CN206494122U - Aircraft power mechanism and multi-rotor unmanned aerial vehicle - Google Patents
Aircraft power mechanism and multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN206494122U CN206494122U CN201720187492.9U CN201720187492U CN206494122U CN 206494122 U CN206494122 U CN 206494122U CN 201720187492 U CN201720187492 U CN 201720187492U CN 206494122 U CN206494122 U CN 206494122U
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- rotor
- fuel engines
- electric motor
- aircraft power
- power mechanism
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Abstract
The utility model is related to unmanned air vehicle technique field, more particularly, to a kind of aircraft power mechanism and multi-rotor unmanned aerial vehicle.The aircraft power mechanism that the utility model is provided includes：Rotor, rotor shaft, electric motor assembly and fuel engines component；One end of rotor shaft is fixedly connected with rotor, and the other end is used to be connected with the cabin of multi-rotor unmanned aerial vehicle；Electric motor assembly is connected with fuel engines component with rotor shaft, to drive rotor shaft to rotate.Fuel engines component drives rotor shaft rotation with electric motor assembly simultaneously, fuel engines component consumption oil, electric motor assembly consumes electric energy, that is, using the electric mixed form of oil as power, while driving rotor work using chemical energy and electric energy, the rotating speed of fuel engines output is higher, so as to make the cruising time length, voyage length, load of multi-rotor unmanned aerial vehicle high, while can ensure stabilized flight and safe falling in the case of a component failures wherein, security is preferable.
Description
Technical field
The utility model is related to unmanned air vehicle technique field, more particularly, to a kind of aircraft power mechanism and many rotors nobody
Machine.
Background technology
Multi-rotor unmanned aerial vehicle is a kind of many rotors of special pilotless helicopter with three and above rotor shaft without
Man-machine, it drives rotor, so as to produce a liter thrust by the motor rotation on each axle.Rotor always away from fixation, rather than
General helicopter is variable like that.By changing the relative rotation speed between different rotors, thus it is possible to vary the size of single shaft propulsive force, from
And control the running orbit of aircraft.With the continuous development of scientific technology, multi-rotor unmanned aerial vehicle is due to use easy to use
Feature is applied to increasing industry.
But, rotation is driven because the rotor shaft of multi-rotor unmanned aerial vehicle in the prior art passes through motor, motor needs
It is powered, exported so as to convert electrical energy into mechanical energy to rotor shaft, while the rotating speed of motor is relatively low, so as to cause many rotations
Cruising time of wing unmanned plane is few, voyage is short, load is low and security is poor.
Utility model content
The purpose of this utility model is to provide a kind of aircraft power mechanism and multi-rotor unmanned aerial vehicle, to solve existing skill
Cruising time of multi-rotor unmanned aerial vehicle present in art is few, voyage is short, load is low and the poor technical problem of security.
A kind of aircraft power mechanism that the utility model is provided, the aircraft power mechanism includes：Rotor, rotor
Axle, electric motor assembly and fuel engines component；One end of the rotor shaft is fixedly connected with the rotor, and the other end is used for
It is connected with the cabin of multi-rotor unmanned aerial vehicle；The electric motor assembly is driven with the fuel engines component with the rotor shaft
Connection, to drive the rotor shaft to rotate.
Further, the rotor shaft include being removably secured successively the first connecting shaft of connection, the second connecting shaft and
3rd connecting shaft；The fuel engines component is connected with first connecting shaft；The electric motor assembly and described the
Two connecting shafts are connected；The rotor is connected with the 3rd connecting shaft.
Further, the fuel engines component is connected including fuel engines and with the fuel engines
First reducing gear；The fuel engines is connected by first reducing gear and the rotor shaft.
Further, the fuel engines component also includes engine controller；The engine controller with it is described
Fuel engines is electrically connected, the rotating speed for controlling the fuel engines.
