CN203652106U - Multi-axis aerial vehicle - Google Patents
Multi-axis aerial vehicle Download PDFInfo
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- CN203652106U CN203652106U CN201420040783.1U CN201420040783U CN203652106U CN 203652106 U CN203652106 U CN 203652106U CN 201420040783 U CN201420040783 U CN 201420040783U CN 203652106 U CN203652106 U CN 203652106U
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- synchronizer gear
- main shaft
- motor
- gear
- side lever
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Abstract
The utility model discloses a multi-axis aerial vehicle. The multi-axis aerial vehicle comprises a support and a driving system arranged on the support, wherein the driving system comprises a motor and a plurality of rotor wings, the motor drives the rotor wings to rotate simultaneously by a synchronous transmission device, and the synchronous transmission device comprises a gear. The unmanned aerial vehicle is provided with one motor which drives all rotor wings to rotate simultaneously, as only one motor is arranged, the cost is low and the weight is light; compared with high-frequency vibration produced by a plurality of motors, high-frequency vibration produced by one motor has little influence on the aerial shooting definition; and besides, one motor drives all rotor wings to rotate simultaneously, the synchronism is easy to control.
Description
Technical field
The application belongs to the field of taking photo by plane, and particularly relates to a kind of Multi-axis aircraft.
Background technology
Unmanned vehicle has that volume is little, lightweight, expense is low, flexible operation and safe feature, can be widely used in taking photo by plane, monitors, the field such as search and rescue, resource exploration.
Prior art scheme be by each screw propeller separately with electric motor driven, aviation brushless motor is because its principle of work causes allowing the rotating speed of all motors be consistent, and existing manufacturing process makes the speed difference of each motor larger.In existing technical scheme, if whole motor speed is consistent or difference is very little, all kinds of Flight Control Softwares that are very beneficial for current use are controlled it, and now the efficiency of complete machine is the highest.If the speed difference of each motor is very large, will increase the weight of the burden of Flight Control Software, because it will allow a sky, be born with very unsettled flying platform keeps stable.Also can fly although it is so, if but coordinate various maneuver, fly control and will carry out each motor speed control very frequently, accelerate the power consumption speed of complete machine.
Utility model content
The purpose of this utility model provides a kind of unmanned vehicle, solve in prior art unmanned vehicle weight large, take photo by plane unintelligible, power consumption fast and rotor synchronism problem rambunctious.
For achieving the above object, the utility model provides following technical scheme:
The application provides a kind of Multi-axis aircraft, comprises support and is installed on the drive system on described support, and described drive system comprises:
One motor;
Multiple rotors, described motor drives described multiple rotor synchronously to rotate by synchronous drive mechanism, and described synchronous drive mechanism comprises gear.
Preferably, in above-mentioned Multi-axis aircraft, described synchronous drive mechanism comprises and can be driven the main shaft rotating by described motor, described multiple rotor is symmetrically distributed in the both sides of described main shaft, between described main shaft and each rotor, be connected with respectively the first transmission device, between described main shaft and motor, be connected with the second transmission device.
Preferably, in above-mentioned Multi-axis aircraft, described the first transmission device is synchrodrive belt, on described main shaft and rotor, be fixed with respectively the first synchronizer gear and the second synchronizer gear, the two ends of described synchrodrive belt are sheathed on respectively on described the first synchronizer gear and the second synchronizer gear, the inside face of described synchrodrive belt is provided with teeth groove, and the outside face of described the first synchronizer gear and the second synchronizer gear is respectively equipped with the teeth groove being meshed with described synchrodrive belt inside face.
Preferably, in above-mentioned Multi-axis aircraft, described the first transmission device is synchrodrive axle, the two ends of described synchrodrive axle are fixed with respectively the 3rd synchronizer gear and the 4th synchronizer gear, on described main shaft and rotor, be fixed with respectively the 5th synchronizer gear and the 6th synchronizer gear, described the 3rd synchronizer gear and the 6th synchronizer gear surface are provided with the teeth groove being meshed, and described the 4th synchronizer gear and the 5th synchronizer gear surface are provided with the teeth groove being meshed.
Preferably, in above-mentioned Multi-axis aircraft, described the second transmission device comprises the 7th synchronizer gear and the 8th synchronizer gear, described the 7th synchronizer gear is fixed on the output shaft of described motor, described the 8th synchronizer gear is fixed on described main shaft, and described the 7th synchronizer gear and the 8th synchronizer gear are provided with the teeth groove being meshed.
