CN206417203U - Unmanned Aerial Vehicle Powerplants - Google Patents
Unmanned Aerial Vehicle Powerplants Download PDFInfo
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- CN206417203U CN206417203U CN201720043494.0U CN201720043494U CN206417203U CN 206417203 U CN206417203 U CN 206417203U CN 201720043494 U CN201720043494 U CN 201720043494U CN 206417203 U CN206417203 U CN 206417203U
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- aerial vehicle
- unmanned aerial
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- shaft coupling
- shaft
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Abstract
The utility model is related to aeropropulsion system field, particularly a kind of small volume for being mainly used in unmanned plane field, lightweight and high functional reliability Unmanned Aerial Vehicle Powerplants.TRT and reduction box are disposed with along the axis of the output shaft outbound course of turboshaft engine；Transmission shafts bearing is provided with reduction box, power transmission shaft left end is with reduction box internal drive and with transmission shafts bearing by bearing fit, and right-hand member is driven with output shaft to be coordinated；TRT includes stator and rotor, and stator is fixed on the right side of transmission shafts bearing, and power transmission shaft passes freely through stator；Rotor is sleeved on power transmission shaft.Unmanned Aerial Vehicle Powerplants of the present utility model, pass through the cooperation of turboshaft engine, power transmission shaft, reduction box, stator and rotor etc., also output power while power is provided for unmanned plane, with the characteristics of simple in construction, weight is small, occupancy cabin inner volume is few, and can generate electricity simultaneously driving unmanned plane rotor and onboard electrical equipment, it is easy to use.
Description
Technical field
The utility model is related to aviation power field, particularly a kind of small volume for being mainly used in unmanned plane field, again
Measure the light and high Unmanned Aerial Vehicle Powerplants of functional reliability.
Background technology
The conventional dynamical system of depopulated helicopter can be divided mainly into driven by power mode and the major class of fuel oil type of drive two.
Power-driven system is by battery power, and power output is low, and cruising time is shorter, the electricity included in power-driven system
Pond occupancy cabin volumes are more, and construction weight is big, and functional reliability is not good enough under low-temp low-pressure environment, battery when working long hours
Caloric value is larger, and security risk is brought to other equipment in depopulated helicopter cabin.In addition, precharge is needed when use,
It is quite inconvenient.
Oil burning power system is based on piston aviation engine, and fuel expands in gas in-cylinder combustion, drives piston reciprocating
Motion, shaft power is exported by crankshaft connecting rod system.Acutely, noise is big, complicated in mechanical structure for piston-mode motor operational shock,
Maintaining is inconvenient, and long-play needs to install reinforcing cooling device additional and carries working medium, greatly increases power system architecture
Weight.When being powered using generator for airborne equipment, transmission shifting mechanism need to be additionally installed, both increase weight, power is reduced again
System global reliability.
Utility model content
In view of this, the purpose of this utility model is to overcome the deficiencies in the prior art there is provided a kind of small volume, lightweight
And the high Unmanned Aerial Vehicle Powerplants of functional reliability.
The utility model solves its technical problem and uses the technical scheme to be：Unmanned Aerial Vehicle Powerplants, including whirlpool axle start
Machine, TRT and reduction box are disposed with along the axis of the output shaft outbound course of the turboshaft engine；Also include biography
Be provided with transmission shafts bearing on moving axis, described reduction box, described power transmission shaft left end with reduction box internal drive and with biography
Moving axis bearing block is by bearing fit, and right-hand member is driven with output shaft to be coordinated；Described TRT includes stator and rotor, described
Stator be fixed on the right side of transmission shafts bearing, described power transmission shaft passes freely through stator；Described rotor is sleeved on biography
On moving axis, stator right-hand member is matched with.
Further, for convenience of installing/dismounting, maintained equipment, described power transmission shaft is matched somebody with somebody by shaft coupling with output shaft transmission
Close.
Further, described shaft coupling includes shaft coupling input disc and shaft coupling output panel, described shaft coupling input
Disk right-hand member is fixedly connected with output shaft, and left end is connected with the right-hand member of shaft coupling output panel, the left end of described shaft coupling output panel
It is connected with power transmission shaft.
Further, to reduce the influence that vibration is caused to flight, stability and reliability are improved, described shaft coupling is defeated
Enter and flexible connection transition block is provided between disk and shaft coupling output panel.
Further, described flexible connection transition block is made using elastic caoutchouc.
