CN205971825U - Be applied to unmanned aerial vehicle's power equipment - Google Patents
Be applied to unmanned aerial vehicle's power equipment Download PDFInfo
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- CN205971825U CN205971825U CN201620805741.1U CN201620805741U CN205971825U CN 205971825 U CN205971825 U CN 205971825U CN 201620805741 U CN201620805741 U CN 201620805741U CN 205971825 U CN205971825 U CN 205971825U
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Abstract
The utility model discloses a be applied to unmanned aerial vehicle's power equipment belongs to aviation technical field, include: a single cylinder engine is provided with the primary shaft, the 2nd single cylinder engine is provided with the secondary shaft, the starter is respectively with the primary shaft and secondary shaft swing joint, the connection pad, a single cylinder engine passes the connection pad through the primary shaft, and the 2nd single cylinder engine passes the connection pad through the secondary shaft, the forced air cooling system is fixed in a single cylinder engine with on the 2nd single cylinder engine. The utility model discloses a being applied to unmanned aerial vehicle, setting up the comburent production mechanical energy that a single cylinder engine and the 2nd single cylinder engine inject into in advance with the burning, and then for the rotation of rotor provides power, replaced traditional passing through battery poweredly or increase the electronic flight mode that battery quantity improves time of endurance, feasible application has the utility model discloses an unmanned aerial vehicle has the characteristics that time of endurance is long, the lifting capacity is strong at least.
Description
Technical field
This utility model belongs to technical field of aerospace, particularly to a kind of power-equipment machine being applied to unmanned plane.
Background technology
Unmanned plane (english abbreviation:Unmanned Aerial Vehicle) it is a kind of with wireless remotecontrol or by itself journey
Not manned aircraft based on sequence control.
Unmanned plane of the prior art mostly is electronic unmanned plane, mainly adopts battery, electric tune, motor, flies control and propeller
Etc. main devices, the flight realizing unmanned plane by changing the rotating speed of each propeller controls.But, this electric type unmanned
Machine, due to being limited by battery energy density, typically very of short duration during its boat, there is the defect of duration performance difference, and by single
Pure increase number of batteries also can substantially reduce its lifting capacity come mode when improving its boat.
Utility model content
This utility model provides a kind of power-equipment being applied to unmanned plane, by arranging the first single-cylinder engine and second
Horizontal bar electromotor, notes the comburant in cylinder body in advance and produces mechanical kinetic energy, and then provide for the rotation of unmanned plane dynamic to burn
Power, instead of traditional powered by battery or increase number of batteries improving the electronic offline mode in cruising time so that
Application has unmanned plane of the present utility model at least to have the strong technical characterstic of cruising time length, lifting capacity.
This utility model provides a kind of power-equipment being applied to unmanned plane, the described power-equipment being applied to unmanned plane
Including：First single-cylinder engine, described first single-cylinder engine is provided with first axle；Second single-cylinder engine, described second is single
Cylinder engine is provided with the second axle；Trigger, described trigger is flexibly connected with described first axle and described second axle respectively, with
Described first axle and described second axle rotation are started by described trigger；Terminal pad；Described first single-cylinder engine passes through institute
State first axle and pass through described terminal pad, described second single-cylinder engine passes through described terminal pad by described second axle, to pass through
Described first single-cylinder engine and described second single-cylinder engine are connected as one by described terminal pad；Air cooling system, described wind
Cooling system is fixed on described first single-cylinder engine and described second single-cylinder engine so that the cold air in the external world is by described
Air cooling system is inhaled in described first single-cylinder engine and described second single-cylinder engine, with to described first single-cylinder engine
And/or described second single-cylinder engine is cooled down.
Optionally, also include：First carburator, described first carburator is connected with the oil-in of described first single-cylinder engine
Connect；Second carburator, described second carburator is connected with the oil-in of described second single-cylinder engine；Wherein, described first is single
Comburant in the cylinder body of Cylinder engine is injected into by described first carburator, in the cylinder body of described second single-cylinder engine
Comburant is injected into by described second carburator.
Optionally, described first axle is arranged with one first shaft gear；One second shaft gear is arranged with described second axle；
Described trigger is meshed with described first shaft gear and described second shaft gear respectively by a starter receiver, so that described
The direction of rotation of one axle and described second axle is contrary.
Optionally, described terminal pad includes：First lid；Second lid；Wherein, described first lid and described second lid
Body detachable connection, and it is formed with an accommodation space, described first axle between described first lid and described second lid
Gear, described second shaft gear and described starter receiver are located in described accommodation space.
Optionally, described detachable connection is bolt connection or mode connects for screw.
Optionally, described first axle and described second axle are parallel to each other；And described first axle and described second axle respectively with
Described terminal pad is perpendicular.
Optionally, the direction of rotation of described first axle and described second axle is contrary.
Optionally, described first single-cylinder engine and described second single cylinder are with the center vertical pivot of described terminal pad as axis of symmetry
Symmetrical.
Optionally, also include：First row gas tank；Second row gas tank；Wherein, described first row gas tank is fixed on described first
The bottom of horizontal bar electromotor, and communicate with the cylinder body of described first single-cylinder engine；Described second row gas tank is fixed on described
The bottom of two single-cylinder engines, and communicate with the cylinder body of described second single-cylinder engine.
Optionally, described first row gas tank and described first single-cylinder engine bolt connection or welding；And/or, described
Second row gas tank and described second single-cylinder engine bolt connection or welding.
Beneficial effect：
The power-equipment being applied to unmanned plane that this utility model provides, by being applied to unmanned plane, is flying of unmanned plane
Row provides power, and the comburant being previously implanted in the cylinder body of the first single-cylinder engine and the second single-cylinder engine is (as gaseous state
Comburant that comburant, liquid-phase combustion thing, gaseous state and liquid combine etc.), to produce mechanical kinetic energy, drive and send out with the first horizontal bar
The rotor of motivation connection corresponding with the second single-cylinder engine is rotated.To substitute the electric models such as conventionally employed battery, electricity tune
Be powered thinking the electronic unmanned plane of the powered rotation of rotor, and this utility model need not by increase number of batteries Lai
Improve cruising time and lead to the lifting capacity of unmanned plane to reduce so that application to have unmanned plane of the present utility model at least to have continuous
The strong technical characterstic of ETS estimated time of sailing length, lifting capacity.