Further, the electric motor assembly includes motor and the second reductor being connected with the electric-motor drive
Structure；The motor is connected by second reducing gear and the rotor shaft.
Further, the electric motor assembly also includes motor controller；The motor controller with it is described electronic
Mechatronics, the rotating speed for controlling the motor.
Further, the aircraft power mechanism also includes steering wheel；The steering wheel is connected with the rotor, for controlling
The pitch of the rotor.
Further, the utility model also provides a kind of multi-rotor unmanned aerial vehicle, the multi-rotor unmanned aerial vehicle include cabin with
And it is multiple such as aircraft power mechanism described in the utility model；Multiple rotor shafts are connected with the cabin.
Further, the aircraft power mechanism is four；The upper surface of the cabin is connected with I-shaped branch
Brace；Four aircraft power mechanisms are connected at the corner of the support arm.
Further, the multi-rotor unmanned aerial vehicle also includes the control system being arranged in the cabin；The motor
Component, the fuel engines component are electrically connected with the control system；The control system is used to control the motor
Component and the fuel engines component operation.
The aircraft power mechanism that the utility model is provided, when the cabin of the actuating unit and multi-rotor unmanned aerial vehicle is connected
When, fuel engines component drives rotor shaft rotation with electric motor assembly simultaneously, and rotor shaft drives rotor rotational, so as to produce liter
Thrust.
The aircraft power mechanism that the utility model is provided, fuel engines component drives rotor simultaneously with electric motor assembly
Axle rotates, fuel engines component consumption oil, electric motor assembly consumption electric energy, that is, using the electric mixed form of oil as power,
Drive rotor work using chemical energy and electric energy simultaneously, the rotating speed of fuel engines output is higher, so as to make many rotors nobody
The cruising time length of machine, voyage length, load are high, while can ensure stabilized flight in the case of a component failures wherein
And safe falling, security is preferable.
Brief description of the drawings
, below will be right in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art
The accompanying drawing used required in embodiment or description of the prior art is briefly described, it should be apparent that, describe below
In accompanying drawing be some embodiments of the present utility model, for those of ordinary skill in the art, do not paying creativeness
On the premise of work, other accompanying drawings can also be obtained according to these accompanying drawings.
The structural representation for the aircraft power mechanism that Fig. 1 provides for the utility model embodiment；
The structural representation for the multi-rotor unmanned aerial vehicle that Fig. 2 provides for the utility model embodiment；
Fig. 3 be Fig. 2 shown in multi-rotor unmanned aerial vehicle in cabin and support arm structural representation；
Another structural representation for the multi-rotor unmanned aerial vehicle that Fig. 4 provides for the utility model embodiment；
The another structural representation for the multi-rotor unmanned aerial vehicle that Fig. 5 provides for the utility model embodiment.
Reference：
1- rotors；2- rotor shafts；3- electric motor assemblies；
4- fuel engines components；5- steering wheels；6- cabins；
7- support arms；8- undercarriages；9- control systems；
The connecting shafts of 21- first；The connecting shafts of 22- second；The connecting shafts of 23- the 3rd；
24- shaft couplings；31- motor；The reducing gears of 32- second；
33- motor controllers；41- fuel engines；The reducing gears of 42- first；
43- engine controllers.
Embodiment
The technical solution of the utility model is clearly and completely described below in conjunction with accompanying drawing, it is clear that described
Embodiment is a part of embodiment of the utility model, rather than whole embodiments.Based on the embodiment in the utility model, sheet
The every other embodiment that field those of ordinary skill is obtained under the premise of creative work is not made, belongs to this practicality
Novel protected scope.
, it is necessary to explanation in description of the present utility model, term " " center ", " on ", " under ", it is "left", "right", " perpendicular
Directly ", the orientation or position relationship of the instruction such as " level ", " interior ", " outer " are, based on orientation shown in the drawings or position relationship, to be only
Described for the ease of description the utility model and simplifying, rather than to indicate or imply that signified device or element must have specific
Orientation, with specific azimuth configuration and operation, therefore it is not intended that to limitation of the present utility model.In addition, term " the
One ", " second ", " the 3rd " are only used for describing purpose, and it is not intended that indicating or implying relative importance.