Preferably, in above-mentioned Multi-axis aircraft, described the second transmission device comprises the 9th synchronizer gear, the tenth synchronizer gear and synchronous drive belt, described the 9th synchronizer gear is fixed on the output shaft of described motor, described the tenth synchronizer gear is fixed on described main shaft, the two ends of described synchronous drive belt are sheathed on respectively on described the 9th synchronizer gear and the tenth synchronizer gear, the inside face of described synchronous drive belt is provided with teeth groove, the outside face of described the 9th synchronizer gear and the tenth synchronizer gear is respectively equipped with the teeth groove being meshed with described synchronous drive belt inside face.
Preferably, in above-mentioned Multi-axis aircraft, described support comprises the first side lever and the second side lever that be arranged in parallel, and be fixed on the mobile jib between described the first side lever and the second side lever, the two ends of described mobile jib are individually fixed in the middle part of described the first side lever and the second side lever, described drive system comprises four rotors, and these four rotors are installed on respectively four ends of described the first side lever and the second side lever.
Preferably, in above-mentioned Multi-axis aircraft, described main shaft is located in described mobile jib.
Compared with prior art, the utility model has the advantage of: Multi-axis aircraft of the present utility model is provided with a motor, and drive all rotors synchronously to rotate by this motor, due to a motor being only set, cost is low, lightweight; And with respect to multiple motors, the high-frequency vibration that motor produces obtains larger weakening to the impact of the visibility of taking photo by plane; In addition, drive all rotors to rotate by a motor, each rotor synchronism is almost in full accord simultaneously.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present application or technical scheme of the prior art, to the accompanying drawing of required use in embodiment or description of the Prior Art be briefly described below, apparently, the accompanying drawing the following describes is only some embodiment that record in the application, for those of ordinary skills, do not paying under the prerequisite of creative work, can also obtain according to these accompanying drawings other accompanying drawing.
Figure 1 shows that the schematic perspective view of unmanned vehicle in the utility model the first embodiment;
Figure 2 shows that the exploded perspective view of unmanned vehicle in the utility model the first embodiment;
Figure 3 shows that the exploded perspective view of unmanned vehicle in the utility model the second embodiment;
Figure 4 shows that the exploded perspective view of unmanned vehicle in the utility model the 3rd embodiment.
The specific embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is described in detail, obviously, described embodiment is only the utility model part embodiment, rather than whole embodiment.Based on the embodiment in the utility model, the every other embodiment that those of ordinary skills obtain under the prerequisite of not making creative work, belongs to the scope that the utility model is protected.
Embodiment 1
Shown in ginseng Fig. 1 and Fig. 2, in the utility model the first embodiment, Multi-axis aircraft comprises support 10 and is installed on the drive system 20 on support.
Support comprises that the first side lever 11 and the second side lever 12, the first side levers 11 that be arranged in parallel are two hollow round bars that length is identical, diameter is identical with the second side lever 12.Between the first side lever 11 and the second side lever 12, be fixed with mobile jib 13, mobile jib 13 is a hollow round bar, and its two ends are individually fixed in the midway location of the first side lever 11 and the second side lever 12, and mobile jib 13 is preferably perpendicular to the first side lever 11 and the second side lever 12.
In other embodiments, mobile jib 13 also can be not orthogonal to the first side lever 11 and the second side lever 12.The material of the first side lever 11, the second side lever 12 and mobile jib is preferably carbon fiber, is easy to expect, under the prerequisite that meets support strength, the first side lever 11, the second side lever 12 and mobile jib 13 can adopt other materials, more gently better.
Above-mentioned support, owing to only adopting three round bars to be fixed, simple in structure, and the maximized weight that reduced.
The utility model exports propulsive effort to main shaft by a motor, and controls the rotation of main shaft, and main shaft further outputs power to four rotors by four synchrodrive belts.Can expect thus, the technical solution of the utility model goes for having the aircraft of other quantity rotors equally, can be according to the quantity of rotor on main shaft, correspondence is provided with the synchronizer gear of similar number, for example: can increase by two synchronizer gears at the middle part of main shaft, simultaneously, the medium position of mobile jib can vertically be fixed a round bar, the two ends of this round bar are rotated respectively a rotor are set, and so, main shaft can drive six rotors synchronously to rotate simultaneously.
In sum, Multi-axis aircraft of the present utility model is provided with a motor, and drives all rotors synchronously to rotate by this motor, and tool has the following advantages:
1, flight control system need not be again in order to control the attitude of complete machine and action and frequently change the rotating speed of each motor, the power consumption of having saved complete machine, has postponed cruise duration;
2, reduced the performance requriements to flying to control software, make Multi-axis aircraft fly control software development and use cost and reduce a lot;
3, single motor-driven displacement Multi-axis aircraft cost in the time occurring such as crash is low, prior art scheme is that each motor is by the each screw propeller of hard connection, once the screw propeller that crashes because high rotating speed inertia is encountered any object and at once damaged, can further damage and hardwired each motor of screw propeller, the cost of the spare and accessory parts that complete machine is changed in repair process like this will increase greatly simultaneously
In addition, in the utility model embodiment, part adopts the mode of gear drive, adopts the accurate efficiency of gear high, can the large torsion of the large load of transmission, and also the life-span is high.