Brief description
In order to be illustrated more clearly that this utility model embodiment or technical scheme of the prior art, below will be to embodiment
In required use accompanying drawing be briefly described it should be apparent that, drawings in the following description are only of the present utility model
Some embodiments, for those of ordinary skill in the art, on the premise of not paying creative work, can also be according to this
A little accompanying drawings obtain other accompanying drawings.
The overall structure diagram one of the unmanned plane that Fig. 1 provides for this utility model embodiment；
The overall structure diagram two of the unmanned plane that Fig. 2 provides for this utility model embodiment；
The overall structure diagram three of the unmanned plane that Fig. 3 provides for this utility model embodiment；
The overall structure diagram of the power-equipment being applied to unmanned plane that Fig. 4 provides for this utility model embodiment；
The overall structure front view of the power-equipment being applied to unmanned plane that Fig. 5 provides for this utility model embodiment；
The detonation configuration front view of the power-equipment being applied to unmanned plane that Fig. 6 provides for this utility model embodiment；
The part-structure front view of the first belt drive unit that Fig. 7 provides for this utility model embodiment；
The part-structure sectional view of the first belt drive unit that Fig. 8 provides for this utility model embodiment；
The part-structure front view of the second belt drive unit that Fig. 9 provides for this utility model embodiment；
The part-structure sectional view of the second belt drive unit that Figure 10 provides for this utility model embodiment；
The overall structure front view of the variable pitch device that Figure 11 provides for this utility model embodiment；
The overall structure diagram of the variable pitch device that Figure 12 provides for this utility model embodiment.
Specific embodiment
The power-equipment being applied to unmanned plane that this utility model provides, by being applied to unmanned plane, is flying of unmanned plane
Row provides power, and the comburant being previously implanted in the cylinder body of the first single-cylinder engine and the second single-cylinder engine is (as gaseous state
Comburant that comburant, liquid-phase combustion thing, gaseous state and liquid combine etc.), to produce mechanical kinetic energy, drive and send out with the first horizontal bar
The rotor of motivation connection corresponding with the second single-cylinder engine is rotated.To substitute the electric models such as conventionally employed battery, electricity tune
Be powered thinking the electronic unmanned plane of the powered rotation of rotor, and this utility model need not by increase number of batteries Lai
Improve cruising time and lead to the lifting capacity of unmanned plane to reduce so that application to have unmanned plane of the present utility model at least to have continuous
The strong technical characterstic of ETS estimated time of sailing length, lifting capacity.
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is carried out
Clearly and completely description is it is clear that described embodiment is only a part of embodiment of this utility model rather than whole
Embodiment.Based on the embodiment in this utility model, the every other embodiment that those of ordinary skill in the art are obtained, all belong to
Scope in this utility model protection；Wherein involved in this enforcement "and/or" key word, represent and or two kinds of situations, change
Sentence is talked about, A and/or B mentioned by this utility model embodiment illustrates A and B, two kinds of situations of A or B, describe A and B and deposited
Three kinds of states, such as A and/or B, represent：Only include A and do not include B；Only include B and do not include A；Including A and B.
Meanwhile, in this utility model embodiment, when assembly is referred to as " being fixed on " another assembly, it can be directly another
On one assembly or can also there is assembly placed in the middle.When an assembly is considered as " connection " another assembly, it can be
It is directly connected to another assembly or may be simultaneously present assembly placed in the middle.When assembly be considered as " being arranged at " another
Assembly, it can be to be set directly on another assembly or may be simultaneously present assembly placed in the middle.This utility model embodiment
Used in term " vertical ", " level ", "left", "right" and similar statement be merely for purposes of illustration, not
It is intended to limit this utility model.
The power-equipment being applied to unmanned plane in order to provide to utility model elaborates, to support utility model institute
Technical problem to be solved, below, in the embodiment that this utility model provides, first the overall structure of unmanned plane is done specifically
Bright, then during narration unmanned plane, that targetedly draws this utility model offer further is applied to unmanned plane
Power-equipment, with reach complete, clear, understand purpose.
Refer to Fig. 1-2, this utility model embodiment provides a kind of unmanned plane, at least includes：Frame 1, several rotations
Wing group 2, it is applied to the power-equipment 3 of unmanned plane.Wherein, each described rotor group 2 includes several rotors 21, and each
Described rotor group 2 be rotationally fixed in described frame 1 so that described rotor 21 in each described rotor group 2 with respect to
Described frame 1 can rotate；And the described power-equipment 3 being applied to unmanned plane is fixed in described frame 1, and corresponding difference
It is flexibly connected so that the described power-equipment 3 being applied to unmanned plane and each described rotor group with rotor group 2 each described
Can machine driving between 2.Wherein, the comburant by being applied to be previously implanted in the power-equipment 3 of unmanned plane described in burning, produces
Raw mechanical kinetic energy, drives and the institute in each described rotor group 2 of the described corresponding connection of power-equipment 3 being applied to unmanned plane
State rotor 21 to be rotated.
Specifically, the frame 1 in this utility model embodiment is the support platform of unmanned flight's equipment overall structure, with
For several rotor groups 2, it is applied to the fixed installation on unmanned flight's equipment such as power-equipment 3 of unmanned plane and supports.If
Each of dry rotor group 2 described rotor group 2 is rotationally fixed in described frame 1, wherein, for rotation each described
How wing group 2 is rotationally fixed in described frame 1, and this utility model embodiment is not limited, and can be that rotor group 2 is direct
It is fixed in frame 1 so that can be with respect to rotating naturally it is also possible to be by one individually between rotor group 2 and frame 1
Head rotor group 2 is actively fixed in frame 1 so that can be with respect to rotation, between rotor group 2 and frame 1
As long as being capable of so that the described rotor 21 in each described rotor group 2 is rotated with respect to described frame 1, then all eventually
It is applicable to this utility model.