, it is necessary to which explanation, unless otherwise clearly defined and limited, term " are pacified in description of the present utility model
Dress ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integratedly
Connection；Can be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected to by intermediary,
It can be the connection of two element internals.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
Concrete meaning of the language in the utility model.
A kind of aircraft power mechanism that the utility model embodiment is provided, the aircraft power mechanism includes：Rotor 1,
Rotor shaft 2, electric motor assembly 3 and fuel engines component 4；One end of rotor shaft 2 is fixedly connected with rotor 1, and the other end is used
It is connected in the cabin 6 with many unmanned planes of rotor 1；Electric motor assembly 3 is connected with fuel engines component 4 with rotor shaft 2,
To drive rotor shaft 2 to rotate.
The structural representation for the aircraft power mechanism that Fig. 1 provides for the utility model embodiment；As shown in figure 1, this reality
The aircraft power mechanism provided with new embodiment, when the actuating unit is connected with the cabin 6 of many unmanned planes of rotor 1, combustion
Oil turbine component 4 drives rotor shaft 2 to rotate simultaneously with electric motor assembly 3, and rotor shaft 2 drives rotor 1 to rotate, so as to produce liter
Thrust, it is adaptable to loading and manned.
The aircraft power mechanism that the utility model embodiment is provided, fuel engines component 4 and electric motor assembly 3 are simultaneously
Rotor shaft 2 is driven to rotate, fuel engines component 4 consumes oil, the consumption electric energy of electric motor assembly 3, that is, using oil electricity mixing shape
Formula is as power, while driving rotor 1 to work using chemical energy and electric energy, the rotating speed that fuel engines 41 is exported is higher, so that
The cruising time length, voyage length, load of many unmanned planes of rotor 1 can be made high, while a component failures wherein can be ensured
In the case of stabilized flight and safe falling, security is preferable.
As shown in figure 1, on the basis of above-described embodiment, further, rotor shaft 2 includes the company of being removably secured successively
The first connecting shaft 21, the second connecting shaft 22 and the 3rd connecting shaft 23 connect；Fuel engines component 4 is driven with the first connecting shaft 21
Connection；Electric motor assembly 3 is connected with the second connecting shaft 22；Rotor 1 is connected with the 3rd connecting shaft 23.
In the present embodiment, rotor shaft 2 is included into the first connecting shaft 21, the second connecting shaft 22 and the 3rd connecting shaft 23, first
Connecting shaft 21, the second connecting shaft 22 and the 3rd connecting shaft 23 are detachably connected successively, that is, using discontinuous rotor shaft 2, combustion
The connecting shaft 21 of oil turbine component 4 and first constitutes engine power module, and the connecting shaft 22 of electric motor assembly 3 and second constitutes electricity
The power plant module of motivation 31, so that the actuating unit of rotor 1 is decomposed into dismountable engine power module and motor 31 is moved
Power module.When the parts damages of engine power module or the power plant module of motor 31, user can be by corresponding module
Get off from integral demounting, it is not necessary to which overall mechanism is dismantled, so that convenient use person's quick-replaceable repairs motor
31 modules and engine block.
Wherein, the first connecting shaft 21, the second connecting shaft 22 and the 3rd connecting shaft 23 can be detachable by shaft coupling 24 respectively
Connection.
As shown in figure 1, on the basis of above-described embodiment, further, fuel engines component 4 includes fuel engines
41 and with fuel engines 41 be connected the first reducing gear 42；Fuel engines 41 passes through the first reducing gear 42 and rotation
Wing axle 2 is connected.