Shown in ginseng Fig. 3, in the utility model the second embodiment, between main shaft and rotor, be provided with synchrodrive axle 30, synchrodrive axle 30 is a round bar, its two ends are fixed with respectively the 3rd synchronizer gear 31 and the 4th synchronizer gear 32, are fixed with the 5th synchronizer gear 33 on main shaft, and the below of rotor is fixed with the 6th synchronizer gear 34, the 3rd synchronizer gear 31 and the 6th synchronizer gear 34 surfaces are provided with the teeth groove being meshed, and the 4th synchronizer gear 32 and the 5th synchronizer gear 33 surfaces are provided with the teeth groove being meshed.The 5th synchronizer gear 33 can drive two the 4th synchronizer gears 32 that are positioned at its both sides to rotate simultaneously.
In the present embodiment, other structures are identical with the first embodiment, repeat no more.Compared with the first embodiment, the second embodiment has adopted all gear type of drive.
Embodiment 3
Shown in ginseng Fig. 4, in the utility model the 3rd embodiment, between motor and main shaft, be provided with the 9th synchronizer gear 41, the tenth synchronizer gear 42 and synchronous drive belt 43.Wherein, the 9th synchronizer gear 41 is fixed on the output shaft of motor, the tenth synchronizer gear 42 is fixed on main shaft, the two ends of synchronous drive belt 43 are sheathed on respectively the outside of the 9th synchronizer gear 41 and the tenth synchronizer gear 42, the inside face of synchronous drive belt 43 is provided with teeth groove, and the outside face of the 9th synchronizer gear 41 and the tenth synchronizer gear 42 is respectively equipped with the teeth groove being meshed with synchronous drive belt 43 inside faces.
Electric machine rotation can directly drive the 9th synchronizer gear 41 to rotate, and the 9th synchronizer gear 41 drives the tenth synchronizer gear 42 to rotate by synchronous drive belt 43, and the tenth synchronizer gear 42 rotates and then can drive main shaft to rotate.
Between main shaft and rotor, be provided with synchrodrive axle, its structure and start principle thereof are identical with embodiment 2, and the present embodiment repeats no more.
It should be noted that, in this article, relational terms such as the first and second grades is only used for an entity or operation to separate with another entity or operational zone, and not necessarily requires or imply and between these entities or operation, have the relation of any this reality or sequentially.And, term " comprises ", " comprising " or its any other variant are intended to contain comprising of nonexcludability, thereby the process, method, article or the equipment that make to comprise a series of key elements not only comprise those key elements, but also comprise other key elements of clearly not listing, or be also included as the intrinsic key element of this process, method, article or equipment.The in the situation that of more restrictions not, the key element being limited by statement " comprising ... ", and be not precluded within process, method, article or the equipment that comprises described key element and also have other identical element.
The above is only the application's the specific embodiment; it should be pointed out that for those skilled in the art, do not departing under the prerequisite of the application's principle; can also make some improvements and modifications, these improvements and modifications also should be considered as the application's protection domain.
Claims (8)
1. a Multi-axis aircraft, is characterized in that, comprises support and is installed on the drive system on described support, and described drive system comprises:
One motor;
Multiple rotors, described motor drives described multiple rotor synchronously to rotate by synchronous drive mechanism, and described synchronous drive mechanism comprises gear.
2. Multi-axis aircraft according to claim 1, it is characterized in that: described synchronous drive mechanism comprises and can be driven the main shaft rotating by described motor, described multiple rotor is symmetrically distributed in the both sides of described main shaft, between described main shaft and each rotor, be connected with respectively the first transmission device, between described main shaft and motor, be connected with the second transmission device.
3. Multi-axis aircraft according to claim 2, it is characterized in that: described the first transmission device is synchrodrive belt, on described main shaft and rotor, be fixed with respectively the first synchronizer gear and the second synchronizer gear, the two ends of described synchrodrive belt are sheathed on respectively on described the first synchronizer gear and the second synchronizer gear, the inside face of described synchrodrive belt is provided with teeth groove, and the outside face of described the first synchronizer gear and the second synchronizer gear is respectively equipped with the teeth groove being meshed with described synchrodrive belt inside face.