Further, described flexible connection transition block is made using nylon material.
Further, described flexible connection transition block is made using polyurethane material.
Further, described stator is that flywheel-type is cylindric, and multiple coils have been evenly arranged along the cylinder of the cylinder；Institute
The rotor stated is the cylindrical shape for covering the stator, is evenly arranged with multiple permanent magnetic iron blocks on the cylinder face of described rotor, this is forever
Magnet piece and fitting coils.
Further, in order to improve stability and unfailing performance, the right side of described rotor and shaft coupling output panel
Connection.
Further, in order to which minimizing electrostatic disturbs the precise electronic component in unmanned plane, described reduction box, generate electricity dress
Put and turboshaft engine is coated with Anti-static paint.
The beneficial effects of the utility model are：Unmanned Aerial Vehicle Powerplants of the present utility model, pass through turboshaft engine, transmission
The cooperation of axle, reduction box, stator and rotor etc., also output power while power is provided for unmanned plane, with structure letter
Single, weight is small, take the characteristics of cabin inner volume is few, and can generate electricity simultaneously driving unmanned plane rotor and onboard electrical equipment,
Using quite convenient.Coordinate because described power transmission shaft is driven by shaft coupling and output shaft, facilitate installation and removal, it is convenient
Safeguard, if described power transmission shaft and output shaft integrated molding are set, the installation and removal of other parts can quite not
It is convenient.Because described shaft coupling includes shaft coupling input disc and shaft coupling output panel, described shaft coupling input disc right-hand member with
Output shaft is fixedly connected, and left end is connected with the right-hand member of shaft coupling output panel, the left end and power transmission shaft of described shaft coupling output panel
Connection, power transmission is realized by the cooperation of shaft coupling input disc and shaft coupling output panel, can be by shaft coupling input disc
Concaveconvex structure is set to realize stable drive in the one side relative with shaft coupling output panel.Due to described shaft coupling input disc and
Flexible connection transition block is provided between shaft coupling output panel, by being flexibly connected the effect of transition block, transmission and can be absorbed
When most of vibration for producing, improve the stability and reliability of machinery, reduce the interference to unmanned plane during flying.Due to described
Stator for flywheel-type it is cylindric, be evenly arranged multiple coils along the cylinder of the cylinder；Described rotor is to cover the stator
Cylindrical shape, be evenly arranged with multiple permanent magnetic iron blocks on the cylinder face of described rotor, the permanent magnetic iron block and fitting coils, cylinder
The rotor of shape and columned stator coordinate so that uniform cutting magnetic induction line, Uniform power reduces the generation of pulse voltage,
Improve the stability and reliability of whole device.Because the right side of described rotor is connected with shaft coupling output panel, auxiliary
Power transmission shaft is connected with shaft coupling, double shield, improves stability and reliability.Due to described reduction box, TRT with
And turboshaft engine is coated with Anti-static paint, interference of the electrostatic to the precise electronic component in unmanned plane is reduced, is improved
Stability and unfailing performance.
Brief description of the drawings
, below will be to embodiment in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art
Or the accompanying drawing used required in description of the prior art is briefly described, it should be apparent that, drawings in the following description are only
It is some embodiments of the present utility model, for those of ordinary skill in the art, is not paying the premise of creative work
Under, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is a kind of configuration schematic diagram of Unmanned Aerial Vehicle Powerplants of the present utility model；
In figure, 1-turboshaft engine；2-shaft coupling input disc；3-flexible connection transition block；4-shaft coupling output panel；
5-rotor；6-stator；7-transmission shafts bearing；8-reduction box.
Embodiment
, below will be to technology of the present utility model to make the purpose of this utility model, technical scheme and advantage clearer
Scheme is described in detail.Obviously, described embodiment is only the utility model one side point embodiment, rather than comprehensively
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not before creative work is made
Resulting all other embodiment is put, the scope that the utility model is protected is belonged to.
