CN109305331A - It is a kind of with the quadrotor drone that can stack undercarriage - Google Patents
It is a kind of with the quadrotor drone that can stack undercarriage Download PDFInfo
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- CN109305331A CN109305331A CN201811308174.9A CN201811308174A CN109305331A CN 109305331 A CN109305331 A CN 109305331A CN 201811308174 A CN201811308174 A CN 201811308174A CN 109305331 A CN109305331 A CN 109305331A
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- rotor mechanism
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- shaft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention belongs to unmanned plane fields, more particularly to it is a kind of with the quadrotor drone that can stack undercarriage, it includes body, the first rotor mechanism, the second rotor mechanism, wherein the first rotor mechanism and the second rotor mechanism are symmetrically mounted at body two sides by corresponding second pin shaft and third pin shaft respectively；Unmanned plane in the present invention only realizes stacking for the first fold mechanism in the first rotor mechanism and the second rotor mechanism and the second fold mechanism by a steering engine；In unmanned plane landing, the first fold mechanism and the second fold mechanism in the first rotor mechanism and the second rotor mechanism can be with folding and unfoldings；When unmanned plane lands, the first fold mechanism and the second fold mechanism in the first rotor mechanism and the second rotor mechanism have certain pooling feature；When avoiding UAV Landing as ground in face of the impact of stabilizer blade and caused by steering engine high speed gear teeth impact failure the phenomenon that generation, and then ensure that the driving device on unmanned plane is not damaged.
Description
Technical field
The invention belongs to unmanned plane fields more particularly to a kind of with the quadrotor drone that can stack undercarriage.
Background technique
The undercarriage in traditional quadrotor drone point, which does not have, at present can stack function；In unmanned plane during flying process
In, without the undercarriage for stacking function the flight windage of unmanned plane is increased, and then influence the voyage and speed of unmanned plane；
Even if some unmanned planes have the undercarriage for stacking function, also increase unmanned plane because of the complexity of the control mode of undercarriage
Research and development and production cost；There are two types of the control mode of undercarriage on traditional unmanned plane with undercarriage substantially has: a kind of
It is the hydraulic pump being installed on by Serve Motor Control on body, and then stacking by several undercarriages of hydraulic control；It is another
Kind is the folding by several undercarriages of at least two Serve Motor Controls；This traditional undercarriage stacking mode similarly increases
Add research and development and the production cost of unmanned plane, to influence the progress that unmanned plane is widely used, and then influences relevant enterprise
Economic benefit.
The present invention design it is a kind of solved the problems, such as with the quadrotor drone that can stack undercarriage it is as above.
Summary of the invention
To solve drawbacks described above in the prior art, the present invention disclose it is a kind of with can stack undercarriage quadrotor nobody
Machine, it adopts the following technical solutions to realize.
In the description of the present invention, it should be noted that the indicating positions such as term "inner", "lower", "upper" or position are closed
System be orientation based on the figure perhaps positional relationship or the invention product using when the orientation or position usually put
Set relationship, it is only for convenient for the description present invention and simplify description, rather than the device or element of indication or suggestion meaning must
There must be specific orientation, be constructed or operated with specific orientation, therefore be not considered as limiting the invention.In addition, art
Language " first ", " second " etc. are only used for distinguishing description, are not understood to indicate or imply relative importance.
It is a kind of with the quadrotor drone that can stack undercarriage, it is characterised in that: it include body, steering engine, second pin
Axis, third pin shaft, the first rotor mechanism, the second rotor mechanism, wherein body is existing quadrotor drone body；First rotation
Wing mechanism and the second rotor mechanism are symmetrically mounted at body two sides by corresponding second pin shaft and third pin shaft respectively.
Steering engine passes through dynamic first rotor mechanism of the driving gear band being mounted thereon and the second rotor mechanism synchronizes upper and lower pendulum
It is dynamic；When unmanned plane lift-off flight, steering engine drives the first rotor mechanism and the second rotor mechanism along corresponding second pin shaft and third
Pin shaft is swung up, while the first fold mechanism and the folding of the second fold mechanism in the first rotor mechanism and the second rotor mechanism
It packs up, to reduce the windage that unmanned plane is subject in flight course, and then improves unmanned plane during flying voyage and speed；Unmanned plane
When from airborne, steering engine drives the first rotor mechanism and the second rotor mechanism downward along corresponding second pin shaft and third pin shaft
It swings, while the first fold mechanism in the first rotor mechanism and the second rotor mechanism and the second fold mechanism put down expansion, are
The landing of unmanned plane is ready.
As the further improvement of this technology, opened up on above-mentioned body there are two the first loose slot, gear grooved, driver slot,
The first loose slot of two of them is symmetrically distributed in the two sides of body；Gear grooved is located on the upper surface of body, and gear grooved with
Two side end faces of body communicate；Gear grooved is laterally communicated with two the first loose slots；Driver slot is located on the upper surface of body,
And driver slot is laterally communicated with gear grooved；Driver slot and two the first loose slots are located at the two sides of gear grooved.
As the further improvement of this technology, above-mentioned steering engine is mounted in the driver slot on body, and steering engine be installed on
Flight control system electrical connection on body；The output shaft end of steering engine is equipped with driving gear, and gear is driven to be located on body
Gear grooved in；First transmission gear is mounted in the gear grooved on body by the first pin shaft, and the first transmission gear and drive
Moving gear is meshed.
As the further improvement of this technology, above-mentioned first rotor mechanism includes cantilever, the second transmission gear, axle sleeve, cross
Beam, connecting rod, the 4th pin shaft, swing rod, third transmission gear, locating piece, transmission shaft, first bevel gear, the first fold mechanism, second
Fold mechanism, wherein one end of cantilever offers pin hole, offers pin hole on the end face of the second transmission gear；Second transmission gear
One end by offering pin hole on one end face and cantilever is connected, and the pin on the pin hole and cantilever on the second transmission gear
Hole docking；One end that pin hole is offered on cantilever is mounted on one on body together with the second transmission gear by the second pin shaft
In one loose slot；Second transmission gear is meshed with driving gear；The first revolution axis hole is offered at the end face center of axle sleeve；Axis
The second loose slot of certain radian, and the second loose slot and the first rotating shaft are offered at the periphery center of set along circumferential direction
Hole communicates；The both ends of the periphery of axle sleeve circumferentially offer the flank of tooth of 360 degree of radians respectively；Axle sleeve passes through its periphery center
The one end for not offering pin hole in place and cantilever is connected, and the central axis of the central axis of axle sleeve and the second transmission gear is flat
Row；The second loose slot on axle sleeve is located at the lower section of cantilever；The bearing fit that crossbeam passes through its periphery and the first revolution axis hole
It is installed in axle sleeve, and axle sleeve is located at the center of crossbeam；One end of connecting rod offers pin hole, does not offer pin hole on connecting rod
One end passes vertically through the first revolution axis hole on axle sleeve from bottom to up and is connected with crossbeam；The both ends of swing rod have a pin
Hole；Hinged notch is offered on the end face of one end of swing rod, and hinged notch is communicated with the pin hole for being located at this end on swing rod；Connecting rod
On be provided in the hinged notch that one end of pin hole is mounted on swing rod by the 4th pin shaft；The one end not connect with connecting rod on swing rod
It is mounted in the first loose slot on body by third pin shaft, and the position that connect with body of swing rod is located at the lower section of cantilever；
Body, cantilever, connecting rod and swing rod form a parallelogram；The both ends of crossbeam are separately installed with the first fold mechanism and second
Fold mechanism；The first fixed shaft hole and the second revolution axis hole are offered on the end face of locating piece；Two locating pieces are each by it
On the first fixed shaft hole be fixedly mounted on crossbeam, and two locating pieces are symmetrically distributed in the two sides of axle sleeve；Transmission shaft is logical
The bearing fit for the second revolution axis hole crossed on its periphery and two locating pieces is mounted on two locating pieces；Two thirds pass
Moving gear is mounted on transmission shaft, and two third transmission gears are meshed with the flank of tooth at axle sleeve both ends respectively；Third driving cog
Cooperate between wheel and transmission shaft for key；Two first bevel gears are separately mounted to the both ends of transmission shaft, and two first bevel gears
It is matched respectively with the first fold mechanism and the second fold mechanism.