In the present embodiment, fuel engines component 4 includes the reducing gear 42 of fuel engines 41 and first, fuel engines
41 are connected by the first reducing gear 42 and rotor shaft 2.Operationally, the output of fuel engines 41 power, by first
Reducing gear 42, which is decelerated to after preset rotation speed, to be transmitted to rotor shaft 2, so as to drive rotor shaft 2 to be rotated under preset rotation speed.
Wherein, the first reducing gear 42 can include driving gear and driven gear, and driving gear is mutually nibbled with driven gear
Close, meanwhile, driving gear is fixedly connected with the power output shaft of fuel engines 41, and driven gear is fixedly connected with rotor shaft 2.
The number of teeth of driving gear is more than the number of teeth of driven gear.
Further, fuel engines 41 is connected by the first reducing gear 42 with the first connecting shaft 21, so that band
Dynamic first connecting shaft 21 is rotated.
On the basis of above-described embodiment, further, fuel engines component 4 also includes engine controller 43；Hair
Motivation controller 43 is electrically connected with fuel engines 41, the rotating speed for controlling fuel engines 41.
In the present embodiment, engine controller 43 controls the rotating speed of fuel engines 41, and user can be started by default
Machine controller 43, by operating engine controller 43 to be controlled the rotating speed of fuel engines 41, so that fuel oil is sent out
The rotating speed of motivation 41 is the default value of user, convenient use person's operational control fuel engines 41.
As shown in figure 1, on the basis of above-described embodiment, further, electric motor assembly 3 include motor 31 and with electricity
The second reducing gear 32 that motivation 31 is connected；Motor 31 is connected by the second reducing gear 32 and rotor shaft 2.
In the present embodiment, electric motor assembly 3 includes the reducing gear 32 of motor 31 and second, and motor 31 subtracts by second
Fast mechanism 32 is connected with rotor shaft 2.Operationally, the output of motor 31 power, is decelerated to by the second reducing gear 32
Transmitted after preset rotation speed to rotor shaft 2, so as to drive rotor shaft 2 to be rotated under preset rotation speed.
Wherein, the structure type of the second reducing gear 32 can be identical with the structure type of the first reducing gear 42.
Further, motor 31 is connected by the second reducing gear 32 with the second connecting shaft 22, so as to drive
Two connecting shafts 22 are rotated.
As shown in figure 1, on the basis of above-described embodiment, further, electric motor assembly 3 also includes motor controller
33；Motor controller 33 is electrically connected with motor 31, the rotating speed for controlling motor 31.
In the present embodiment, motor controller 33 controls the rotating speed of motor 31, and user can be by presetting motor control
Device 33 processed, by operating motor controller 33 to be controlled the rotating speed of motor 31, so that the rotating speed of motor 31
For the default value of user, convenient use person's operational control motor 31.
As shown in figure 1, on the basis of above-described embodiment, further, aircraft power mechanism also includes steering wheel 5；Rudder
Machine 5 is connected with rotor 1, the pitch for controlling rotor 1.
In the present embodiment, steering wheel 5 is connected with rotor 1, controls the pitch of rotor 1.Operationally, motor 31 and fuel oil hair
Motivation 41 drives rotor shaft 2 to rotate, and user changes the pitch of rotor 1 by steering wheel 5, so as to produce the lift of aircraft needs.
The structural representation for the multi-rotor unmanned aerial vehicle that Fig. 2 provides for the utility model embodiment；Fig. 3 is many shown in Fig. 2
The structural representation of cabin and support arm in rotor wing unmanned aerial vehicle；As shown in Figure 1-Figure 3, on the basis of above-described embodiment, one is entered
Step ground, the utility model embodiment also provides a kind of unmanned plane of many rotors 1, and many unmanned planes of rotor 1 include cabin 6 and multiple
Aircraft power mechanism as described above；Multiple rotor shafts 2 are connected with cabin 6.
Rotor shaft 2 in the unmanned plane of many rotors 1 that the present embodiment is provided, each actuating unit is connected with cabin 6, each
Rotor shaft 2 drives rotor shaft 2 to rotate simultaneously by fuel engines component 4 with electric motor assembly 3, and rotor shaft 2 drives 1 turn of rotor
It is dynamic, so as to produce a liter thrust, it is adaptable to loading and manned.
The unmanned plane of many rotors 1 that the present embodiment is provided, fuel engines component 4 drives rotor simultaneously with electric motor assembly 3
Axle 2 rotates, and fuel engines component 4 consumes oil, the consumption electric energy of electric motor assembly 3, that is, using the electric mixed form of oil as dynamic
Power, while driving rotor 1 to work using chemical energy and electric energy, the rotating speed that fuel engines 41 is exported is higher, so as to make many rotations
The cruising time length of the unmanned plane of the wing 1, voyage length, load are high, while in the case of can ensureing a component failures wherein
Stabilized flight and safe falling, security are preferable.In addition, saving the weight of transmission mechanism, simple in construction, efficiency high is returned
Many unmanned planes of rotor 1 characteristic easy to use.
Another structural representation for the multi-rotor unmanned aerial vehicle that Fig. 4 provides for the utility model embodiment；Fig. 5 is that this practicality is new
The another structural representation for the multi-rotor unmanned aerial vehicle that type embodiment is provided；As shown in Figure 4 and Figure 5, further, in cabin 6
Lower section connects undercarriage 8, battery and fuel tank is set in cabin 6, battery, fuel tank, support arm 7 and cabin 6 constitute nobody
The energy storehouse of machine.
On the basis of above-described embodiment, further, aircraft power mechanism is four；The upper surface connection of cabin 6
Have in I-shaped support arm 7；Four aircraft power mechanisms are connected at the corner of support arm 7.
In the present embodiment, the upper surface of cabin 6 is connected connects an aircraft respectively at support arm 7, the corner of support arm 7
Actuating unit, four aircraft power mechanisms produce the liter thrust to cabin 6 simultaneously.
Wherein, in four aircraft power mechanisms the rotating speed of rotor 1 is consistent, is one group positioned at two rotors 1 of diagonal angle,
Every group of two rotors 1 are turned to unanimously, and two groups of steering is opposite.
As shown in Fig. 2 on the basis of above-described embodiment, further, many unmanned planes of rotor 1 also include being arranged on cabin
Control system 9 in 6；Electric motor assembly 3, fuel engines component 4 are electrically connected with control system 9；Control system 9 is used to control
Electric motor assembly 3 processed works with fuel engines component 4.
In the present embodiment, electric motor assembly 3 and fuel engines component 4 are electrically connected with the control system 9 in cabin 6,
User is manipulated by system 9 and fuel engines component 4 and electric motor assembly 3 is controlled, so as to realize aircraft
Rising, it is lower will, advance, retreat and rotate, convenient use person operation.
Finally it should be noted that：Various embodiments above is only limited to illustrate the technical solution of the utility model, rather than to it
System；Although the utility model is described in detail with reference to foregoing embodiments, one of ordinary skill in the art should
Understand：It can still modify to the technical scheme described in foregoing embodiments, or to which part or whole
Technical characteristic carries out equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from this practicality newly
The scope of each embodiment technical scheme of type.
Claims (10)
1. a kind of aircraft power mechanism, it is characterised in that including：Rotor, rotor shaft, electric motor assembly and fuel engines
Component；
One end of the rotor shaft is fixedly connected with the rotor, and the other end is used to be connected with the cabin of multi-rotor unmanned aerial vehicle；Institute
State electric motor assembly to be connected with the rotor shaft with the fuel engines component, to drive the rotor shaft to rotate.
