wing string of a musical instrument; Gear drive 2 is installed in rotating shaft 1, for driving outer wing 21 ' to rotate around the axial line of rotating shaft 1.Upper by inner wing 22 ' being fixed on to fuselage 1 ', the friction force that unmanned plane alar part 2 ' is subject to is scattered on fuselage, can improve service life; And utilize gear drive 2 to realize outer wing 21 ' around the rotation of rotating shaft 1 axial line, and less to motor torque requirement, more steady when outer wing 21 ' is folding.
In the present embodiment, as shown in Figure 2, gear drive 2 comprises a plurality of pitch wheels (the first gear 21, the second gear 22, the 3rd gear 23, helical wheel 24, the 4th gear 25 and the 5th gear 26) and motor 27.The first gear 21 is a straight gear, is installed on rotating shaft 1 central authorities; The second gear 22 is two straight gears, is installed on respectively the two ends of rotating shaft 1; The 3rd gear 23 is two fan-shaped straight gears, is meshed respectively with the second gear 22, is fixed in outer wing 21 '; Helical wheel 24 is meshed with the first gear 21, and it is fixed in inner wing 22 ', for changing the transmission direction of gear; The 4th gear 25 is coaxial and be connected as a single entity with helical wheel 24; The 5th gear 26 being meshed with the 4th gear 25 is a straight gear, and it is connected with motor 27 and is rotated under it drives.Axis and rotating shaft 1 axis parallel of the first gear 21, the second gear 22 and the 3rd gear 23, the axis of helical wheel 24 is vertical with rotating shaft 1 axial line.When motor 27 operation, motor 27 drives the 5th gear 26 to rotate, and then driving the 4th gear 25 to rotate, helical wheel 24 rotates simultaneously, further drives the first gear 21 to rotate, two the second symmetrical gears 22 synchronously rotate, and then drive two the 3rd gears 23 to rotate, and because the 3rd gear 23 is connected with outer wing 21 ', final outer wing 21 ' and the 3rd gear 23 coaxial rotation, control opening with folding, as shown in Figure 3 of outer wing 21 '.Gear drive 2 adopts monomotor to drive, and motor 27 is fixed on inner wing 22 ' part, and its efficiency improves greatly, has increased the load ability of alar part 2 '; And gear drive 2 is single-direction transmissions, no matter forward and reverse rotation can only be driven by motor 27, be transferred to successively the 3rd gear 23, therefore no matter alar part 2 ' folds into any degree, all lock, there is the larger ability of bearing moment.
In the present embodiment, gear drive 2 and rotating shaft 1 are also covered with shell 3, have guaranteed the integraty of outer wing 21 ' aerofoil in folding process, have met the aeroperformance requirement of aircraft.The axle overall length 255mm at helical wheel 24 and the 4th gear 25 places, helical wheel 24 inside radiuss are 6.5mm, and the second gear 22 inside radiuss are 26mm, and the 3rd gear 23 inside radiuss are 21.5mm, and the central angle of quadrant gear is greater than 90 °.The quality of fit of each gear is no more than 0.2mm, and each parts installation error is no more than 2mm.
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 wing-folding formula unmanned plane, comprise fuselage and the symmetrical alar part that is installed on described fuselage both sides, described alar part is comprised of interconnective two sections of wings, the wing that definition fixes with described fuselage is inner wing, away from the wing of described fuselage, is outer wing, it is characterized in that: described outer wing and inner wing junction are provided with axis parallel in the rotating shaft of the wing string of a musical instrument, the gear drive for driving outer wing to rotate around rotating shaft core line is installed in described rotating shaft.
2. wing-folding formula unmanned plane according to claim 1, is characterized in that: described gear drive and rotating shaft are covered with shell.
3. wing-folding formula unmanned plane according to claim 1 and 2, it is characterized in that: described gear drive comprises the second gear of being installed on the first gear of rotating shaft central authorities, being installed on respectively rotating shaft two ends, be fixed in outer wing and the 3rd gear being meshed with the second gear respectively, be installed in inner wing for driving the motor of the first gear rotation, the axis of described the first gear, the second gear and the 3rd gear and rotating shaft core line parallel.
4. wing-folding formula unmanned plane according to claim 3, it is characterized in that: described gear drive also comprises the helical wheel that is fixed in inner wing and is meshed with the first gear, and four gear that be connected as a single entity coaxial with helical wheel, described motor is meshed with the 4th gear, and described helical gear axis is vertical with rotating shaft core line.
5. wing-folding formula unmanned plane according to claim 4, is characterized in that: between described motor and the 4th gear, be also engaged with at least one the 5th gear.