As the further improvement of this technology, above-mentioned first fold mechanism includes propeller aircraft, motor, fixing seat, folding
Folded block, the second fixed shaft hole, third loose slot, sliding slot, the 5th pin shaft, second bevel gear, buffer stopper, dashpot, the 4th revolution
Axis hole, stabilizer blade, the 6th pin shaft, buffering axle pad, sliding block, buffer spring, buffering leaf spring, are wherein provided with folding on the lower end surface of fixing seat
Folded slot, and folded slot is communicated with a side end face of fixing seat；Third revolution axis hole is provided on one side end face of fixing seat, and
Third revolution axis hole is communicated with folded slot；One end of the side end face and transmission shaft that communicate in fixing seat with folded slot is connected；It is fixed
Motor is installed on the upper surface of seat；The output shaft end of motor is equipped with propeller aircraft；Winged control on motor and body
System electrical connection；Be provided with third loose slot on the lower end surface of folded piece, and on third loose slot and folded piece two it is opposite
Side end face communicates；Second that perforation is provided between the two opposite side end faces not communicated with third loose slot on folded piece is fixed
Axis hole, and the second fixed shaft hole is located at the top of third loose slot；It is symmetrical along the vertical direction on two sides of third loose slot
It opens there are two sliding slot on ground；One end that the second fixed shaft hole is provided on folded piece is mounted on folding in fixing seat by the 5th pin shaft
In slot；The third that 5th pin shaft one end is stretched out in fixing seat turns round axis hole；Second bevel gear, which is mounted on the 5th pin shaft, stretches out
One end of three revolution axis holes；Second bevel gear is meshed on transmission shaft positioned at first bevel gear herein；The lower end of buffer stopper
Dashpot is offered on face, and dashpot is communicated with two opposite side end faces on buffer stopper；On buffer stopper not with dashpot
The two side end faces lower end communicated is provided with the 4th revolution axis hole of perforation；Two side end faces not communicated with dashpot on buffer stopper
It symmetrically installs there are two sliding block upper end；Buffer stopper is slidably installed on folded piece by two sliding blocks and two sliding slots
Third loose slot in；Axis hole is offered between two opposite side end faces of the upper end of stabilizer blade；Stabilizer blade is pacified by the 6th pin shaft
In the dashpot on buffer stopper；The 4th revolution axis hole that the both ends of 6th pin shaft are each passed through dashpot two sides enters folding
In two sliding slots on block；Circumferentially equably there are two buffer axle pad for installation respectively on the periphery at the both ends of the 6th pin shaft；
Two buffering axle pads for being mounted on the 6th every end of pin shaft are matched with corresponding sliding slot；Buffer spring is located at the third on folded piece
In loose slot；The upper end of buffer spring is connect with the inner wall of three loose slots of ground, the upper surface connection of lower end and buffer stopper；Buffering
Leaf spring one end is connect with the side end face communicated on buffer stopper with dashpot, does not open up one of axis hole on the other end and stabilizer blade
Side end face connection.
Zero in components and the first fold mechanism as the further improvement of this technology, in above-mentioned second fold mechanism
Component is identical；The internal structure of second fold mechanism and the internal structure of the first fold mechanism are about the cross in rotor mechanism
The median plane of beam is symmetrical；In the side end face communicated in fixing seat in second this fold mechanism with folded slot and the first rotor mechanism
Crossbeam the other end be connected.
As the further improvement of this technology, above-mentioned second rotor mechanism is mounted on another first loose slot on body
In；Components in second rotor mechanism are identical with the components in the first rotor mechanism, and the second rotor mechanism
Internal structure and the internal structure of the first rotor mechanism are symmetrical about the median plane of body；The second transmission in second rotor mechanism
Gear is meshed with the first transmission gear in gear grooved；The winged control subsystem on two motors and body in second rotor mechanism
System electrical connection.
As the further improvement of this technology, the transmission ratio of above-mentioned second transmission gear and driving gear is 1:1.
As the further improvement of this technology, the biography of the periphery of teeth is offered on above-mentioned third transmission gear and axle sleeve
Dynamic ratio is 1:1.
As the further improvement of this technology, the transmission ratio of above-mentioned first bevel gear and second bevel gear is 1:1.
Relative to traditional unmanned plane, the unmanned plane in the present invention only realized by a steering engine the first rotor mechanism and
The first fold mechanism and the second fold mechanism in second rotor mechanism stack；In unmanned plane landing, the first rotor mechanism
With in the second rotor mechanism the first fold mechanism and the second fold mechanism put down, be ready for the landing of unmanned plane；Meanwhile
The first fold mechanism and the second fold mechanism in first rotor mechanism and the second rotor mechanism have certain pooling feature；By
The rotation speed of operative gear component during the work time in steering engine is very high, if be easily damaged by impact；Institute
It is avoided with the pooling feature in the first fold mechanism and the second fold mechanism in the first rotor mechanism and the second rotor mechanism
When UAV Landing as ground in face of stabilizer blade impact and caused by steering engine high speed gear teeth impact failure the phenomenon that
Generation, and then ensure that the driving device on unmanned plane is not damaged, so that the landing of unmanned plane is steady, to the maximum extent
Extend the service life of unmanned plane；The configuration of the present invention is simple has preferable using effect.
Detailed description of the invention
Fig. 1 is unmanned plane overall schematic.
Fig. 2 is driving gear, the first transmission gear, the first rotor mechanism and the second rotor mechanism cooperation diagrammatic cross-section.
Fig. 3 is the first rotor mechanism, the second rotor mechanism and body cooperation diagrammatic cross-section.
Fig. 4 is the first fold mechanism and the second fold mechanism profile schematic diagram.
Fig. 5 is steering engine and body cooperation diagrammatic cross-section.
Fig. 6 is body schematic diagram.
Fig. 7 is the first rotor mechanism schematic diagram.
Fig. 8 is the first rotor mechanism diagrammatic cross-section.
Fig. 9 is cantilever, axle sleeve, crossbeam, connecting rod and swing rod cooperation diagrammatic cross-section.
Figure 10 is axle sleeve schematic diagram.
Figure 11 is axle sleeve diagrammatic cross-section.
Figure 12 is swing rod schematic diagram.
Figure 13 is the first locating piece schematic diagram.
Figure 14 is the first fold mechanism schematic diagram.