For the rotor group 2 in this utility model embodiment, can be multiple it will be understood that due to every
One rotor group 2 includes several rotors 21, then the quantity of rotor group 2 is more, and that is, the quantity of rotor 21 is more.
In this utility model embodiment, the quantity of rotor group 2 can be m, and described m is the even number more than or equal to 2.Why will
Quantity m of rotor group 2 is defined to the even number more than or equal to 2, is mainly based upon the unmanned flight of this utility model embodiment offer
The integral structure layout of equipment, to improve the stationarity of equipment in flight course.As m rotor group 2 being divided into first group
With second group, that is, include first group of m/2 rotor group and second group of m/2 rotor group, described first group of m/2 rotor
Group is flexibly connected with the described power-equipment 3 being applied to unmanned plane respectively, described second group of m/2 rotor group respectively with described
The power-equipment 3 being applied to unmanned plane is flexibly connected, and described first group of m/2 rotor group and the described unmanned plane that is applied to
Machine driving between power-equipment, and described second group of m/2 rotor group and the described power-equipment being applied to unmanned plane
Between machine driving separate.Wherein, m/2 rotor group of first group of m/2 rotor group and second group, to be applied to
Point of symmetry centered on the power-equipment 3 of unmanned plane, are symmetrically dispersed in the both sides of the power-equipment 3 being applied to unmanned plane.
Refer to Fig. 3-6 in the lump incorporated by reference to Fig. 2, for the power-equipment 3 being applied to unmanned plane, at least include first and move
Power source 32, the second power source 33 and trigger 34.Wherein, described first power source 32 is provided with first axle 321, described first group
M/2 rotor group be flexibly connected with described first axle 321 respectively.Described second power source 32 is provided with the second axle 331, described
Second group of m/2 rotor group is flexibly connected with described second axle 331 respectively.Described trigger 34 respectively with described first axle
321 and described second axle 331 be flexibly connected, so that described first axle 321 and described second axle 331 are started by described trigger 34
Rotation.It should be noted that the first axle 321 set by described first power source 32 is used for driving described first group of m/2
Individual rotor group is rotated, and the second axle 331 set by described second power source 33 is used for driving m/2 of described second group
Rotor group is rotated.
Specifically, trigger 34, as activation member, starts first axle 321 first and the second axle 331 is rotated, and
Start postrotational described first axle 321, compress the described comburant of injection in described first power source 32, explode and burn,
Convert heat into mechanical kinetic energy, drive described first axle 321 to continue rotation, Jin Ertong under the impact of the air pressure of rapid expansion
Crossing described first axle 321 drives each of described first group of m/2 rotor group rotor to be rotated, and enters first with this
The normal circulation driver of m/2 rotor group of power source 32, first axle 321 and first group.Start postrotational described
Two axles 331, compress the described comburant of injection in described second power source 32, explode and burn, and convert heat into machinery dynamic
Can, drive described second axle 331 to continue rotation under the impact of the air pressure of rapid expansion；And then carried by described second axle 331
Each of dynamic described second group of m/2 rotor group rotor is rotated, and enters the second power source 33, the second axle with this
331 and the normal circulation driver of second group of m/2 rotor group.It should be noted that in this utility model embodiment
Trigger 34 starts after first axle 321 and the second axle 331 rotated as activation member, then trigger 34 is automatically and first axle
321 and second axle 331 depart from and quit work, now rely on the internal energy of itself of the first power source 32, the second power source 33
Conversion heat energy-mechanical energy, thinks first axle 321 and the powered rotation of the second axle 331.
Wherein, how first axle 321 is started for trigger 34 and the second axle 331 rotates, this utility model is implemented
Example is not limited, and can be directly with first axle 321 and the second axle 331, trigger 34 to be set up machine driving relation, such as exist
Several teeth are opened up on the side wall of first axle 321 and the second axle 331, the rotary shaft of trigger 34 is directly and first axle 321 and the
Opened up several teeth on the side wall of two axles 331 to be meshed, then by the rotation of the rotary shaft of trigger 34, driven described the
One axle 321 and the second axle 331 are rotated.For another example can each setting one on the side wall of first axle 321 and the second axle 331 respectively
The individual mechanical arm that can rotate rotating around the carrying out of first axle 321 or the second axle 331, this 2 mechanical arms respectively with described trigger
34 connections, to drive 2 described mechanical arm actions respectively by described trigger 34, realize 2 described mechanical arms each then
The first axle 321 that corresponding drive is attached thereto or the second axle 331 are rotated.
Again or, directly can set up the first shaft gear 322 in the first power source 32, the second power source 33 is set up
Two shaft gears 332, set up starter receiver 31 in the power-equipment be applied to unmanned plane.Wherein, 322 sets of described first shaft gear
It is located in described first axle 321, to realize and described first axle 321 synchronous axial system, described second shaft gear 332 is set in described
On second axle 331, to realize and described second axle 331 synchronous axial system.Meanwhile, described starter receiver 31 and described trigger 34
Rotary shaft connects, and to drive described starter receiver 31 to be rotated by described trigger 34, and described starter receiver 31 is respectively
Accordingly it is meshed with described first shaft gear 322 and described second shaft gear 332, to ensure the mistake rotating in starter receiver 31
In journey, the first shaft gear 322 and the second shaft gear 332 being capable of synchronous axial system.Certainly, for the first shaft gear 322 and first axle
321 connected mode, and the connected mode of the second shaft gear 332 and the second axle 331 or diversified, such as the
One shaft gear 322 and first axle 321 can be using the connected modes of welding, and the second shaft gear 332 and the second axle 331 can adopt
The connected mode of welding.For another example the first shaft gear 322 and first axle 321 can adopt integrally formed design, the second axle
Gear 332 and the second axle 331 can also adopt integrally formed connected mode.As long as can reach in this utility model embodiment
Technology to the first shaft gear 322 and described first axle 321 synchronous axial system, the second shaft gear 332 and the second axle 331 synchronous axial system
Effect.Likewise, due to there are 2 shaft gears (the first shaft gear 322 and the second shaft gear 332), for starter receiver
31 number or even trigger 34 can also be all 2 respectively.That is, the first shaft gear 322 mates a starter receiver 31 and
Individual trigger 34, the second shaft gear 332 mates a starter receiver 31 and a trigger 34, or the first shaft gear 322
Join a starter receiver 31, the second shaft gear 332 mates a starter receiver 31, a trigger 34 starts two startups simultaneously
Gear 31 rotates etc., as long as being finally capable of driving first axle 321 and the second axle 331 to be rotated, is then all applied to
This utility model.