Embodiment 1：
As shown in figure 1, Unmanned Aerial Vehicle Powerplants of the present utility model, including turboshaft engine 1, along the turboshaft engine 1
The axis of output shaft outbound course be disposed with TRT and reduction box 8；Also include power transmission shaft, described reduction box
Transmission shafts bearing 7 is provided with 8, described power transmission shaft left end passes through with the internal drive of reduction box 8 and with transmission shafts bearing 7
Bearing fit, right-hand member is driven with output shaft to be coordinated；Described TRT includes stator 6 and rotor 5, and described stator 6 is fixed
In the right side of transmission shafts bearing 7, described power transmission shaft passes freely through stator 6；Described rotor 5 is sleeved on power transmission shaft,
It is matched with the right-hand member of stator 6.Unmanned Aerial Vehicle Powerplants of the present utility model, by turboshaft engine 1, power transmission shaft, reduction box 8, fixed
The cooperation of son 6 and the grade of rotor 5, also output power while power is provided for unmanned plane, with simple in construction, weight it is small,
The characteristics of cabin inner volume is few, and can generate electricity simultaneously driving unmanned plane rotor and onboard electrical equipment are taken, use is quite square
Just.In use, the burning fuel of turboshaft engine 1 is done work, power is exported by output shaft, transmission shaft driven is driven, to reduction box 8
Input power, meanwhile, power transmission shaft rotor driven is rotated occurs magnetic strength wire cutting with stator, generates electricity and is set for other electronics of unmanned plane
Available electricity, of course for the sustainable of power supply is ensured, can also be combined with corresponding battery.It should be noted that being in Fig. 1
Convenience shows the position relationship of miscellaneous part, does not draw power transmission shaft.
Embodiment 2：
As preferred, on the basis of above-described embodiment, the present embodiment does further optimization, and described power transmission shaft passes through
Shaft coupling is driven with output shaft to be coordinated.Coordinate because described power transmission shaft is driven by shaft coupling and output shaft, facilitate installation
And dismounting, maintenance is facilitated, if described power transmission shaft and output shaft integrated molding are set, the peace installation and dismantling of other parts
Unloading can be quite inconvenient.
Embodiment 3：
As preferred, on the basis of above-described embodiment, the present embodiment does further optimization, and described shaft coupling includes
Shaft coupling input disc 2 and shaft coupling output panel 4, the described right-hand member of shaft coupling input disc 2 are fixedly connected with output shaft, left end and connection
The right-hand member connection of axle device output panel 4, the left end of described shaft coupling output panel 4 is connected with power transmission shaft.Due to described shaft coupling
Including shaft coupling input disc 2 and shaft coupling output panel 4, the described right-hand member of shaft coupling input disc 2 is fixedly connected with output shaft, left end
It is connected with the right-hand member of shaft coupling output panel 4, the left end of described shaft coupling output panel 4 is connected with power transmission shaft, defeated by shaft coupling
Power transmission is realized in the cooperation for entering disk 2 and shaft coupling output panel 4, can be by shaft coupling input disc 2 and shaft coupling output panel 4
Set concaveconvex structure to realize stable drive in relative one side, can also be realized by spline or other structures.
Embodiment 4：
As preferred, on the basis of above-described embodiment, the present embodiment does further optimization, described shaft coupling input
Flexible connection transition block 3 is provided between disk 2 and shaft coupling output panel 4.Because described shaft coupling input disc 2 and shaft coupling are defeated
Flexible connection transition block 3 is provided between placing 4, by being flexibly connected the effect of transition block 3, is produced when and transmission can be absorbed
Most of vibration, improve the stability and reliability of machinery, reduce the interference to unmanned plane during flying.
Embodiment 5：
As preferred, on the basis of above-described embodiment, the present embodiment does further optimization, above-mentioned flexible connection
Crossing block 3 can be made using elastic caoutchouc, absorbed and vibrated by elasticity, improve stability.
Embodiment 6：
As preferred, on the basis of above-described embodiment, the present embodiment does further optimization, described flexible connection
Crossing block 3 can be made using nylon material, absorbed and vibrated by elasticity, improve stability.
Embodiment 7：
As preferred, on the basis of above-described embodiment, the present embodiment does further optimization, described flexible connection
Crossing block 3 can be made using polyurethane material, absorbed and vibrated by elasticity, improve stability.
Embodiment 8：
As preferred, on the basis of above-described embodiment, the present embodiment does further optimization, and described stator 6 is winged
It is wheeled cylindric, it has been evenly arranged multiple coils along the cylinder of the cylinder；Described rotor 5 is the cylindrical shape for covering the stator 6,
Multiple permanent magnetic iron blocks are evenly arranged with the cylinder face of described rotor 5, the permanent magnetic iron block and fitting coils.Because described is determined
Son 6 is that flywheel-type is cylindric, and multiple coils have been evenly arranged along the cylinder of the cylinder；Described rotor 5 is to cover the stator 6
Cylindrical shape, is evenly arranged with multiple permanent magnetic iron blocks, the permanent magnetic iron block and fitting coils, cylinder on the cylinder face of described rotor 5
The rotor 5 and columned stator 6 of shape coordinate so that uniform cutting magnetic induction line, Uniform power reduces the production of pulse voltage
It is raw, improve the stability and reliability of whole device.
Embodiment 9：
As preferred, on the basis of above-described embodiment, the present embodiment does further optimization, the right side of described rotor 5
End face is connected with shaft coupling output panel 4.Because the right side of described rotor 5 is connected with shaft coupling output panel 4, attachment driving shaft
It is connected with shaft coupling, double shield improves stability and reliability.
Embodiment 10：
As preferred, on the basis of above-described embodiment, the present embodiment does further optimization, described reduction box 8, hair
Electric installation and turboshaft engine 1 are coated with Anti-static paint.Because described reduction box 8, TRT and whirlpool axle start
Machine 1 is coated with Anti-static paint, reduces interference of the electrostatic to the precise electronic component in unmanned plane, improves stability
And unfailing performance.
Embodiment 11：
As a preferred embodiment, on the basis of above-described embodiment, the present embodiment does further optimization, whirlpool axle
The chemical energy of fuel combustion is converted into the mechanical energy of output shaft rotation, can driven by engine 1 as the power resources of unmanned plane
Drive axis, so as to drive rotor rotational by reduction box 8, can also drive TRT.Flexible clutch is by shaft coupling
Input disc 2, flexible connection transition block 3 and shaft coupling output panel 4 are constituted.The shaft coupling input disc 2 and flexibility of flexible clutch are even
Connect transition block 3 and the output shaft of turboshaft engine 1 is fastened, the profile of flexible connection transition block 3 is opened with the center of shaft coupling output panel 4
The shape of groove is mutually matched, can reliable delivery whirlpool axle behind the relevant position of the flexible connection insertion shaft coupling of transition block 3 output panel 4
The rotary motion of the output shaft of engine 1, can absorb by flexible material and vibrate, reduce resonance harm again.
TRT is made up of rotor 5 with the two parts of stator 6, and shaft coupling output panel 4 is directly connected to the rotor of TRT
5, simplify attachment structure, the center of rotor 5 of TRT is connected with the power transmission shaft of reduction box 8, export rotary motion.In stator 6
It is placed in the cavity of rotor 5 and is fixed on reduction box casing, reduces outside dynamical system appearance and size, cylindric stator 6
Side is evenly arranged some coils.The wall of the rotor 5 of TRT is along the circumferential direction uniformly embedded into permanent magnet blocks, during high-speed rotation
Periodic magnetic flux change can be formed in the coil of stator 6, wire produces induced electromotive force, electricity can be outwards exported after collecting
Can, it is other power electronic equipments.
Lightweight with small volume using turboshaft engine 1 as power resources, power output is high, and mechanical oscillation are small,
The characteristics of functional reliability is high.
Each part is arranged along same axis in Unmanned Aerial Vehicle Powerplants, makes full use of depopulated helicopter axial space, is reduced
Dynamical system lateral dimension, helps to reduce fuselage front face area, reduces air drag, improve flight efficiency.
The coupler structure with flexible excessively contiguous block 3 used in Unmanned Aerial Vehicle Powerplants is simple, easy for installation, just
In disassembling replacing, flexible connection transition block 3 therein can be fitted close by profile with output panel, reliably transmission rotation fortune
It is dynamic, and can be vibrated using itself flexible material characteristic absorption, shaking between the improvement part such as Unmanned Aerial Vehicle Powerplants and fuselage rotor
Dynamic characteristic, reduction resonance harm.
Columned stator 6 and cylindric rotor 5, can be in less occupancy dynamical system space with being filled on the premise of weight
Divide using the higher rotating speed of turboshaft engine 1, improve the power output and delivery efficiency of TRT, meet more large-scale
The power demands of airborne equipment, the mode of being co-axially mounted saves the transmission device of complexity, and rotor 5 and the stator 6 of TRT are distinguished
With miscellaneous part fasten, the two is not directly contacted with, without using bearing etc. support lubricating structure, add electric energy delivery efficiency with
The global reliability of Unmanned Aerial Vehicle Powerplants, the high-speed rotation of rotor 5 can also produce air cooling effect, be below deck equipment cooling, improve
Unmanned plane during flying reliability.