Figure 15 is the first fold mechanism diagrammatic cross-section.
Figure 16 is limit leaf spring, buffer stopper, stabilizer blade and buffer spring cooperation diagrammatic cross-section.
Figure 17 is sliding block, buffering axle pad and folded piece cooperation diagrammatic cross-section.
Figure 18 is fixing seat schematic diagram.
Figure 19 is folded piece schematic diagram.
Figure 20 is folded piece diagrammatic cross-section.
Figure 21 is buffer stopper schematic diagram.
Figure label title: 1, body；2, the first loose slot；3, gear grooved；4, driver slot；5, steering engine；6, gear is driven；
7, the first transmission gear；8, the first pin shaft；9, the second pin shaft；10, third pin shaft；11, the first rotor mechanism；12, the second rotor
Mechanism；13, cantilever；14, the second transmission gear；15, axle sleeve；16, the first revolution axis hole；17, the second loose slot；18, crossbeam；
19, connecting rod；20, the 4th pin shaft；21, swing rod；22, hinged notch；23, buffer spring；24, leaf spring is buffered；25, third driving cog
Wheel；26, locating piece；27, the first fixed shaft hole；28, the second revolution axis hole；29, transmission shaft；30, first bevel gear；31, first
Fold mechanism；32, the second fold mechanism；33, propeller aircraft；34, motor；35, fixing seat；36, folded slot；37, third is returned
Shaft hole；38, folded piece；39, the second fixed shaft hole；40, third loose slot；41, sliding slot；42, the 5th pin shaft；43, the second cone
Gear；44, buffer stopper；45, dashpot；46, the 4th revolution axis hole；47, stabilizer blade；48, the 6th pin shaft；49, axle pad is buffered；50,
Sliding block.
Specific embodiment
As shown in Figure 1, 2, 3, it include body 1, steering engine 5, the second pin shaft 9, third pin shaft 10, the first rotor mechanism 11,
Second rotor mechanism 12, wherein body 1 is existing quadrotor drone body 1；First rotor mechanism 11 and the second gyroplane
Structure 12 is symmetrically mounted at 1 two sides of body by corresponding second pin shaft 9 and third pin shaft 10 respectively.
As shown in Fig. 2,5, steering engine 5 passes through the driving gear 6 being mounted thereon and drives the first rotor mechanism 11 and the second rotation
Wing mechanism 12 synchronizes upper and lower swing；When unmanned plane lift-off flight, steering engine 5 drives the first rotor mechanism 11 and the second rotor mechanism
12 are swung up along corresponding second pin shaft 9 and third pin shaft 10, while in the first rotor mechanism 11 and the second rotor mechanism 12
The first fold mechanism 31 and the second fold mechanism 32 folding pack up, to reduce the wind that unmanned plane is subject in flight course
Resistance, and then improve unmanned plane during flying voyage and speed；When unmanned plane is from airborne, steering engine 5 drives 11 He of the first rotor mechanism
Second rotor mechanism 12 along corresponding second pin shaft 9 and third pin shaft 10 to lower swing, while the first rotor mechanism 11 and second
The first fold mechanism 31 and the second fold mechanism 32 in rotor mechanism 12 put down expansion, are ready for the landing of unmanned plane.
As shown in fig. 6, opened up on above-mentioned body 1 there are two the first loose slot 2, gear grooved 3, driver slot 4, two of them the
One loose slot 2 is symmetrically distributed in the two sides of body 1；Gear grooved 3 is located on the upper surface of body 1, and gear grooved 3 and body 1
Two side end faces communicate；Gear grooved 3 is laterally communicated with two the first loose slots 2；Driver slot 4 is located on the upper surface of body 1,
And driver slot 4 is laterally communicated with gear grooved 3；Driver slot 4 and two the first loose slots 2 are located at the two sides of gear grooved 3.
As shown in Fig. 3,5, above-mentioned steering engine 5 is mounted in the driver slot 4 on body 1, and steering engine 5 and is installed on body 1
Flight control system electrical connection；The output shaft end of steering engine 5 is equipped with driving gear 6, and gear 6 is driven to be located on body 1
In gear grooved 3；First transmission gear 7 is mounted in the gear grooved 3 on body 1 by the first pin shaft 8, and the first transmission gear 7
It is meshed with driving gear 6.
As shown in Figure 7,8, above-mentioned first rotor mechanism 11 includes cantilever 13, the second transmission gear 14, axle sleeve 15, crossbeam
18, connecting rod 19, the 4th pin shaft 20, swing rod 21, third transmission gear 25, locating piece 26, transmission shaft 29, first bevel gear 30,
One fold mechanism 31, the second fold mechanism 32, wherein as shown in fig. 7, one end of cantilever 13 offers pin hole, the second transmission gear
Pin hole is offered on 14 end face；Second transmission gear 14 is solid by the one end for offering pin hole on one end face and cantilever 13
Even, and the pin hole on the second transmission gear 14 is docked with the pin hole on cantilever 13；As shown in figure 3, offering pin hole on cantilever 13
First loose slot 2 being mounted on body 1 together with the second transmission gear 14 by the second pin shaft 9 of one end in；Second passes
Moving gear 14 is meshed with driving gear 6；As shown in Figure 10, the first revolution axis hole 16 is offered at the end face center of axle sleeve 15；
As shown in figure 11, the second loose slot 17 of certain radian, and second are offered at the periphery center of axle sleeve 15 along circumferential direction
Loose slot 17 is communicated with the first revolution axis hole 16；As shown in Figure 10, the both ends of the periphery of axle sleeve 15 circumferentially offer respectively
The flank of tooth of 360 degree of radians；As shown in Fig. 7,9, axle sleeve 15 is not by offering pin hole at its periphery center and on cantilever 13
One end is connected, and the centerline axis parallel of the central axis of axle sleeve 15 and the second transmission gear 14；As shown in figure 9, on axle sleeve 15
The second loose slot 17 be located at the lower section of cantilever 13；As shown in figure 4, crossbeam 18 turns round axis hole 16 by its periphery and first
Bearing fit is installed in axle sleeve 15, and axle sleeve 15 is located at the center of crossbeam 18；As shown in figure 9, one end of connecting rod 19 opens up
Have pin hole, do not offered on connecting rod 19 pin hole one end pass vertically through from bottom to up on axle sleeve 15 first revolution axis hole 16 with
Crossbeam 18 is connected；As shown in figure 12, the both ends of swing rod 21 have a pin hole；It is offered on the end face of one end of swing rod 21
Hinged notch 22, and hinged notch 22 is communicated with the pin hole for being located at this end on swing rod 21；As shown in figure 9, being provided with pin on connecting rod 19
The one end in hole is mounted in the hinged notch 22 on swing rod 21 by the 4th pin shaft 20；As shown in figure 3, on swing rod 21 not with connecting rod
One end of 19 connections are mounted in the first loose slot 2 on body 1 by third pin shaft 10, and swing rod 21 is connect with body 1
Position is located at the lower section of cantilever 13；Body 1, cantilever 13, connecting rod 19 and swing rod 21 form a parallelogram；As shown in fig. 7,
The both ends of crossbeam 18 are separately installed with the first fold mechanism 31 and the second fold mechanism 32；As shown in figure 13, the end of locating piece 26
The first fixed shaft hole 27 and the second revolution axis hole 28 are offered on face；As shown in fig. 7, two locating pieces 26 are each by thereon
First fixed shaft hole 27 is fixedly mounted on crossbeam 18, and two locating pieces 26 are symmetrically distributed in the two sides of axle sleeve 15；Transmission
Axis 29 is mounted on two locating pieces 26 by the bearing fit of the second revolution axis hole 28 on its periphery and two locating pieces 26
On；Two third transmission gears 25 are mounted on transmission shaft 29, and two third transmission gears 25 respectively with 15 both ends of axle sleeve
The flank of tooth is meshed；Cooperate between third transmission gear 25 and transmission shaft 29 for key；Two first bevel gears 30 are separately mounted to pass
The both ends of moving axis 29, and two first bevel gears 30 are matched with the first fold mechanism 31 and the second fold mechanism 32 respectively.