Sum it up, as stated above, how first axle 321 is started for trigger 34 and the second axle 331 revolves
Turn, this utility model embodiment is not limited, can be with using three kinds of startup structures of above-mentioned at least description and mode, certainly
Can be using not limiting to other startup structures and the mode that this utility model embodiment is provided, as long as can be real during being suitable for
Existing trigger normally starts first axle 321 and the second axle 331 is rotated, and is all applied to this utility model, here is omitted.
But it is noted that first axle 321 described in this utility model embodiment and described second axle 331 are parallel and described
The direction of rotation of first axle 321 and described second axle 331 is contrary.
Further, for the power-equipment 3 being applied to unmanned plane, in order to simplify internal structure design, reduce work
Industry manufacturing cost, the first power source 32 described above can be first single-cylinder engine, and the second power source 33 can be
One the second single-cylinder engine.And be applied to the power-equipment 3 of unmanned plane and can also include terminal pad 35.
Wherein, described first single-cylinder engine is provided with described first axle 321, the cylinder body of described first single-cylinder engine
Inside it is injected with comburant；Described second axle 331, the cylinder of described second single-cylinder engine are provided with described second single-cylinder engine
It is injected with comburant in vivo；Described first single-cylinder engine by described first axle 321 pass through described terminal pad 35, described second
Single-cylinder engine passes through described terminal pad 35 by described second axle 331 so that by described terminal pad 35 by described first singly
Cylinder engine and described second single-cylinder engine connect as one.
Meanwhile, the described power-equipment 3 being applied to unmanned plane also includes：First carburator 36 and the second carburator 37, and
Described first carburator 36 is connected with the oil-in of described first single-cylinder engine；Described second carburator 37 is single with described second
The oil-in of Cylinder engine connects.So allow for comburant (as liquid-phase combustion thing) under different conditions in the first carburator 36
And/or second in the presence of carburator 37, it is converted into gaseous combustion thing, thinks comburant in the first single-cylinder engine and/or
Blast in two single-cylinder engines, burning are prepared.It is to be understood that the comburant in the cylinder body of described first single-cylinder engine
It is injected into by described first carburator 36, the comburant in the cylinder body of described second single-cylinder engine vaporizes by described second
Device 37 is injected into.
It should be noted that the first single-cylinder engine and the second single cylinder are sent out by this utility model embodiment by terminal pad 35
Motivation connects as one, and to form the power-equipment 3 being applied to unmanned plane of a twin shaft, this described terminal pad 35 can include：
First lid 351 and the second lid 352.Wherein, described first lid 351 and described second lid 352 detachable connection, and
It is formed with an accommodation space 353 between described first lid 351 and described second lid 352, described first shaft gear 322,
Described second shaft gear 332 and described starter receiver 31 are placed in described accommodation space 353.And, described trigger 34 passes through institute
State the first lid 351 or described second lid 352 is connected with described starter receiver 31.
It is to be understood that the first axle 321 of the first single-cylinder engine is arranged with described first shaft gear 322, the second single cylinder
Described second shaft gear 332 is arranged with electromotor.Trigger 34 starts the first shaft gear 322 He first by starter receiver 31
Second shaft gear 33 is rotated, and then drives first axle 321 and the second axle 331 to be rotated (the two direction of rotation is contrary),
And start postrotational described first axle 321, and the described comburant of injection in the described first single-cylinder engine cylinder body of compression, blast
And burn, convert heat into mechanical kinetic energy, drive described first axle 321 to continue rotation under the impact of the air pressure of rapid expansion
Turn, and then drive each of described first group of m/2 rotor group rotor to be rotated by described first axle 321, with
This enters the normal circulation driver of m/2 rotor group of the first single-cylinder engine, first axle 321 and first group.Start rotation
Described second axle 331 after turning, compresses the described comburant of injection in described second power source 32, explodes and burn, by heat energy
It is converted into mechanical kinetic energy, drive described second axle 331 to continue rotation under the impact of the air pressure of rapid expansion；And then by described
Second axle 331 drives each of described second group of m/2 rotor group rotor to be rotated, and enters the second single cylinder with this and sends out
The normal circulation driver of m/2 rotor group of motivation, the second axle 331 and second group.It is noted that the first single cylinder is sent out
The inside principle of motivation and the second single-cylinder engine (as started postrotational described first axle 321, is compressed described first single cylinder and is sent out
The described comburant of injection, explodes and burns, convert heat into mechanical kinetic energy in engine cylinder body, in the air pressure of rapid expansion
Impact is lower to drive described first axle 321 to continue rotation), for the operation principle of electromotor in prior art, here is omitted.
And how the first single-cylinder engine and the second single-cylinder engine to be passed through terminal pad 35, trigger 34 and/or starter receiver 31 shape
Become twin-tub opposed double output shaft electromotor, and be applied on the flight equipment of the dynamic many rotors of displacement of oil so as to structure is simple
Reliable light, it is provided simultaneously with the high technical characteristic innovative point exactly of the present utility model of cruising time length, load-carrying and be located.
Further, so that this utility model embodiment provide be applied to unmanned plane power-equipment 3 timely
Cooling, it is to avoid affect it and normally use because its temperature is too high.Preferably, this utility model embodiment also includes：Air-cooled system
System 38.Described air cooling system 38 is fixed on described first power source 32 and described second power source 33 so that the cold sky in the external world
Gas by described air cooling system 38 be inhaled into described in be applied to unmanned plane power-equipment 3 inside, and then flow through described first
Power source 32 and/or described second power source 33, cold to carry out to described first power source 32 and/or described second power source 33
But.