6. wing-folding formula unmanned plane according to claim 4, is characterized in that: described the first gear, the second gear and the 4th gear are as straight gear, and the 3rd gear is fan-shaped straight gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420195341.4U CN203767064U (en) | 2014-04-21 | 2014-04-21 | Wing-folded type unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420195341.4U CN203767064U (en) | 2014-04-21 | 2014-04-21 | Wing-folded type unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203767064U true CN203767064U (en) | 2014-08-13 |
Family
ID=51284285
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420195341.4U Expired - Fee Related CN203767064U (en) | 2014-04-21 | 2014-04-21 | Wing-folded type unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203767064U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105460206A (en) * | 2014-09-10 | 2016-04-06 | 深圳一电航空技术有限公司 | Unmanned aerial vehicle |
| CN106915438A (en) * | 2015-12-25 | 2017-07-04 | 北京臻迪机器人有限公司 | Unmanned plane |
| CN110127030A (en) * | 2019-05-24 | 2019-08-16 | 刘占波 | A kind of unmanned plane wing-folding self-locking device |
| CN110562434A (en) * | 2019-10-10 | 2019-12-13 | 河北科技大学 | Automatic folding wing unmanned aerial vehicle |
| CN112124564A (en) * | 2020-09-17 | 2020-12-25 | 西安电子科技大学 | Fixed wing unmanned aerial vehicle folding mechanism based on launching tube |
| CN113353243A (en) * | 2021-07-30 | 2021-09-07 | 郑州航空工业管理学院 | From multi-functional unmanned aerial vehicle commodity circulation car of becoming wing |
| CN114475118A (en) * | 2022-03-30 | 2022-05-13 | 合肥工业大学 | Post-disaster air-land dual-purpose rescue robot |
-
2014
- 2014-04-21 CN CN201420195341.4U patent/CN203767064U/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105460206A (en) * | 2014-09-10 | 2016-04-06 | 深圳一电航空技术有限公司 | Unmanned aerial vehicle |
| CN106915438A (en) * | 2015-12-25 | 2017-07-04 | 北京臻迪机器人有限公司 | Unmanned plane |
| CN110127030A (en) * | 2019-05-24 | 2019-08-16 | 刘占波 | A kind of unmanned plane wing-folding self-locking device |
| CN110562434A (en) * | 2019-10-10 | 2019-12-13 | 河北科技大学 | Automatic folding wing unmanned aerial vehicle |
| CN110562434B (en) * | 2019-10-10 | 2023-02-28 | 河北科技大学 | Automatic folding wing unmanned aerial vehicle |
| CN112124564A (en) * | 2020-09-17 | 2020-12-25 | 西安电子科技大学 | Fixed wing unmanned aerial vehicle folding mechanism based on launching tube |
| CN112124564B (en) * | 2020-09-17 | 2022-04-01 | 西安电子科技大学 | Fixed wing unmanned aerial vehicle folding mechanism based on launching tube |
| CN113353243A (en) * | 2021-07-30 | 2021-09-07 | 郑州航空工业管理学院 | From multi-functional unmanned aerial vehicle commodity circulation car of becoming wing |
| CN113353243B (en) * | 2021-07-30 | 2023-08-22 | 郑州航空工业管理学院 | Self-wing-changing multifunctional unmanned aerial vehicle logistics vehicle |
| CN114475118A (en) * | 2022-03-30 | 2022-05-13 | 合肥工业大学 | Post-disaster air-land dual-purpose rescue robot |
| CN114475118B (en) * | 2022-03-30 | 2023-09-15 | 合肥工业大学 | Post-disaster air-land dual-purpose rescue robot |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203767064U (en) | Wing-folded type unmanned aerial vehicle | |
| CN103963958B (en) | Unmanned plane wingfold mechanism | |
| CN102951290A (en) | Non-co-axial multi-rotor aircraft and attitude control method thereof | |
| CN105501422A (en) | All deflection propeller vector boost mechanism and underwater navigation vehicle | |
| CN203767067U (en) | Centre-of-gravity shift yawing device for helicopters | |
| CN204050974U (en) | There is the remote control distributor toy of multiple power set | |
| CN203094433U (en) | Tilting and rotating mechanism of helium airship duct | |
| CN203094440U (en) | Non-coaxial multi-rotor wing air vehicle | |
| CN105366053A (en) | Disk shaped vehicle | |
| CN204297058U (en) | A kind of high lift hardware aircraft | |
| CN109606634B (en) | Double-shaft wing folding mechanism | |
| CN204056293U (en) | Longitudinal staggered form DCB Specimen depopulated helicopter | |
| CN203767065U (en) | Wing folding mechanism of unmanned aerial vehicle | |
| CN103466088B (en) | The nacelle gear inclining rotary mechanism of a kind of rotocraft that verts | |
| CN204535711U (en) | The universal adjusting device of gyro | |
| CN101962078A (en) | Aircraft propeller vector engine | |
| CN202124116U (en) | Propeller transmission mechanism | |
| CN202569556U (en) | Toy helicopter | |
| CN210942215U (en) | Civil light aircraft | |
| CN208789939U (en) | A kind of rotary-wing transmission mechanism of unmanned plane | |
| CN206317614U (en) | Tire device and the multi-purpose vehicle(MPV) using the tire device | |
| CN100441258C (en) | Power assembly of model airplane | |
| CN105597335A (en) | Flight device with two power devices | |
| CN102285451A (en) | Propeller drive mechanism | |
| CN104097768A (en) | Longitudinally crossed dual-rotor helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140813 Termination date: 20200421 |