As shown in figure 14, above-mentioned first fold mechanism 31 includes propeller aircraft 33, motor 34, fixing seat 35, folded piece
38, the second fixed shaft hole 39, third loose slot 40, sliding slot 41, the 5th pin shaft 42, second bevel gear 43, buffer stopper 44, dashpot
45, the 4th revolution axis hole 46, stabilizer blade 47, the 6th pin shaft 48, buffering axle pad 49, sliding block 50, buffer spring 23, buffering leaf spring 24,
Wherein as shown in figure 18, folded slot 36, and a side of folded slot 36 and fixing seat 35 are provided on the lower end surface of fixing seat 35
Face communicates；Third revolution axis hole 37, and third revolution axis hole 37 and 36 phase of folded slot are provided on one side end face of fixing seat 35
It is logical；As shown in figure 4, the side end face communicated in fixing seat 35 with folded slot 36 and one end of transmission shaft 29 are connected；As shown in figure 18,
Motor 34 is installed on the upper surface of fixing seat 35；The output shaft end of motor 34 is equipped with propeller aircraft 33；Motor 34 with
Winged control subsystem electrical connection on body 1；As shown in figure 19, third loose slot 40 is provided on the lower end surface of folded piece 38, and
Third loose slot 40 is communicated with two opposite side end faces on folded piece 38；As shown in figure 20, not living with third on folded piece 38
The second fixed shaft hole 39 of perforation is provided between two opposite side end faces that dynamic slot 40 communicates, and the second fixed shaft hole 39 is located at
The top of third loose slot 40；Sliding slot 41 there are two symmetrically being opened along the vertical direction on two sides of third loose slot 40；Such as
Shown in Figure 15, one end that the second fixed shaft hole 39 is provided on folded piece 38 passes through the folding that the 5th pin shaft 42 is mounted in fixing seat 35
In folded slot 36；The third that 5th pin shaft, 42 one end is stretched out in fixing seat 35 turns round axis hole 37；Second bevel gear 43 is mounted on the 5th
One end of third revolution axis hole 37 is stretched out on pin shaft 42；As shown in figure 8, being located at herein on second bevel gear 43 and transmission shaft 29
First bevel gear 30 is meshed；As shown in figure 21, dashpot 45 is offered on the lower end surface of buffer stopper 44, and dashpot 45 and slow
The two opposite side end faces rushed on block 44 communicate；The two side end faces lower end not communicated with dashpot 45 on buffer stopper 44 is provided with
Penetrate through the 4th revolution axis hole 46；As shown in figure 15, the upper end pair for two side end faces not communicated with dashpot 45 on buffer stopper 44
Claiming ground installation, there are two sliding blocks 50；Buffer stopper 44 is slidably installed by two sliding blocks 50 and two sliding slots 41 in folded piece
In third loose slot 40 on 38；Axis hole is offered between two opposite side end faces of the upper end of stabilizer blade 47；Stabilizer blade 47 passes through
6th pin shaft 48 is mounted in the dashpot 45 on buffer stopper 44；The both ends of 6th pin shaft 48 are each passed through 45 two sides of dashpot
4th revolution axis hole 46 enters in two sliding slots 41 on folded piece 38；As shown in Figure 15,17, outside the both ends of the 6th pin shaft 48
Circumferentially equably there are two buffer axle pad 49 for installation respectively on disc；It is mounted on two buffering axle pads at the every end of the 6th pin shaft 48
49 match with corresponding sliding slot 41；As shown in figure 16, buffer spring 23 is located in the third loose slot 40 on folded piece 38；It is slow
The upper end for rushing spring 23 is connect with the inner wall of three loose slots of ground, and lower end is connect with the upper surface of buffer stopper 44；Buffer leaf spring 24
One end is connect with the side end face communicated on buffer stopper 44 with dashpot 45, does not open up the one of axis hole on the other end and stabilizer blade 47
A side end face connection.
As shown in Fig. 4,7, the components in above-mentioned second fold mechanism 32 and the components in the first fold mechanism 31 are complete
It is exactly the same；The internal structure of second fold mechanism 32 and the internal structure of the first fold mechanism 31 are about the crossbeam in rotor mechanism
18 median plane is symmetrical；The side end face communicated in fixing seat 35 in second this fold mechanism with folded slot 36 and the first gyroplane
The other end of crossbeam 18 in structure 11 is connected.
As shown in figure 3, above-mentioned second rotor mechanism 12 is mounted in another first loose slot 2 on body 1；Second rotation
Components in wing mechanism 12 are identical with the components in the first rotor mechanism 11, and the inside of the second rotor mechanism 12
Structure and the internal structure of the first rotor mechanism 11 are symmetrical about the median plane of body 1；As shown in Fig. 2, the second rotor mechanism 12
In the second transmission gear 14 be meshed with the first transmission gear 7 in gear grooved 3；Two motors in second rotor mechanism 12
34 are electrically connected with the winged control subsystem on body 1.
As shown in Fig. 2, the transmission ratio of above-mentioned second transmission gear 14 and driving gear 6 is 1:1.
As shown in figure 3, the transmission ratio for offering the periphery of teeth on above-mentioned third transmission gear 25 and axle sleeve 15 is 1:
1。
As shown in fig. 7, the transmission ratio of above-mentioned first bevel gear 30 and second bevel gear 43 is 1:1.
The transmission ratio of the second transmission gear 14 and driving gear 6 is 1:1, third transmission gear 25 and axle sleeve 15 in the present invention
On offer teeth the transmission ratio of periphery be 1:1, transmission ratio the setting for 1:1 of first bevel gear 30 and second bevel gear 43
Meter purpose is, when unmanned plane lift-off, when steering engine 5 drives driving gear 6 to be rotated by 90 °, driving gear 6 drives the first gyroplane
The second transmission gear 14 in structure 11 is rotated by 90 °；Meanwhile it driving gear 6 to pass through the first transmission gear 7 being engaged with and driving
The second transmission gear 14 in second rotor mechanism 12 is rotated by 90 °；In first rotor mechanism 11 and the second rotor mechanism 12
Two transmission gears 14 drive the first rotor by the cantilever 13 in the first rotor mechanism 11 and the second rotor mechanism 12 respectively respectively
Mechanism 11 and the second rotor mechanism 12 are swung up 90 degree of positions that reach capacity around corresponding second pin shaft 9 and third pin shaft 10；
Axle sleeve 15 in first rotor mechanism, 11 second rotor mechanism 12 drives two third transmission gears 25 being meshed therewith respectively
It is rotated by 90 °；Third transmission gear 25 in first rotor mechanism, 11 second rotor mechanism 12 is driven by corresponding transmission shaft 29
Two first bevel gears 30 of 29 two sides of transmission shaft are rotated by 90 °；Two first bevel gears 30 difference in first rotor mechanism 11
Two second bevel gears 43 in the first fold mechanism 31 and the second fold mechanism 32 are driven to be rotated by 90 °；Second rotor mechanism 12
In two first bevel gears 30 drive two second in corresponding first fold mechanism 31 and the second fold mechanism 32 respectively
Bevel gear 43 is rotated by 90 °；The second cone tooth in the first fold mechanism 31 and the second fold mechanism 32 in first rotor mechanism 11
Wheel 43 drives the first fold mechanism 31 and the second fold mechanism 32 around the 5th pin shaft 42 by corresponding 5th pin shaft 42 respectively
Central axis is swung up 90 degree, so that the first fold mechanism 31 and the second fold mechanism 32 occur fully horizontally to fold, to protect
It demonstrate,proves windage of the unmanned plane in flight course and reaches minimum, and then the air mileage and speed that guarantee unmanned plane be not by windage
It influences；When unmanned plane starts landing, when steering engine 5 drives driving gear 6 to reversely rotate 90 degree, driving gear 6 drives the first rotation
The second transmission gear 14 in wing mechanism 11 reversely rotates 90 degree；Meanwhile gear 6 being driven to pass through the first driving cog being engaged with
Wheel 7 drives the second transmission gear 14 in the second rotor mechanism 12 to reversely rotate 90 degree；First rotor mechanism 11 and the second rotor
The second transmission gear 14 in mechanism 12 is distinguished by the cantilever 13 in the first rotor mechanism 11 and the second rotor mechanism 12 respectively
The first rotor mechanism 11 and the second rotor mechanism 12 is driven to reach around corresponding second pin shaft 9 and third pin shaft 10 to 90 degree of lower swing
To extreme position；Axle sleeve 15 in first rotor mechanism, 11 second rotor mechanism 12 drives two thirds being meshed therewith respectively
Transmission gear 25 reversely rotates 90 degree；Third transmission gear 25 in first rotor mechanism, 11 second rotor mechanism 12 passes through corresponding
Transmission shaft 29 drive 29 two sides of transmission shaft two first bevel gears 30 reversely rotate 90 degree；Two in first rotor mechanism 11
A first bevel gear 30 drives two second bevel gears 43 in the first fold mechanism 31 and the second fold mechanism 32 reversed respectively
It is rotated by 90 °；Two first bevel gears 30 in second rotor mechanism 12 drive corresponding first fold mechanism 31 and second respectively
Two second bevel gears 43 in fold mechanism 32 reversely rotate 90 degree；31 He of the first fold mechanism in first rotor mechanism 11
Second bevel gear 43 in second fold mechanism 32 drives the first fold mechanism 31 and the by corresponding 5th pin shaft 42 respectively
Two-fold mechanism 32 around the 5th pin shaft 42 central axis to 90 degree of lower swing so that the first fold mechanism 31 and the second folding machine
Structure 32 occurs vertically to put down completely, is ready for the landing of unmanned plane.
Workflow of the invention: it when unmanned plane lift-off, is run by the steering engine 5 on remote control control body 1；Steering engine
5 drive the second transmission gear 14 rotation in the first transmission gear 7 and the first rotor mechanism 11 by driving gear 6；Due to
Components in two rotor mechanisms 12 are identical with the components in the first rotor mechanism 11, and the second rotor mechanism 12
Internal structure and the internal structure of the first rotor mechanism 11 are symmetrical about the median plane of body 1, so the first transmission gear 7 drives
The second transmission gear 14 rotation in second rotor mechanism 12；The rotation side of the second transmission gear 14 in first rotor mechanism 11
To opposite with the direction of rotation of the second transmission gear 14 in the second rotor mechanism 12；In the work of corresponding second transmission gear 14
Under, the cantilever 13 in the first rotor mechanism 11 and the second rotor mechanism 12 is swung up along corresponding second pin shaft 9 respectively；The
Cantilever 13 in one rotor mechanism 11 is driven in the first rotor mechanism 11 by corresponding axle sleeve 15, transmission shaft 29 and connecting rod 19
Swing rod 21 is swung up around corresponding third pin shaft 10；Cantilever 13 in second rotor mechanism 12 passes through corresponding axle sleeve 15, biography
Moving axis 29 and connecting rod 19 drive the swing rod 21 in the second rotor mechanism 12 to be swung up around corresponding third pin shaft 10；Due to first
Formed between rotor mechanism 11 or axle sleeve 15, connecting rod 19, swing rod 21 and body 1 in the second rotor mechanism 12 one it is closed flat
Row quadrangle, so in the first rotor mechanism 11 and the second rotor mechanism 12 when being swung up, in the first rotor mechanism 11
Connecting rod 19 in connecting rod 19 and the second rotor mechanism 12 is in a vertical state always, to guarantee the first rotor mechanism 11 and the second rotation
The flight that propeller aircraft 33 in wing mechanism 12 is in a horizontal position always without influencing unmanned plane；First rotor mechanism, 11 He
When cantilever 13 in second rotor mechanism 12 drives corresponding axle sleeve 15 to be swung up, axle sleeve 15 in the first rotor mechanism 11 with
Relative rotation occurs for corresponding two third transmission gears 25；Axle sleeve 15 in second rotor mechanism 12 and corresponding two thirds
Relative rotation occurs for transmission gear 25；Axle sleeve 15 in first rotor mechanism 11 and the second rotor mechanism 12 drives accordingly respectively
Third transmission gear 25 is rotated around the central axis of corresponding transmission shaft 29；Two third driving cogs in first rotor mechanism 11
Wheel 25 drives the first bevel gear 30 at 29 both ends of transmission shaft to rotate by corresponding transmission shaft 29；In second rotor mechanism 12
Two third transmission gears 25 by corresponding transmission shaft 29 drive 29 both ends of transmission shaft first bevel gear 30 rotate；
Two first bevel gears 30 in first rotor mechanism 11 drive two second bevel gears 43 to rotate respectively；First gyroplane
The second bevel gear 43 in the first fold mechanism 31 in structure 11 drives the first fold mechanism 31 by corresponding 5th pin shaft 42
In folded piece 38, buffer stopper 44 and stabilizer blade 47 together around the central axis of the 5th pin shaft 42 into transmission shaft 29 side oscillation and send out
It is raw to fold；The second bevel gear 43 in the second fold mechanism 32 in first rotor mechanism 11 passes through corresponding 5th pin shaft, 42 band
Folded piece 38, buffer stopper 44 and stabilizer blade 47 in dynamic second fold mechanism 32 are together around the central axis of the 5th pin shaft 42 to transmission
Side oscillation in axis 29 and fold；Two first bevel gears 30 in second rotor mechanism 12 drive two second cone teeth respectively
Wheel 43 rotates；The second bevel gear 43 in the first fold mechanism 31 in second rotor mechanism 12 passes through corresponding 5th pin
Axis 42 drives folded piece 38, buffer stopper 44 and stabilizer blade 47 in the first fold mechanism 31 together around the central axis of the 5th pin shaft 42
The side oscillation into corresponding transmission shaft 29 and fold；The second cone in the second fold mechanism 32 in second rotor mechanism 12
Gear 43 drives folded piece 38, buffer stopper 44 and stabilizer blade 47 in the second fold mechanism 32 together by corresponding 5th pin shaft 42
Around the 5th pin shaft 42 central axis into corresponding transmission shaft 29 side oscillation and fold；To ensure that unmanned plane is flying
Windage during row is maximally reduced, and is extended its voyage and is increased its flying speed, and then improves the work of unmanned plane
Make efficiency.
When unmanned plane starts landing, run by the steering engine 5 on remote control control body 1；Steering engine 5 passes through driving gear
6 drive the second transmission gear 14 in the first transmission gear 7 and the first rotor mechanism 11 to reversely rotate；Due to the second rotor mechanism
Components in 12 are identical with the components in the first rotor mechanism 11, and the internal structure of the second rotor mechanism 12 with
The internal structure of first rotor mechanism 11 is symmetrical about the median plane of body 1, so the first transmission gear 7 drives the second gyroplane
The second transmission gear 14 in structure 12 reversely rotates；The direction of rotation of the second transmission gear 14 in first rotor mechanism 11 and the
The direction of rotation of the second transmission gear 14 in two rotor mechanisms 12 is opposite；Under the action of corresponding second transmission gear 14,
Cantilever 13 in first rotor mechanism 11 and the second rotor mechanism 12 is respectively along corresponding second pin shaft 9 to lower swing；First rotation
Cantilever 13 in wing mechanism 11 drives the swing rod in the first rotor mechanism 11 by corresponding axle sleeve 15, transmission shaft 29 and connecting rod 19
21 around corresponding third pin shaft 10 to lower swing；Cantilever 13 in second rotor mechanism 12 passes through corresponding axle sleeve 15, transmission shaft
29 and connecting rod 19 drive the swing rod 21 in the second rotor mechanism 12 around corresponding third pin shaft 10 to lower swing；Due to the first rotor
One closed parallel four is formed between mechanism 11 or axle sleeve 15, connecting rod 19, swing rod 21 and body 1 in the second rotor mechanism 12
Side shape, so the connecting rod in the first rotor mechanism 11 and the second rotor mechanism 12 when to lower swing, in the first rotor mechanism 11
19 and the second connecting rod 19 in rotor mechanism 12 it is in a vertical state always, to guarantee the first rotor mechanism 11 and the second gyroplane
The flight that propeller aircraft 33 in structure 12 is in a horizontal position always without influencing unmanned plane；First rotor mechanism 11 and second
When cantilever 13 in rotor mechanism 12 drives corresponding axle sleeve 15 to lower swing, axle sleeve 15 in the first rotor mechanism 11 and corresponding
Two third transmission gears 25 occur relative rotation；Axle sleeve 15 in second rotor mechanism 12 is driven with corresponding two thirds
Relative rotation occurs for gear 25；Axle sleeve 15 in first rotor mechanism 11 and the second rotor mechanism 12 drives corresponding third respectively
Transmission gear 25 is reversely rotated around the central axis of corresponding transmission shaft 29；Two third driving cogs in first rotor mechanism 11
Wheel 25 drives the first bevel gear 30 at 29 both ends of transmission shaft to reversely rotate by corresponding transmission shaft 29；Second rotor mechanism
Two third transmission gears 25 in 12 drive the first bevel gear 30 at 29 both ends of transmission shaft to occur by corresponding transmission shaft 29
It reversely rotates；Two first bevel gears 30 in first rotor mechanism 11 drive two second bevel gears 43 to occur reversely to revolve respectively
Turn；The second bevel gear 43 in the first fold mechanism 31 in first rotor mechanism 11 drives the by corresponding 5th pin shaft 42
Folded piece 38, buffer stopper 44 and stabilizer blade 47 in one fold mechanism 31 are together around the central axis of the 5th pin shaft 42 to transmission shaft 29
Interior side oscillation and fold；The second bevel gear 43 in the second fold mechanism 32 in first rotor mechanism 11 passes through corresponding
5th pin shaft 42 drives folded piece 38, buffer stopper 44 and stabilizer blade 47 in the second fold mechanism 32 together in the 5th pin shaft 42
Mandrel line is to the outer side oscillation of transmission shaft 29 and puts down；Two first bevel gears 30 in second rotor mechanism 12 drive two respectively
A second bevel gear 43 reversely rotates；The second bevel gear 43 in the first fold mechanism 31 in second rotor mechanism 12 is logical
Crossing corresponding 5th pin shaft 42 drives folded piece 38, buffer stopper 44 and stabilizer blade 47 in the first fold mechanism 31 together around the 5th pin
The central axis of axis 42 is to the outer side oscillation of corresponding transmission shaft 29 and puts down；The second fold mechanism in second rotor mechanism 12
Second bevel gear 43 in 32 drives folded piece 38, buffer stopper 44 in the second fold mechanism 32 by corresponding 5th pin shaft 42
It to the outer side oscillation of corresponding transmission shaft 29 and is put down around the central axis of the 5th pin shaft 42 together with stabilizer blade 47, is unmanned plane
Landing is ready.
When unmanned plane starts to land, the first fold mechanism 31 and the second fold mechanism 32 in the first rotor mechanism 11 are
It is put down completely, while the first fold mechanism 31 in the second rotor mechanism 12 and the second fold mechanism 32 are put down completely；
Stabilizer blade 47 in first rotor mechanism 11 and the second rotor mechanism 12 start with face contact and interact；The gravity of unmanned plane
Effect along corresponding sliding slot 41 so that slide respectively with four buffer stoppers 44 that four stabilizer blades 47 match；Four buffer springs 23
It is compressed simultaneously, so that the vertical landing for unmanned plane provides certain buffering, avoids the hard landing of unmanned plane, ensure that
Unmanned plane not will receive impact when landing and be damaged；If working as the not complete vertical landing of unmanned plane, have
When the speed of certain horizontal direction, ground has the impact of horizontal direction in face of unmanned plane；First in first rotor mechanism 11
The central axis of fold mechanism 31 and stabilizer blade 47 in the second fold mechanism 32 and the 6th pin shaft 48 around corresponding 6th pin shaft 48
It swings, deformation occurs and energy storage for the buffering leaf spring 24 in the first fold mechanism 31 and the second fold mechanism 32；Meanwhile first
The first fold mechanism 31 in rotor mechanism 11 and the buffering axle pad 49 at 48 both ends of the 6th pin shaft in the second fold mechanism 32 with
41 side wall of sliding slot generates extruding；Since buffering axle pad 49 has certain elasticity, so the buffering axle pad at 48 both ends of the 6th pin shaft
49 play buffer function to the impact of the horizontal direction of unmanned plane together with buffering leaf spring 24；Due to the second rotor mechanism 12
Internal structure and the internal structure of the first rotor mechanism 11 are symmetrical about the median plane of body 1, so in the second rotor mechanism 12
The first fold mechanism 31 and the second fold mechanism 32 occur similarly to move；The first fold mechanism in second rotor mechanism 12
31 and the second 48 both ends of the 6th pin shaft in fold mechanism 32 buffering axle pad 49 and buffering leaf spring 24 simultaneously to unmanned plane in water
Square identical buffer function is played to the impact being subject to, and then avoids unmanned plane in the speed with certain level direction
Impacted and be damaged when landing, to the maximum extent reduce therefore and caused by economic loss.