It is described above, embodiment only of the present utility model, but protection domain of the present utility model do not limit to
In this, any one skilled in the art can readily occur in change in the technical scope that the utility model is disclosed
Or replace, it should all cover within protection domain of the present utility model.Therefore, protection domain of the present utility model should be with the power
The protection domain that profit is required is defined.
Claims (10)
1. Unmanned Aerial Vehicle Powerplants, it is characterised in that：Including turboshaft engine (1), the output shaft along the turboshaft engine (1) is defeated
The axis of outgoing direction is disposed with TRT and reduction box (8)；Also include and set on power transmission shaft, described reduction box (8)
Transmission shafts bearing (7) is equipped with, described power transmission shaft left end is with reduction box (8) internal drive and logical with transmission shafts bearing (7)
Bearing fit is crossed, right-hand member is driven with output shaft to be coordinated；Described TRT includes stator (6) and rotor (5), described stator
(6) right side of transmission shafts bearing (7) is fixed on, described power transmission shaft passes freely through stator (6)；Described rotor (5) set
On power transmission shaft, stator (6) right-hand member is matched with.
2. Unmanned Aerial Vehicle Powerplants according to claim 1, it is characterised in that：Described power transmission shaft by shaft coupling with it is defeated
Shaft transmission coordinates.
3. Unmanned Aerial Vehicle Powerplants according to claim 2, it is characterised in that：Described shaft coupling is inputted including shaft coupling
Disk (2) and shaft coupling output panel (4), described shaft coupling input disc (2) right-hand member are fixedly connected with output shaft, left end and shaft coupling
The right-hand member connection of output panel (4), the left end of described shaft coupling output panel (4) is connected with power transmission shaft.
4. Unmanned Aerial Vehicle Powerplants according to claim 3, it is characterised in that：Described shaft coupling input disc (2) and connection
Flexible connection transition block (3) is provided between axle device output panel (4).
5. Unmanned Aerial Vehicle Powerplants according to claim 4, it is characterised in that：Described flexible connection transition block (3) is adopted
It is made with elastic caoutchouc.
6. Unmanned Aerial Vehicle Powerplants according to claim 4, it is characterised in that：Described flexible connection transition block (3) is adopted
It is made with nylon material.
7. Unmanned Aerial Vehicle Powerplants according to claim 4, it is characterised in that：Described flexible connection transition block (3) is adopted
It is made with polyurethane material.
8. Unmanned Aerial Vehicle Powerplants according to claim 1, it is characterised in that：Described stator (6) is flywheel-type cylinder
Shape, multiple coils have been evenly arranged along the cylinder of the cylinder；Described rotor (5) is the cylindrical shape for covering the stator (6), in institute
Multiple permanent magnetic iron blocks are evenly arranged with the cylinder face for the rotor (5) stated, the permanent magnetic iron block and fitting coils.
9. Unmanned Aerial Vehicle Powerplants according to claim 3, it is characterised in that：The right side of described rotor (5) and connection
Axle device output panel (4) is connected.
10. Unmanned Aerial Vehicle Powerplants according to claim 1, it is characterised in that：Described reduction box (8), TRT
And turboshaft engine (1) is coated with Anti-static paint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720043494.0U CN206417203U (en) | 2017-01-13 | 2017-01-13 | Unmanned Aerial Vehicle Powerplants |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720043494.0U CN206417203U (en) | 2017-01-13 | 2017-01-13 | Unmanned Aerial Vehicle Powerplants |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206417203U true CN206417203U (en) | 2017-08-18 |
Family
ID=59571387
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720043494.0U Active CN206417203U (en) | 2017-01-13 | 2017-01-13 | Unmanned Aerial Vehicle Powerplants |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206417203U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106542100A (en) * | 2017-01-13 | 2017-03-29 | 必扬星环（北京）航空科技有限公司 | Unmanned Aerial Vehicle Powerplants |
-
2017
- 2017-01-13 CN CN201720043494.0U patent/CN206417203U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106542100A (en) * | 2017-01-13 | 2017-03-29 | 必扬星环（北京）航空科技有限公司 | Unmanned Aerial Vehicle Powerplants |
| CN106542100B (en) * | 2017-01-13 | 2019-07-16 | 重庆星环航空科技有限公司 | Unmanned Aerial Vehicle Powerplants |
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