2. aircraft power mechanism according to claim 1, it is characterised in that the rotor shaft is included successively removably
The first connecting shaft, the second connecting shaft and the 3rd connecting shaft being fixedly connected；
The fuel engines component is connected with first connecting shaft；The electric motor assembly and second connecting shaft
Drive connection；The rotor is connected with the 3rd connecting shaft.
3. aircraft power mechanism according to claim 1, it is characterised in that the fuel engines component includes fuel oil
Engine and the first reducing gear being connected with the fuel engines；
The fuel engines is connected by first reducing gear and the rotor shaft.
4. aircraft power mechanism according to claim 3, it is characterised in that the fuel engines component also includes hair
Motivation controller；
The engine controller is electrically connected with the fuel engines, the rotating speed for controlling the fuel engines.
5. aircraft power mechanism according to claim 1, it is characterised in that the electric motor assembly include motor and
The second reducing gear being connected with the electric-motor drive；
The motor is connected by second reducing gear and the rotor shaft.
6. aircraft power mechanism according to claim 5, it is characterised in that the electric motor assembly also includes motor
Controller；
The motor controller and the electronic mechatronics, the rotating speed for controlling the motor.
7. aircraft power mechanism according to claim 5, it is characterised in that also including steering wheel；
The steering wheel is connected with the rotor, the pitch for controlling the rotor.
8. a kind of multi-rotor unmanned aerial vehicle, it is characterised in that including cabin and multiple flying as described in claim any one of 1-7
Row device actuating unit；
Multiple rotor shafts are connected with the cabin.
9. multi-rotor unmanned aerial vehicle according to claim 8, it is characterised in that the aircraft power mechanism is four；
The upper surface of the cabin is connected with I-shaped support arm；Four aircraft power mechanisms are connected to institute
State at the corner of support arm.
10. multi-rotor unmanned aerial vehicle according to claim 8, it is characterised in that the also control including being arranged in the cabin
System processed；
The electric motor assembly, the fuel engines component are electrically connected with the control system；The control system is used for
Control the electric motor assembly and the fuel engines component operation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720187492.9U CN206494122U (en) | 2017-02-28 | 2017-02-28 | Aircraft power mechanism and multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720187492.9U CN206494122U (en) | 2017-02-28 | 2017-02-28 | Aircraft power mechanism and multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206494122U true CN206494122U (en) | 2017-09-15 |
Family
ID=59806122
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720187492.9U Expired - Fee Related CN206494122U (en) | 2017-02-28 | 2017-02-28 | Aircraft power mechanism and multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206494122U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108033000A (en) * | 2017-12-05 | 2018-05-15 | 长沙展朔轩兴信息科技有限公司 | Variable multi-rotor unmanned aerial vehicle |
| CN110450955A (en) * | 2019-08-21 | 2019-11-15 | 深圳洲际通航投资控股有限公司 | A kind of stable continuation of the journey heavy-duty unmanned plane optimization structure |
| CN111319758A (en) * | 2018-11-29 | 2020-06-23 | 空客直升机 | Modular aircraft and method for preparing such an aircraft for a specific task |
-
2017
- 2017-02-28 CN CN201720187492.9U patent/CN206494122U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108033000A (en) * | 2017-12-05 | 2018-05-15 | 长沙展朔轩兴信息科技有限公司 | Variable multi-rotor unmanned aerial vehicle |
| CN111319758A (en) * | 2018-11-29 | 2020-06-23 | 空客直升机 | Modular aircraft and method for preparing such an aircraft for a specific task |
| CN110450955A (en) * | 2019-08-21 | 2019-11-15 | 深圳洲际通航投资控股有限公司 | A kind of stable continuation of the journey heavy-duty unmanned plane optimization structure |
| CN110450955B (en) * | 2019-08-21 | 2023-06-09 | 深圳洲际通航投资控股有限公司 | Stable endurance large-load unmanned aerial vehicle optimization structure |
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| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170915 Termination date: 20200228 |
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| CF01 | Termination of patent right due to non-payment of annual fee |