In conclusion beneficial effects of the present invention: the unmanned plane in the present invention only realizes the first rotation by a steering engine 5
The first fold mechanism 31 and the second fold mechanism 32 in wing mechanism 11 and the second rotor mechanism 12 stack；Land in unmanned plane
When, the first fold mechanism 31 and the second fold mechanism 32 in the first rotor mechanism 11 and the second rotor mechanism 12 are put down, and are nothing
Man-machine landing is ready；Meanwhile first rotor mechanism 11 and the first fold mechanism 31 in the second rotor mechanism 12 and
Two-fold mechanism 32 has certain pooling feature；Due to the rotation speed of the operative gear component in steering engine 5 during the work time
Degree is very high, if be easily damaged by impact；So the first folding in the first rotor mechanism 11 and the second rotor mechanism 12
Since ground faces the impact of stabilizer blade 47 when pooling feature in folded mechanism 31 and the second fold mechanism 32 avoids UAV Landing
Generation caused by and the phenomenon that the impact failure of the teeth of 5 high speed gear of steering engine, and then ensure that the driving on unmanned plane
Device is not damaged, so that the landing of unmanned plane is steady, extends the service life of unmanned plane to the maximum extent.
Claims (10)
1. a kind of with the quadrotor drone that can stack undercarriage, it is characterised in that: it include body, steering engine, the second pin shaft,
Third pin shaft, the first rotor mechanism, the second rotor mechanism, wherein body is existing quadrotor drone body；First rotor
Mechanism and the second rotor mechanism are symmetrically mounted at body two sides by corresponding second pin shaft and third pin shaft respectively；
Steering engine passes through dynamic first rotor mechanism of the driving gear band being mounted thereon and the second rotor mechanism synchronizes upper and lower swing；
When unmanned plane lift-off flight, steering engine drives the first rotor mechanism and the second rotor mechanism along corresponding second pin shaft and third pin shaft
It is swung up, while the first fold mechanism and the second fold mechanism folding receipts in the first rotor mechanism and the second rotor mechanism
It rises, to reduce the windage that unmanned plane is subject in flight course, and then improves unmanned plane during flying voyage and speed；Unmanned plane from
When airborne, steering engine drives the first rotor mechanism and the second rotor mechanism along corresponding second pin shaft and third pin shaft to the bottom
It is dynamic, while the first fold mechanism in the first rotor mechanism and the second rotor mechanism and the second fold mechanism put down expansion, for nothing
Man-machine landing is ready.
2. according to claim 1 a kind of with the quadrotor drone that can stack undercarriage, it is characterised in that: above-mentioned machine
It is opened up on body there are two the first loose slot, gear grooved, driver slot, the first loose slot of two of them is symmetrically distributed two in body
Side；Gear grooved is located on the upper surface of body, and gear grooved is communicated with two side end faces of body；Gear grooved and two first work
Dynamic slot laterally communicates；Driver slot is located on the upper surface of body, and driver slot is laterally communicated with gear grooved；Driver slot and two
One loose slot is located at the two sides of gear grooved.
3. according to claim 2 a kind of with the quadrotor drone that can stack undercarriage, it is characterised in that: above-mentioned rudder
Machine is mounted in the driver slot on body, and steering engine is electrically connected with the flight control system being installed on body；The output shaft of steering engine
Shaft end is equipped with driving gear, and gear is driven to be located in the gear grooved on body；First transmission gear is pacified by the first pin shaft
In the gear grooved on body, and the first transmission gear is meshed with driving gear.
4. according to claim 2 a kind of with the quadrotor drone that can stack undercarriage, it is characterised in that: above-mentioned
One rotor mechanism includes cantilever, the second transmission gear, axle sleeve, crossbeam, connecting rod, the 4th pin shaft, swing rod, third transmission gear, determines
Position block, transmission shaft, first bevel gear, the first fold mechanism, the second fold mechanism, wherein one end of cantilever offers pin hole, the
Pin hole is offered on the end face of two transmission gears；Second transmission gear is by offering the one of pin hole on one end face and cantilever
End is connected, and the pin hole on the second transmission gear is docked with the pin hole on cantilever；One end of pin hole is offered on cantilever together with
In first loose slot that two transmission gears are mounted on body by the second pin shaft；Second transmission gear and driving gear phase
Engagement；The first revolution axis hole is offered at the end face center of axle sleeve；One is offered along circumferential direction at the periphery center of axle sleeve
Determine the second loose slot of radian, and the second loose slot is communicated with the first revolution axis hole；The both ends of the periphery of axle sleeve are respectively along week
To the flank of tooth for offering 360 degree of radians；Axle sleeve is connected by not offering one end of pin hole at its periphery center and on cantilever,
And the centerline axis parallel of the central axis of axle sleeve and the second transmission gear；The second loose slot on axle sleeve is located under cantilever
Side；Crossbeam is installed in axle sleeve by the bearing fit of its periphery and the first revolution axis hole, and axle sleeve is located at the center of crossbeam
Place；One end of connecting rod offers pin hole, do not offered on connecting rod pin hole one end pass vertically through from bottom to up on axle sleeve
Single-revolution axis hole and crossbeam are connected；The both ends of swing rod have a pin hole；It is offered on the end face of one end of swing rod hinged
Notch, and hinged notch is communicated with the pin hole for being located at this end on swing rod；Pacified by the 4th pin shaft one end that pin hole is provided on connecting rod
In hinged notch on swing rod；The one end not connecting with connecting rod on swing rod is mounted on first on body by third pin shaft
In loose slot, and the position that connect with body of swing rod is located at the lower section of cantilever；Body, cantilever, connecting rod and swing rod form one and put down
Row quadrangle；The both ends of crossbeam are separately installed with the first fold mechanism and the second fold mechanism；It is offered on the end face of locating piece
First fixed shaft hole and the second revolution axis hole；Two locating pieces are fixedly mounted on crossbeam each by the first fixed shaft hole thereon
On, and two locating pieces are symmetrically distributed in the two sides of axle sleeve；Transmission shaft passes through second on its periphery and two locating pieces
The bearing fit of revolution axis hole is mounted on two locating pieces；Two third transmission gears are mounted on transmission shaft, and two
Three transmission gears are meshed with the flank of tooth at axle sleeve both ends respectively；Cooperate between third transmission gear and transmission shaft for key；Two
One bevel gear is separately mounted to the both ends of transmission shaft, and two first bevel gears respectively with the first fold mechanism and the second folding machine
Structure matches.
5. according to claim 3 a kind of with the quadrotor drone that can stack undercarriage, it is characterised in that: above-mentioned
One fold mechanism includes propeller aircraft, motor, fixing seat, folded piece, the second fixed shaft hole, third loose slot, sliding slot, the 5th
Pin shaft, second bevel gear, buffer stopper, dashpot, the 4th revolution axis hole, stabilizer blade, the 6th pin shaft, buffering axle pad, sliding block, buffering elastic
Spring, buffering leaf spring, are wherein provided with folded slot, and folded slot is communicated with a side end face of fixing seat on the lower end surface of fixing seat；
Third revolution axis hole is provided on one side end face of fixing seat, and third revolution axis hole is communicated with folded slot；In fixing seat with folding
One end of side end face and transmission shaft that folded slot communicates is connected；Motor is installed on the upper surface of fixing seat；The output shaft axis of motor
End is equipped with propeller aircraft；Winged control subsystem on motor and body is electrically connected；Third is provided on the lower end surface of folded piece
Loose slot, and third loose slot is communicated with two opposite side end faces on folded piece；It is not communicated with third loose slot on folded piece
Two opposite side end faces between be provided with the second fixed shaft hole of perforation, and the second fixed shaft hole is located at the upper of third loose slot
Side；Sliding slot there are two symmetrically being opened along the vertical direction on two sides of third loose slot；The second fixing axle is provided on folded piece
The one end in hole is mounted in the folded slot in fixing seat by the 5th pin shaft；The third that 5th pin shaft one end is stretched out in fixing seat is returned
Shaft hole；Second bevel gear is mounted on one end that third revolution axis hole is stretched out on the 5th pin shaft；In second bevel gear and transmission shaft
First bevel gear positioned at herein is meshed；Dashpot is offered on the lower end surface of buffer stopper, and on dashpot and buffer stopper
Two opposite side end faces communicate；The two side end faces lower end not communicated with dashpot on buffer stopper is provided with the 4th rotating shaft of perforation
Hole；It symmetrically installs there are two sliding block the upper end for two side end faces not communicated with dashpot on buffer stopper；Buffer stopper passes through two
In the third loose slot of a sliding block and two sliding slots being slidably installed on folded piece；Two of the upper end of stabilizer blade are opposite
Axis hole is offered between side end face；Stabilizer blade is mounted in the dashpot on buffer stopper by the 6th pin shaft；The both ends of 6th pin shaft
The 4th revolution axis hole for being each passed through dashpot two sides enters in two on folded piece sliding slots；The outer circle at the both ends of the 6th pin shaft
Circumferentially equably there are two buffer axle pad for installation respectively on face；It is mounted on two buffering axle pads at the 6th every end of pin shaft and corresponding
Sliding slot match；Buffer spring is located in the third loose slot on folded piece；Three loose slots of upper end and ground of buffer spring
The upper surface of inner wall connection, lower end and buffer stopper connects；Buffering leaf spring one end and communicated on buffer stopper with dashpot one
Side end face connection, the other end are connect with a side end face for not opening up axis hole on stabilizer blade.
6. according to claim 5 a kind of with the quadrotor drone that can stack undercarriage, it is characterised in that: above-mentioned
Components in two-fold mechanism are identical with the components in the first fold mechanism；The internal structure of second fold mechanism with
The internal structure of first fold mechanism is symmetrical about the median plane of the crossbeam in rotor mechanism；Fixation in second this fold mechanism
The other end of crossbeam in the side end face communicated on seat with folded slot and the first rotor mechanism is connected.
7. according to claim 5 a kind of with the quadrotor drone that can stack undercarriage, it is characterised in that: above-mentioned
Two rotor mechanisms are mounted in another first loose slot on body；Components and the first gyroplane in second rotor mechanism
Components in structure are identical, and the internal structure of the second rotor mechanism and the internal structure of the first rotor mechanism are about machine
The median plane of body is symmetrical；The second transmission gear in second rotor mechanism is meshed with the first transmission gear in gear grooved；The
The winged control subsystem on two motors and body in two rotor mechanisms is electrically connected.
8. according to claim 4 a kind of with the quadrotor drone that can stack undercarriage, it is characterised in that: above-mentioned
The transmission ratio of two transmission gears and driving gear is 1:1.
9. according to claim 8 a kind of with the quadrotor drone that can stack undercarriage, it is characterised in that: above-mentioned
The transmission ratio that the periphery of teeth is offered on three transmission gears and axle sleeve is 1:1.
10. according to claim 9 a kind of with the quadrotor drone that can stack undercarriage, it is characterised in that: above-mentioned
The transmission ratio of first bevel gear and second bevel gear is 1:1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811308174.9A CN109305331A (en) | 2018-11-05 | 2018-11-05 | It is a kind of with the quadrotor drone that can stack undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811308174.9A CN109305331A (en) | 2018-11-05 | 2018-11-05 | It is a kind of with the quadrotor drone that can stack undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109305331A true CN109305331A (en) | 2019-02-05 |
Family
ID=65222786
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811308174.9A Withdrawn CN109305331A (en) | 2018-11-05 | 2018-11-05 | It is a kind of with the quadrotor drone that can stack undercarriage |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104192A (en) * | 2019-05-14 | 2019-08-09 | 深圳市智旋科技有限公司 | A kind of 3D light show unmanned plane device and application method |
| CN110406666A (en) * | 2019-07-29 | 2019-11-05 | 南京精微迅智能科技有限公司 | A kind of buffering is landed anti-rebound unmanned plane and its anti-rebound method of buffering |
| CN111003161A (en) * | 2019-12-26 | 2020-04-14 | 穆芳玲 | Intelligent retraction device and method for unmanned aerial vehicle foot stand |
| CN111038719A (en) * | 2019-12-31 | 2020-04-21 | 罗嘉宇 | Many rotors plant protection unmanned aerial vehicle undercarriage |
| CN113602494A (en) * | 2021-08-10 | 2021-11-05 | 安徽智天智慧科技有限公司 | Can replace functional module's agricultural plant protection unmanned aerial vehicle |
| CN113928535A (en) * | 2021-10-08 | 2022-01-14 | 中科信同科技集团有限公司 | Folding arm of unmanned aerial vehicle and unmanned aerial vehicle |
-
2018
- 2018-11-05 CN CN201811308174.9A patent/CN109305331A/en not_active Withdrawn
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104192A (en) * | 2019-05-14 | 2019-08-09 | 深圳市智旋科技有限公司 | A kind of 3D light show unmanned plane device and application method |
| CN110406666A (en) * | 2019-07-29 | 2019-11-05 | 南京精微迅智能科技有限公司 | A kind of buffering is landed anti-rebound unmanned plane and its anti-rebound method of buffering |
| CN111003161A (en) * | 2019-12-26 | 2020-04-14 | 穆芳玲 | Intelligent retraction device and method for unmanned aerial vehicle foot stand |
| CN111038719A (en) * | 2019-12-31 | 2020-04-21 | 罗嘉宇 | Many rotors plant protection unmanned aerial vehicle undercarriage |
| CN111038719B (en) * | 2019-12-31 | 2021-08-06 | 汉中万利航空装备制造有限公司 | Many rotors plant protection unmanned aerial vehicle undercarriage |
| CN113602494A (en) * | 2021-08-10 | 2021-11-05 | 安徽智天智慧科技有限公司 | Can replace functional module's agricultural plant protection unmanned aerial vehicle |
| CN113928535A (en) * | 2021-10-08 | 2022-01-14 | 中科信同科技集团有限公司 | Folding arm of unmanned aerial vehicle and unmanned aerial vehicle |
| CN113928535B (en) * | 2021-10-08 | 2024-05-28 | 中科信同科技集团有限公司 | Unmanned aerial vehicle folding arm and unmanned aerial vehicle |
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Application publication date: 20190205 |
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