Specifically, please continue to refer to Fig. 4-5, described air cooling system 38 can include：Cover body 381, the first centrifugal fan 382
With the second centrifugal fan 383.Wherein, described first centrifugal fan 382 is flexibly connected with described first axle 321, with by described
First axle 321 drives described first centrifugal fan 382 to be rotated；Described second centrifugal fan 383 is lived with described second axle 331
It is dynamically connected, to drive described second centrifugal fan 383 to be rotated by described second axle 331.And, described first centrifugal fan
382nd, described second centrifugal fan 383, described first power source 32 and described second power source 33 are placed in described cover body 381,
And described first centrifugal fan 382 after rotating and/or described second centrifugal fan 383 drive described cold air in described cover body
Flowed in 381, to cool down to described first power source 32 and/or described second power source 33.
In this utility model embodiment, the effect of the first centrifugal fan 382 and the second centrifugal fan 383 be by fluid from
Fluid is thrown out it can be understood as getting rid of in cover body 381 from circumferencial direction after sucking by the axial direction of fan using its centrifugal force, enters
And described first power source 32 and described second power source 33 are carried out air-cooled.To prevent described first power source 32 and described
Two power sources 33 are longer because of the working time, and persistent fever makes cover body 381 interior temperature spend height and affect described first power source
32 and the normal operation of described second power source 33, have the characteristics that security performance is high.
Certainly, although in this utility model embodiment, the quantity of power source is two, such as：Described first power source 32 He
Described second power source 33.The quantity of matched centrifugal fan is also two, such as：Described first centrifugal fan 382 He
Described second centrifugal fan 383.The quantity of matched axle is also two, such as：First axle 321 and the second axle 331.But its
Particular number this utility model is not limited.In other words, according to actual job demand, the quantitative design of power source is become
Three, four or five etc., may also apply to this utility model, only need to be by the quantity of corresponding centrifugal fan, axle
Quantity is also designed to three, four or five.Remaining structure does adaptation, then all in protection of the present utility model
Within the scope of.
Preferably, the described cover body 381 in this utility model embodiment can include：The first side wall 3811, the second side
Wall 3812 and air intake plate 3813.Wherein, described air intake plate 3813 offers the first air inlet 3813a and the second air inlet
3813b, and the end of the end of described the first side wall 3811 and described second sidewall 3812 is solid with described air intake plate 3813 respectively
Fixed connect, to constitute the described cover body 381 of U-shaped structure, and described the first side wall 3811 and described second sidewall 3812 mutual
Parallel.Described first power source 32 and described second power source 33 are placed in the U-type groove of described U-shape structure, and the institute after rotation
Stating the first centrifugal fan 382 drives described cold air to be flowed into inside described cover body 381 by described first air inlet 3813a, rotates
Described second centrifugal fan 383 afterwards drives described cold air to be flowed in described cover body 381 by described second air inlet 3813b
Portion.
In this utility model embodiment, the machinery biography and the power-equipment 3 being applied to unmanned plane between for rotor group 2
For dynamic, a belt drive unit 4 can be passed through, be fixed in described frame 1, and by the described power-equipment being applied to unmanned plane
3 and each described rotor group 2 be accordingly flexibly connected, to be applied to unmanned plane described in making by described belt drive unit 4
Power-equipment 3 and each described rotor group 2 between can machine driving.Specifically, Fig. 7-10 are referred in the lump incorporated by reference to Fig. 2-3,
Belt drive unit 4 can be specifically divided into：First belt drive unit 41 and the second belt drive unit 42.
Wherein, described first belt drive unit 41 is fixed in described frame 1, and the m/2 with described first group respectively
Individual rotor group is accordingly flexibly connected.Described second belt drive unit 42 is fixed in described frame 1, and respectively with described
Two groups of m/2 rotor group is accordingly flexibly connected；Wherein, one end of described first belt drive unit 41 is set in described
On one axle 321, the other end of described first belt drive unit 41 is set in the rotor of rotor in first group of m/2 rotor group
On axle, it is driven by described first belt drive unit 41 that rotarily drives of described first axle 321, to drive described first
Each of m/2 rotor group of group rotor is rotated.One end of described second belt drive unit 42 is set in described
On two axles 331, the other end of described second belt drive unit 42 is set in the rotor of rotor in second group of m/2 rotor group
On axle, it is driven by described second belt drive unit 42 that rotarily drives of described second axle 331, to drive described second
Each of m/2 rotor group of group rotor is rotated.
More specifically, described first belt drive unit 41 at least can include：1 the first power transmission shaft 411, m/2
Second driving shaft 412, the first conveyer belt 413, the first motor 414 and the second motor 415.Wherein, described first power transmission shaft 411 wraps
Include one first fixing end 4111 and one first bevel gear end 4112, and described first bevel gear end 4112 is in bevel gear structure.Often
One described second driving shaft 412 includes one the 3rd bevel gear end 4121 and one the 4th bevel gear end 4122, and described 3rd umbrella
Gear end 4121 and described 4th bevel gear end 4122 are all in bevel gear structure.It is sheathed that described first conveyer belt 413 includes first
End 4131 and the second sheathed end 4132.Described first motor 414 is fixed in described first axle 321, and described first motor and
Described first axle synchronous axial system, described first conveyer belt 413 is set in described first motor by the described first sheathed end 4131
On 414.Described second motor 415 is fixed in described first fixing end 4111, and described second motor 415 and described first biography
Moving axis 411 synchronous axial system, described first conveyer belt 413 is set in described second motor 415 by the described second sheathed end 4132
On.
And then make, described first group of m/2 rotor group and described m/2 second driving shaft 412 correspond, i.e.
One of first group rotor group corresponds to one of m/2 second driving shaft 412 second driving shaft 412.And described first group
M/2 rotor group pass through bevel gear structure respectively, the accordingly individual 4th umbrella tooth with the m/2 of described m/2 second driving shaft 412
Wheel end 4122 is meshed；And described m/2 second driving shaft 412 vertical pivot centered on described first power transmission shaft 411 is symmetrical,
M/2 the 3rd bevel gear end 4121 of described m/2 second driving shaft 412 and described first umbrella of described first power transmission shaft 411
Gear end 4112 is meshed, and the vertical translating rotation by described first power transmission shaft 411 is the horizontal of described second driving shaft 412
Rotation, and then the rotation of each of described first group m/2 rotor group is driven by the transverse rotation of described second driving shaft 412
The wing 21 is rotated.
Due to described first belt drive unit 41 in this utility model embodiment, and described second belt drive unit
42 is the both sides of the power-equipment 3 that symmetrical being distributed in is applied to unmanned plane, you can be interpreted as, the first belt drive unit 41
Be distributed in first axle 321 side corresponding with first axle 321 carry out machine driving, the second belt drive unit 42 is distributed in
The side of two axles 331 is corresponding with the second axle 331 to carry out machine driving.
Therefore, identical, described second belt drive unit 42 includes：1 the 3rd power transmission shaft 421, m/2 the 4th transmission
Axle 422, the second conveyer belt 423, the 3rd motor 424 and the 4th motor 425.Wherein, described 3rd power transmission shaft 421 includes one second
Fixing end 4211 and one the 5th bevel gear end 4212, and described 5th bevel gear end 4212 is in bevel gear structure.Described in each
4th power transmission shaft 422 includes one the 6th bevel gear end 4221 and one the 7th bevel gear end 4222, and described 6th bevel gear end
4221 and described 7th bevel gear end 4222 all in bevel gear structure.Described second conveyer belt 423 includes the 3rd sheathed end 4231
With the 4th sheathed end 4232.Described 3rd motor 424 is fixed on described second axle 331, and described 3rd motor 424 and described
Second axle 331 synchronous axial system, described second conveyer belt 423 is set in described 3rd motor by the described 3rd sheathed end 4231
On 424.Described 4th motor 425 is fixed in described second fixing end 4211, and described 4th motor 425 and described 3rd biography
Moving axis 421 synchronous axial system, described second conveyer belt 423 is set in described 4th motor 425 by the described 4th sheathed end 4232
On.
Again such that, described second group of m/2 rotor group is corresponded with described m/2 the 4th power transmission shaft 422, i.e.
In m/2 rotor group in second group, a rotor group corresponds to one of m/2 the 4th power transmission shaft 422 the 4th power transmission shaft 422.
And described second group of m/2 rotor group passes through bevel gear structure respectively, accordingly with described m/2 the 4th power transmission shaft 422
M/2 the 7th bevel gear end 4222 is meshed；And described m/2 the 4th power transmission shaft 422 is centered on described 3rd power transmission shaft 421
Vertical pivot is symmetrical, m/2 the 6th bevel gear end 4221 of described m/2 the 4th power transmission shaft 422 and described 3rd power transmission shaft 421
M/2 described 5th bevel gear end 4212 be meshed, with by the vertical translating rotation of described 3rd power transmission shaft 421 for described the
The transverse rotation of four power transmission shafts 422, and then described second group of m/2 is driven by the transverse rotation of described 4th power transmission shaft 422
Each of individual rotor group rotor 21 is rotated.
The quantity of rotor described in each of this utility model embodiment described rotor group 2 can be n, and described n
It is the integer more than or equal to 2
Certainly, in this utility model embodiment, in order to preferably to rotor group 2 and the first belt drive unit 41 and
Machine driving between two belt drive units 42 is described in detail, and this utility model enters traveling one taking m=4, n=3 as a example
Step ground illustrates.Certainly, it is obvious to one skilled in the art that m=4 is only a kind of value mode of m, n=3 is also only n
A kind of value mode, when the even number numerical value such as m=6,8,10, n=2, during the integer value such as 4,5,6, may also apply to this practicality
New.
For example, as m=4, n=3, then 4 rotor groups 2 are always co-existed in, 2 rotor groups including first group and second group
2 rotor groups, comprise 3 rotors 21 in each rotor group 2.Now, the 2 rotor groups (first group) in 4 rotor groups
It is distributed in the side of the first power transmission shaft 411, the other 2 rotor groups (second group) in 4 rotor groups are distributed in second driving shaft
412 side.Meanwhile, described first belt drive unit 41 just includes 2 second driving shafts 412.2 described second biographies
Moving axis 412 includes one the 3rd bevel gear end 4121 and one the 4th bevel gear end 4122, and described 3rd bevel gear end 4121 and institute
State the 4th bevel gear end 4122 all in bevel gear structure.So allow for, described first group of 2 rotor groups with described 2 the
Two power transmission shafts 412 correspond, i.e. one of first group rotor group corresponds to one of 2 second driving shafts 412 second biography
Moving axis 412.And described first group of 2 rotor groups pass through bevel gear structure, respectively accordingly with described 2 second driving shafts
412 2 the 4th bevel gear ends 4122 are meshed；And during described 2 second driving shafts 412 with described first power transmission shaft 411 are
Heart vertical pivot is symmetrical, 2 of described 2 second driving shafts 412 the 3rd bevel gear ends 4121 and described first power transmission shaft 411
Described first bevel gear end 4112 is meshed, to be driven the vertical translating rotation of described first power transmission shaft 411 for described second
The transverse rotation of axle 412, and then described first group of 2 rotor groups 2 are driven by the transverse rotation of described second driving shaft 412
In 3 rotors 21 rotated.
Identical, now described second belt drive unit 42 also include 2 the 4th power transmission shafts 422, and 2 the described 4th
Power transmission shaft 422 all includes one the 6th bevel gear end 4221 and one the 7th bevel gear end 4222, and described 6th bevel gear end 4221
With described 7th bevel gear end 4222 all in bevel gear structure.So allow for, described second group of 2 rotor groups and described 2
Individual 4th power transmission shaft 422 corresponds, i.e. in 2 rotor groups in second group, a rotor group corresponds to 2 the 4th power transmission shafts
One of 422 the 4th power transmission shafts 422.And described second group of 2 rotor groups pass through bevel gear structure, respectively accordingly with institute
2 the 7th bevel gear ends 4222 stating 2 the 4th power transmission shafts 422 are meshed；And described 2 the 4th power transmission shafts 422 are with described
Centered on three power transmission shafts 421, vertical pivot is symmetrical, 2 the 6th bevel gear ends 4221 of described 2 the 4th power transmission shafts 422 with described
2 described 5th bevel gear ends 4212 of the 3rd power transmission shaft 421 are meshed, by the vertical rotation of described 3rd power transmission shaft 421
It is converted into the transverse rotation of described 4th power transmission shaft 422, and then driven by the transverse rotation of described 4th power transmission shaft 422 described
In second group of 2 rotor groups 2,3 rotors 21 are rotated.
It is noted that in this utility model embodiment, the quantity of rotor group 3 in first group, with second driving shaft
412 quantity is identical, the quantity of rotor group 3 in second group, and the quantity with the 4th power transmission shaft 422 is identical, but, the
In the quantity of rotor group 3 and second group in one group, the quantity of rotor group 3 can differ.In other words, this utility model
Embodiment to the quantity of rotor group 3 in first group with second group in rotor group 3 quantity whether identical do not limit, as long as meeting
The quantity of rotor group 3 in first group, the quantity with second driving shaft 412 is identical, the quantity of rotor group 3 in second group, with
The quantity of the 4th power transmission shaft 422 is identical.Equally, the quantity of the first power transmission shaft 411, the quantity with first axle 321 is
Identical, the quantity of the 3rd power transmission shaft 421, the quantity with the second axle 331 is identical.But, the quantity of first axle 321 and
The quantity of two axles 331 can differ.And its particular number this utility model is not limited.In other words, according to
Actual job demand, the quantitative design of first axle 321 is become two, three or four etc., and the quantitative design of the second axle 331 becomes
Two, three or four etc., in first group, the quantitative design of rotor group 3 becomes three or four etc., rotor group 3 in second group
Quantitative design become three or four etc., may also apply to this utility model, only need to by corresponding quantitative relation according to
Above-mentioned correspondence, then all within protection domain of the present utility model.
In this utility model embodiment, between rotor group 3 and second driving shaft 412 or the 4th power transmission shaft 422
Transmission for, can also be attached by a variable pitch device 6, as shown in Figure 3.It should be noted that each rotor
Group 3 and each second driving shaft 412 or the 4th power transmission shaft 422 between transmission, all by an above-mentioned variable pitch device 6
It is attached, therefore in order to describe simplification, this utility model embodiment is only described in detail to a variable pitch device 6.Remaining
Transmission between a corresponding second driving shaft 412 of rotor group 3 or the 4th power transmission shaft 422, directly quotes above-mentioned
Variable pitch device 6.So, please continue to refer to Figure 11-12, described variable pitch device at least includes：Main shaft 61, upper sliding block 62,
Anti-lock mechanism 63, steering wheel 64, power transmission arm 65.Described n rotor 21 is rotationally fixed on main shaft 61, and 62 sets of upper sliding block
It is located on main shaft 61, steering wheel 64 is flexibly connected with anti-lock mechanism 63, anti-lock mechanism 63 is flexibly connected with upper sliding block 62, with
Slided up and down by sliding block 62 upper described in described servo driving.And described power transmission arm 65 slides up and down 52 and institute with described respectively
State rotor 21 connect so that slide up and down 52 slide up and down during, drive described rotor 21 rotated, to change its spiral shell
Away from.Described anti-lock mechanism 63 includes：First rocking arm 631, the second rocking arm 632, locating piece 633.
Specifically, sliding up and down 62 is in hollow structure (column type hollow-core construction), and slides up and down 62 by this hollow
Structure is set on the outer wall of main shaft 61；One end of first rocking arm 631 is flexibly connected with sliding up and down 62；First rocking arm 631
The other end is flexibly connected with one end of the second rocking arm 632；The other end of the second rocking arm 632 is flexibly connected with locating piece 633；Positioning
Block 633 is fixed on second driving shaft or the end of the 4th power transmission shaft.During actual job, one end of the first rocking arm 631
By with slide up and down 62 and be flexibly connected so that the first rocking arm 631 can be with the first rocking arm 631 and the connecting portion sliding up and down 62
Centered on position, point is rotated；The other end of the first rocking arm 631 by being flexibly connected so that with one end of the second rocking arm 632
One rocking arm 631, the second rocking arm 632 each can be put centered on the two connecting portion and be rotated；Second rocking arm 632 another
End is by being flexibly connected with locating piece 633 so that the second rocking arm 632 can be with the connecting portion of the second rocking arm 632 and locating piece 633
Centered on position, point is rotated；The top of steering wheel linking arm 641 is flexibly connected with the sidepiece of the first rocking arm 631；Steering wheel linking arm
641 bottom is connected with steering wheel 64；I.e. steering wheel 64 is capable of transmitting steering wheel thrust to the first rocking arm by steering wheel linking arm 641
631, and then drive the first rocking arm 631 to be swung.
In this utility model embodiment, connect for ease of the first rocking arm 631, the second rocking arm 632, the activity between 62 that slides up and down
Connect, realize relatively rotating between any two；Preferably, one end of the first rocking arm 631 is provided with the first U-shaped portion position 6312；First shakes
Arm 631 is located at, by the U-type groove muzzle of this first U-shaped portion position 6312, the outside sliding up and down 62, and passes through the first U-shaped portion position
6312 are flexibly connected with sliding up and down 62；The other end of the first rocking arm 631 is provided with the first boss 6311；And first is raised
The end at position 6311 offers the first connecting hole；First boss 6311 passes through the first connecting hole and the second rocking arm 632
One end is flexibly connected；One end of second rocking arm 632 is provided with the second U-shaped portion position being adapted with the first boss 6311 shape
6321；First boss 6311 be placed in the second U-shaped portion position 6321 U-type groove mouth internal and pass through the second U-shaped portion position 6321 and
One end of second rocking arm 632 is flexibly connected.The other end of the second rocking arm 632 is provided with the 3rd U-shaped portion position 6322；Locating piece 633
One end be provided with the second boss 6311a being adapted with the U-type groove mouth structure of described 3rd U-shaped portion position；Described second
The end of boss 6311a offers the second connecting hole；And described second boss 6311a is placed in described 3rd U-shaped portion
Inside the U-type groove mouth of position 6322 and by described second connecting hole and the 3rd U-shaped portion set by the described second rocking arm other end
Position 6322 flexible connection.Steering wheel linking arm 641 is in the curved structure of the moon；And the top of steering wheel linking arm 641 is provided with least one
3rd connecting hole；The top of steering wheel linking arm 641 is flexibly connected with the side wall of the first rocking arm 631 by the 3rd connecting hole；Steering wheel
The bottom of linking arm 641 is provided with the 4th U-shaped portion position 651；And the bottom of steering wheel linking arm 641 pass through the 4th U-shaped portion position 651 with
Steering wheel 64 connects.