4. Multi-axis aircraft according to claim 2, it is characterized in that: described the first transmission device is synchrodrive axle, the two ends of described synchrodrive axle are fixed with respectively the 3rd synchronizer gear and the 4th synchronizer gear, on described main shaft and rotor, be fixed with respectively the 5th synchronizer gear and the 6th synchronizer gear, described the 3rd synchronizer gear and the 6th synchronizer gear surface are provided with the teeth groove being meshed, and described the 4th synchronizer gear and the 5th synchronizer gear surface are provided with the teeth groove being meshed.
5. Multi-axis aircraft according to claim 2, it is characterized in that: described the second transmission device comprises the 7th synchronizer gear and the 8th synchronizer gear, described the 7th synchronizer gear is fixed on the output shaft of described motor, described the 8th synchronizer gear is fixed on described main shaft, and described the 7th synchronizer gear and the 8th synchronizer gear are provided with the teeth groove being meshed.
6. Multi-axis aircraft according to claim 2, it is characterized in that: described the second transmission device comprises the 9th synchronizer gear, the tenth synchronizer gear and synchronous drive belt, described the 9th synchronizer gear is fixed on the output shaft of described motor, described the tenth synchronizer gear is fixed on described main shaft, the two ends of described synchronous drive belt are sheathed on respectively on described the 9th synchronizer gear and the tenth synchronizer gear, the inside face of described synchronous drive belt is provided with teeth groove, the outside face of described the 9th synchronizer gear and the tenth synchronizer gear is respectively equipped with the teeth groove being meshed with described synchronous drive belt inside face.
7. Multi-axis aircraft according to claim 2, it is characterized in that: described support comprises the first side lever and the second side lever that be arranged in parallel, and be fixed on the mobile jib between described the first side lever and the second side lever, the two ends of described mobile jib are individually fixed in the middle part of described the first side lever and the second side lever, described drive system comprises four rotors, and these four rotors are installed on respectively four ends of described the first side lever and the second side lever.
8. Multi-axis aircraft according to claim 7, is characterized in that: described main shaft is located in described mobile jib.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420040783.1U CN203652106U (en) | 2014-01-23 | 2014-01-23 | Multi-axis aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420040783.1U CN203652106U (en) | 2014-01-23 | 2014-01-23 | Multi-axis aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN203652106U true CN203652106U (en) | 2014-06-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420040783.1U Expired - Fee Related CN203652106U (en) | 2014-01-23 | 2014-01-23 | Multi-axis aerial vehicle |
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| CN (1) | CN203652106U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103754359A (en) * | 2014-01-23 | 2014-04-30 | 江苏艾锐泰克无人飞行器科技有限公司 | Multi-axial aircraft |
| CN104709464A (en) * | 2015-03-12 | 2015-06-17 | 江苏艾锐泰克无人飞行器科技有限公司 | Motor mounting seat, reinforcing part and multi-rotor unmanned aerial vehicle |
| CN104760696A (en) * | 2015-04-22 | 2015-07-08 | 深圳市艾特航空科技股份有限公司 | Multi-rotor aircraft |
| CN105752331A (en) * | 2016-04-26 | 2016-07-13 | 北京理工大学 | Single-internal combustion engine power multi-rotor wing unmanned aerial vehicle based on variable pitch control |
-
2014
- 2014-01-23 CN CN201420040783.1U patent/CN203652106U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103754359A (en) * | 2014-01-23 | 2014-04-30 | 江苏艾锐泰克无人飞行器科技有限公司 | Multi-axial aircraft |
| CN104709464A (en) * | 2015-03-12 | 2015-06-17 | 江苏艾锐泰克无人飞行器科技有限公司 | Motor mounting seat, reinforcing part and multi-rotor unmanned aerial vehicle |
| CN104760696A (en) * | 2015-04-22 | 2015-07-08 | 深圳市艾特航空科技股份有限公司 | Multi-rotor aircraft |
| CN104760696B (en) * | 2015-04-22 | 2016-07-27 | 深圳市艾特航空科技股份有限公司 | A kind of multi-rotor aerocraft |
| CN105752331A (en) * | 2016-04-26 | 2016-07-13 | 北京理工大学 | Single-internal combustion engine power multi-rotor wing unmanned aerial vehicle based on variable pitch control |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20161219 Address after: 510030 Yuexiu District, Guangzhou, Jiefang South Road, No. 3712, room 39, Guangzhou flying over the Model Co., Ltd. Patentee after: Guangzhou flying model Co., Ltd. Address before: Suzhou City, Jiangsu Province, Zhangjiagang free trade zone 215635 emerging industry incubation center building A room 210A Jiangsu AI retech UAV Technology Co. Ltd. Patentee before: Ai Rui Tyke, Jiangsu unmanned vehicle Science and Technology Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140618 Termination date: 20180123 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |