CN206606354U - The opposed hybrid power multi-rotor unmanned aerial vehicle of a kind of pair of fuel engines - Google Patents
The opposed hybrid power multi-rotor unmanned aerial vehicle of a kind of pair of fuel engines Download PDFInfo
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- CN206606354U CN206606354U CN201720284317.1U CN201720284317U CN206606354U CN 206606354 U CN206606354 U CN 206606354U CN 201720284317 U CN201720284317 U CN 201720284317U CN 206606354 U CN206606354 U CN 206606354U
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Abstract
The opposed hybrid power multi-rotor unmanned aerial vehicle of a kind of pair of fuel engines, including frame, it is arranged at the duct of frame central, main lift unit in duct, it is evenly distributed on the multiple electronic rotor systems and the landing chassis below multiple electronic rotor systems of frame surrounding, electronic rotor system includes electronic rotor blade, rotor motor, rotor protective cover, fixed mount, rotor protective cover is connected to shell outside, fix bar is provided with rotor protective cover, fix bar is located on the line at frame central and rotor protective cover center, fix bar end is equipped with rotor motor, electronic rotor blade is in rotor motor, landing chassis is fixed on fix bar lower end, two fuel engines in main lift unit are coaxial, it is opposed to be mounted on duct inner support frame, on the installing plate of lower section, anti- slurry and positive slurry are located at upper respectively, on the fuel engines of lower section;Total, the utility model has the advantages that big loading capacity, cruising time length, fuel oil interest rate are high.
Description
Technical field
The utility model belongs to unmanned air vehicle technique field, and in particular to revolved a kind of pair of opposed hybrid power of fuel engines more
Wing unmanned plane.
Background technology
With society development and technology progress, civilian multi-rotor unmanned aerial vehicle be widely used in take photo by plane, electric power is patrolled
The fields such as inspection, aerial mapping, fire-fighting, real estate, news, agricultural, rescue, but adopted the electric mixing multi-rotor unmanned aerial vehicle of current oil more
Power is provided with separate unit fuel engines, because overcoming the anti-twisted power that separate unit fuel engines is produced with deflector, is carried
Weight is lighter, and cruising time is shorter, and fuel utilization ratio is low, power loss big, to solve the above problems, therefore needing a kind of double combustions
The opposed hybrid power multi-rotor unmanned aerial vehicle of oil turbine.
Utility model content
Main purpose of the present utility model is to provide the high double combustions of a kind of big loading capacity, cruising time length, fuel utilization ratio
The opposed hybrid power multi-rotor unmanned aerial vehicle of oil turbine.
To achieve the above object, the utility model provide a kind of pair of many rotors of the opposed hybrid power of fuel engines nobody
Machine, including frame, be arranged at the duct of frame central, the main lift unit in duct, be evenly distributed on the frame four
Multiple electronic rotor systems and the landing chassis below multiple electronic rotor systems in week, described electronic rotor system include
Electronic rotor blades, rotor motor, rotor protective cover, fix bar, the rotor protective cover are connected to the shell outside, described
The fix bar is provided with rotor protective cover, the fix bar is located at the frame central and the rotor protective cover center
On line, the fix bar end correspondence is provided with the rotor motor, and the output shaft of the rotor motor is located at the rotor
On the central axis of protective cover, it is fixed together with the electronic rotor blades by gland C, the electronic rotor blades are divided into
The electronic rotor blade A rotated clockwise the and electronic rotor blade B rotated counterclockwise, and electronic rotor blade A and electronic rotation
Wing blade B is oppositely oriented, and the landing chassis is fixed on multiple fix bar lower ends, and the main lift unit starts including fuel oil
Machine A, fuel engines B, positive slurry, the anti-support frame starched, right-angled intersection is provided with the duct, the top of support frame as described above,
Lower section is respectively fixed with installing plate A, installing plate B, coaxial, opposed on the installing plate A, installing plate B to be provided with the fuel oil
Engine A, fuel engines B, the fuel engines A, fuel engines B output shaft be located at the duct central axis
On, and be fixedly linked respectively with the positive slurry, anti-slurry by gland B, gland A.
Support frame as described above is that pipe clamp is connected with the installing plate A, installing plate B.
The installing plate A is bolted with the fuel engines A, the installing plate B and fuel engines B
It is bolted.
The positive slurry and the gland B are bolt connection, and the anti-slurry and the gland A are bolt connection.
The fuel engines A2, fuel engines B16 are distributed by Central Symmetry mode.
The beneficial effects of the utility model：The utility model is using double fuel engines, with motor, single fuel engines phase
Than, using the teaching of the invention it is possible to provide bigger power, bigger load is born, while extend cruising time, also, using fuel engines A, combustion
Oil turbine B is coaxial, opposed installation, and positive slurry, anti-slurry are respectively on fuel engines B, fuel engines A, and positive slurry is clockwise
Rotate, anti-slurry is rotated counterclockwise, and fuel engines A, fuel engines B rotating speed are automatically controlled by intelligent throttle control,
So that the anti-twisted power produced in positive slurry, anti-slurry rotation process is cancelled out each other, make flight more stable, so that fuel utilization ratio is improved,
Save the energy.
Brief description of the drawings
Fig. 1 is schematic perspective view of the present utility model.
Fig. 2 is coaxial, the opposed schematic diagram of of the present utility model pair of fuel engines.
Fig. 3 is the enlarged drawing of Fig. 1 gland C, rotor motor and electronic rotor blade.
In figure：1st, frame 2, fuel engines A 3, just starching 4, anti-slurry 5, electronic rotor blades A 6, electronic rotor slurry
Leaf B 7, rotor motor 8, support frame 9, rotor protective cover 10, landing chassis 11, duct 12, fix bar 13, installing plate A
14th, gland A 15, gland C 16, fuel engines B 17, installing plate B 18, gland B D, anti-slurry produce lift direction F,
Positive slurry produces direction H, the unmanned plane ascent direction of lift.
Embodiment
The utility model is described further below in conjunction with the accompanying drawings.
As shown in Figure 1, Figure 2, Figure 3 shows, the opposed hybrid power multi-rotor unmanned aerial vehicle of a kind of pair of fuel engines, including frame 1,
It is arranged at the duct 11 at the center of frame 1, the main lift unit in duct 11, the multiple electricity for being evenly distributed on the surrounding of frame 1
Dynamic rotor system and the landing chassis 10 below multiple electronic rotor systems.The electronic rotor system includes electronic rotor
Leaf, rotor motor 7, rotor protective cover 9, fix bar 12, the rotor protective cover 9 are connected to the outside of frame 1, the rotor
The fix bar 12 is provided with protective cover 9, the fix bar 12 is located in the center of frame 1 and the rotor protective cover 9
On the line of the heart, the end of fix bar 12 correspondence is provided with rotor motor 7, and the output shaft of rotor motor 7 is located at rotor protective cover 9
It is separate between each rotor motor 7 on central axis, adjust the unmanned plane by adjusting the speed of each rotor motor 7
The direction of flight, control flight attitude, the electronic rotor blade and the output shaft of rotor motor 7 are fixed on by gland C15
Together, electronic rotor blades are divided into the electronic rotor blade A5 rotated clockwise and the electronic rotor blade B6 rotated counterclockwise,
And electronic rotor blade A5 and electronic rotor blade B6 are oppositely oriented, electronic rotor blade A5, electronic rotor blade B6 interlock point
Cloth, advantageously ensures that the stability of flight, and landing chassis 10 is fixed on multiple lower ends of fix bar 12.Main lift unit is sent out including fuel oil
Motivation A2, fuel engines B16, just starching 3, it is counter starch the support frame 8 that right-angled intersection is provided with 4, duct 11, support frame 8 it is upper
Side, lower section are respectively fixed with installing plate A13, installing plate B17, coaxial, opposed on installing plate A13, installing plate B17 to be provided with combustion
Oil turbine A2, fuel engines B16, fuel engines A2, fuel engines B16 output shaft are located at the central shaft of duct 11
On line, and it is fixedly linked respectively with positive slurry 3, anti-slurry 4 by gland B18, gland A14, positive slurry 3 is rotated clockwise, arrow in such as Fig. 2
Shown in head D, anti-slurry 4 is rotated counterclockwise, as designated by arrows b in fig, using fuel engines A2, two combustions of fuel engines B16
Oil turbine can provide the unmanned plane and rise more required lift, while larger load can be born, extension continuation of the journey
Time, the anti-twisted power that coaxial, opposed installation contributes to positive slurry 3, anti-slurry 4 to produce is cancelled out each other, so as to improve the utilization rate of fuel oil.
Support frame 8 and installing plate A13, installing plate B17 are that pipe clamp be connected, also can be using welding by the way of, installing plate A13 and
Fuel engines A2 is bolted, and installing plate B17 is bolted with fuel engines B16, positive slurry 3 and gland B18
For bolt connection, anti-slurry 4 and gland A14 is bolt connection, and fuel engines A2, fuel engines B16 press Central Symmetry mode
Distribution, aiutage is distributed in both sides, makes aircraft flight more stable.
When the utility model is implemented：Fuel engines B16, fuel engines A2 start, and drive positive slurry 3 to turn clockwise respectively
Dynamic, anti-slurry 4 is rotated counterclockwise there is provided the lift needed for flight, drives unmanned plane to rise, as shown in arrow E in Fig. 1, meanwhile, point
Cloth is rotated in the driving electric rotor blade A5 of rotor motor 7, the electronic rotor blade B6 of the surrounding of frame 1, by adjusting each rotor
The speed of motor 7, to control the posture that the direction of aircraft operation, adjustment aircraft are run.
While there has been shown and described that embodiment of the present utility model, for the ordinary skill in the art,
It is appreciated that these embodiments can be carried out in the case where not departing from principle of the present utility model and spirit a variety of changes, repaiies
Change, replace and modification, scope of the present utility model is defined by the appended claims and the equivalents thereof.
Claims (5)
1. the opposed hybrid power multi-rotor unmanned aerial vehicle of a kind of pair of fuel engines, including frame（1）, be arranged at frame（1）Center
Duct（11）, positioned at duct（11）Interior main lift unit, it is evenly distributed on the frame（1）Multiple electronic rotors of surrounding
System and the landing chassis below multiple electronic rotor systems（10）, described electronic rotor system includes electronic rotor slurry
Leaf, rotor motor（7）, rotor protective cover（9）, fix bar（12）, the rotor protective cover（9）It is connected to the frame（1）Outside
Side, the rotor protective cover（9）Inside it is provided with the fix bar（12）, the fix bar（12）Positioned at the frame（1）Center
With the rotor protective cover（9）On the line at center, the fix bar（12）End correspondence is provided with the rotor motor（7）,
The rotor motor（7）Output shaft be located at the rotor protective cover（9）Central axis on, it is logical with the electronic rotor blades
Overpressure cap C（15）It is fixed together, the electronic rotor blades are divided into the electronic rotor blade A rotated clockwise（5）And the inverse time
The electronic rotor blade B that pin is rotated（6）, and electronic rotor blade A（5）With electronic rotor blade B（6）It is oppositely oriented, described
Continental shelf（10）It is fixed on multiple fix bars（12）Lower end, it is characterised in that：The main lift unit starts including fuel oil
Machine A（2）, fuel engines B（16）, positive slurry（3）, anti-slurry（4）, the duct（11）The support frame of right-angled intersection is inside installed
（8）, support frame as described above（8）Top, lower section be respectively fixed with installing plate A（13）, installing plate B（17）, in the installing plate A
（13）, installing plate B（17）It is above coaxial, opposed that the fuel engines A is installed（2）, fuel engines B（16）, the fuel oil
Engine A（2）, fuel engines B（16）Output shaft be located at the duct（11）Central axis on, and respectively with it is described just
Slurry（3）, anti-slurry（4）Pass through gland B（18）, gland A（14）It is fixedly linked.
2. the opposed hybrid power multi-rotor unmanned aerial vehicle of a kind of pair of fuel engines according to claim 1, it is characterised in that：
Support frame as described above（8）With the installing plate A（13）, installing plate B（17）Connected for pipe clamp.
3. the opposed hybrid power multi-rotor unmanned aerial vehicle of a kind of pair of fuel engines according to claim 1, it is characterised in that：
The installing plate A（13）With the fuel engines A（2）It is bolted, the installing plate B（17）Start with the fuel oil
Machine B（16）It is bolted.
4. the opposed hybrid power multi-rotor unmanned aerial vehicle of a kind of pair of fuel engines according to claim 1, it is characterised in that：
The positive slurry（3）With the gland B（18）For bolt connection, the anti-slurry（4）With the gland A（14）For bolt connection.
5. the opposed hybrid power multi-rotor unmanned aerial vehicle of a kind of pair of fuel engines according to claim 1, it is characterised in that：
The fuel engines A（2）, fuel engines B（16）It is distributed by Central Symmetry mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720284317.1U CN206606354U (en) | 2017-03-22 | 2017-03-22 | The opposed hybrid power multi-rotor unmanned aerial vehicle of a kind of pair of fuel engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720284317.1U CN206606354U (en) | 2017-03-22 | 2017-03-22 | The opposed hybrid power multi-rotor unmanned aerial vehicle of a kind of pair of fuel engines |
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| Publication Number | Publication Date |
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| CN206606354U true CN206606354U (en) | 2017-11-03 |
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| CN201720284317.1U Active CN206606354U (en) | 2017-03-22 | 2017-03-22 | The opposed hybrid power multi-rotor unmanned aerial vehicle of a kind of pair of fuel engines |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109941429A (en) * | 2019-02-19 | 2019-06-28 | 陈健平 | Unmanned plane |
| CN110304242A (en) * | 2019-05-08 | 2019-10-08 | 吉林大学 | A kind of five axis unmanned planes based on coaxial double-rotary wing ducted fan |
| CN110341940A (en) * | 2019-08-06 | 2019-10-18 | 浙江莱恩克风机有限公司 | A kind of wind resistance rescue unmanned plane of stable movement |
| JP2020128196A (en) * | 2019-02-07 | 2020-08-27 | 愛三工業株式会社 | Multicopter |
-
2017
- 2017-03-22 CN CN201720284317.1U patent/CN206606354U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2020128196A (en) * | 2019-02-07 | 2020-08-27 | 愛三工業株式会社 | Multicopter |
| JP7229874B2 (en) | 2019-02-07 | 2023-02-28 | 愛三工業株式会社 | multicopter |
| CN109941429A (en) * | 2019-02-19 | 2019-06-28 | 陈健平 | Unmanned plane |
| CN110304242A (en) * | 2019-05-08 | 2019-10-08 | 吉林大学 | A kind of five axis unmanned planes based on coaxial double-rotary wing ducted fan |
| CN110341940A (en) * | 2019-08-06 | 2019-10-18 | 浙江莱恩克风机有限公司 | A kind of wind resistance rescue unmanned plane of stable movement |
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