In this utility model embodiment, by variable pitch device 6, by changing the airfoil angle-of-attack of rotor 21, make profile lift
Change to carry out the regulation of output, maintain rotor 21 rotating speed constant, realized by the pitch changing rotor 21 vertical
Motion, roll motion and divertical motion.Meanwhile, this utility model embodiment is by sliding up and down the 62, first rocking arm 631, steering wheel
Folding mechanical motion mode between linking arm 641 three, and slide up and down the 62, first rocking arm 631, the second rocking arm 632 3
Folding mechanical motion mode between person, overcomes in conventional art because steering wheel connecting rod its own mechanical structure (vertical bar shape) is in place
Put limitation spatially so that main shaft 61 easily cannot fall because steering wheel linking arm 641 is long in lifting process completely,
The situation causing rotor 21 locking occurs；If steering wheel linking arm 641 is too short simultaneously and main shaft cannot be gone up in uphill process
It is raised to the defect of setting position.
Obviously, those skilled in the art can carry out various changes and modification without deviating from this practicality to this utility model
New spirit and scope.So, if of the present utility model these modification and modification belong to this utility model claim and
Within the scope of its equivalent technologies, then this utility model is also intended to comprise these changes and modification.
Claims (10)
1. a kind of power-equipment being applied to unmanned plane is it is characterised in that the described power-equipment being applied to unmanned plane includes：
First single-cylinder engine, described first single-cylinder engine is provided with first axle；
Second single-cylinder engine, described second single-cylinder engine is provided with the second axle；
Trigger, described trigger is flexibly connected with described first axle and described second axle respectively, to be opened by described trigger
Move described first axle and described second axle rotation；
Terminal pad；Described first single-cylinder engine passes through described terminal pad, described second single-cylinder engine by described first axle
Described terminal pad is passed through by described second axle, with by described terminal pad by described first single-cylinder engine and described second singly
Cylinder engine connects as one；
Air cooling system, described air cooling system be fixed on described first single-cylinder engine and described second single-cylinder engine so that
Extraneous cold air is inhaled in described first single-cylinder engine and described second single-cylinder engine by described air cooling system, with
Described first single-cylinder engine and/or described second single-cylinder engine are cooled down.
2. it is applied to the power-equipment of unmanned plane as claimed in claim 1 it is characterised in that also including：
First carburator, described first carburator is connected with the oil-in of described first single-cylinder engine；
Second carburator, described second carburator is connected with the oil-in of described second single-cylinder engine；
Wherein, the comburant in the cylinder body of described first single-cylinder engine is injected into by described first carburator, and described second
Comburant in the cylinder body of single-cylinder engine is injected into by described second carburator.
3. be applied to the power-equipment of unmanned plane as claimed in claim 1 it is characterised in that
One first shaft gear is arranged with described first axle；
One second shaft gear is arranged with described second axle；
Described trigger is meshed with described first shaft gear and described second shaft gear respectively by a starter receiver, so that institute
State first axle and the direction of rotation of described second axle is contrary.
4. it is applied to the power-equipment of unmanned plane as claimed in claim 3 it is characterised in that described terminal pad includes：
First lid；
Second lid；
Wherein, described first lid and described second lid detachable connection, and in described first lid and described second lid
It is formed with an accommodation space, described first shaft gear, described second shaft gear and described starter receiver are located at described appearance between body
It is empty interior.
5. be applied to the power-equipment of unmanned plane as claimed in claim 4 it is characterised in that
Described detachable connection is bolt connection or mode connects for screw.
6. the power-equipment being applied to unmanned plane as described in any one of claim 1-5 it is characterised in that
Described first axle and described second axle are parallel to each other；And
Described first axle and described second axle are perpendicular with described terminal pad respectively.
7. be applied to the power-equipment of unmanned plane as claimed in claim 1 it is characterised in that
The direction of rotation of described first axle and described second axle is contrary.
8. be applied to the power-equipment of unmanned plane as claimed in claim 1 it is characterised in that
Described first single-cylinder engine and described second single-cylinder engine are with the center vertical pivot of described terminal pad for symmetrical axial symmetry
Distribution.
9. it is applied to the power-equipment of unmanned plane as claimed in claim 1 it is characterised in that also including：
First row gas tank；
Second row gas tank；
Wherein, described first row gas tank is fixed on the bottom of described first horizontal bar electromotor, and with described first single-cylinder engine
Cylinder body communicate；Described second row gas tank is fixed on the bottom of described second single-cylinder engine, and with described second single-cylinder engine
The cylinder body of machine communicates.
10. be applied to the power-equipment of unmanned plane as claimed in claim 9 it is characterised in that
Described first row gas tank and described first single-cylinder engine bolt connection or welding；
And/or,
Described second row gas tank and described second single-cylinder engine bolt connection or welding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620805741.1U CN205971825U (en) | 2016-07-28 | 2016-07-28 | Be applied to unmanned aerial vehicle's power equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620805741.1U CN205971825U (en) | 2016-07-28 | 2016-07-28 | Be applied to unmanned aerial vehicle's power equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205971825U true CN205971825U (en) | 2017-02-22 |
Family
ID=58027796
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620805741.1U Expired - Fee Related CN205971825U (en) | 2016-07-28 | 2016-07-28 | Be applied to unmanned aerial vehicle's power equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205971825U (en) |
-
2016
- 2016-07-28 CN CN201620805741.1U patent/CN205971825U/en not_active Expired - Fee Related
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