CN206407120U - A kind of new multi-rotor unmanned aerial vehicle - Google Patents
A kind of new multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN206407120U CN206407120U CN201621437672.XU CN201621437672U CN206407120U CN 206407120 U CN206407120 U CN 206407120U CN 201621437672 U CN201621437672 U CN 201621437672U CN 206407120 U CN206407120 U CN 206407120U
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- aerial vehicle
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Abstract
The utility model discloses a kind of new multi-rotor unmanned aerial vehicle, including frame (1), power set (2), rotor (3), also include transmission device (4), transmission device (4) is fixed in frame (1) by unilateral bearing (5)；Rotor (3) is fixed in frame (1) by rotor fix bar (31)；Power set (2) are fixedly connected with frame (1)；Petrol engine (21) is symmetrically fixed on the center line between the adjacent rotor (3) in frame (1)；Fuel tank (22) is symmetrically fixed on the position of centre of gravity of unmanned plane frame (1).The utility model can greatly reduce the vibrations of fuel engines generation, the overall stability of unmanned plane be improved, while also increasing the heavy burden of unmanned plane, endurance.Fuel tank is arranged on frame position of centre of gravity, it is ensured that will not be due to flight oil consumption, the unstable situation for causing fuel tank weight unbalanced and occurring.
Description
Technical field
The utility model design unmanned air vehicle technique field, a kind of new multi-rotor unmanned aerial vehicle of specific design.
Background technology
Unmanned plane is the abbreviation (Unmanned Aerial Vehicle) of UAV, is to utilize wireless remotecontrol
The not manned aircraft of equipment and the presetting apparatus provided for oneself, including depopulated helicopter, fixed-wing aircraft, multi-rotor aerocraft, nothing
People's dirigible, unmanned parasol.Broadly seeing also includes near space vehicle (20-100 kilometers of spatial domains), such as stratospheric airship,
Aerostat, solar energy unmanned plane etc..From the point of view of certain angle, unmanned plane can complete complicated sky under conditions of unmanned
Middle aerial mission and various loading commissions, can be seen as " air-robot ".
Classify according to different platform configuration, unmanned plane can mainly have fixed-wing unmanned plane, depopulated helicopter and many rotors
The large platform of unmanned plane three, other small species unmanned aerial vehicle platforms also include umbrella wing unmanned plane, flapping wing unmanned plane and unmanned spaceship/spacecraft etc..Gu
Determine the Mainstream Platform that wing unmanned plane is military and most civilian unmanned planes, maximum feature is that flying speed is very fast；Depopulated helicopter
It is flexibility most strong unmanned aerial vehicle platform, can takes off vertically and hover with original place；Many rotor (multiaxis) unmanned planes be consumer level and
The preferred platform of part civil use, flexibility between (landing needs thrust) in the middle of fixed-wing and helicopter, but manipulate it is simple,
Cost is relatively low.
But existing multi-rotor unmanned aerial vehicle, the overwhelming majority is using lithium battery energy supply.Because electro-motor shakes
Dynamic very little, it is easy to control.But it is due to that the general endurance of electro-motor is very low, loading capacity is not high, therefore the straight hair of unmanned plane one
Exhibition progress is slow.
Later, fuel oil is used to occur for the unmanned plane of power, because fuel engines vibrations are larger, vibrations are easy to by sending out
Motivation is sent to Rotary-Wing Department so that fuel oil unmanned plane stability and Reliability comparotive are poor.Meanwhile, the general heat production meeting of fuel engines
Very big, existing unmanned plane typically solves heat dissipation problem using radiator fan is added, so since not only waste the energy,
It also add unmanned plane heavy burden.
Meanwhile, the unmanned plane of prior art, regulation state of flight when, generally by increase or reduce engine exert oneself with
Realize.On the one hand, engine is caused damage, on the other hand whard to control, sensitivity is low.
Utility model content
The utility model provides a kind of new multi-rotor unmanned aerial vehicle, is to improve problems of the prior art.
The technical solution of the utility model is：
A kind of new multi-rotor unmanned aerial vehicle, including frame 1, power set 2, rotor 3, in addition to transmission device 4, transmission dress
Put 4 and the top of frame 1 is fixed on by unilateral bearing 5；Rotor 3 is fixed in frame 1 by rotor fix bar 31；Power set 2 and machine
Frame 1 is fixedly connected；Power set 2 are made up of two petrol engines 21, two fuel tanks 22；Petrol engine 21 is symmetrically fixed on
On the center line between adjacent rotor 3 in frame 1；Fuel tank 22 is symmetrically fixed on the position of centre of gravity of unmanned plane frame 1；Gasoline engine
Machine 21 is connected with transmission device 4, drives the propeller rotational of rotor 3.
Transmission device 4 is by final drive shaft 41, rotary-wing transmission axle 42, shaft coupling 43 and is co-axially located at final drive shaft 41
The bevel gear 44 at two ends is constituted.
Belt pulley 45 is coaxially provided with final drive shaft 41, the main power shaft of belt pulley 45 and petrol engine 21 passes through belt
Drive connection.
Two shaft couplings 43 are arranged with final drive shaft 41.
The bevel gear 44 at the two ends of final drive shaft 41 is engaged with the gear of the one end of rotary-wing transmission axle 42；The one end of rotary-wing transmission axle 42
Engaged with bevel gear 44, the other end is engaged with the gear of rotor 3, the propeller of driving rotor 3 turns under the drive of final drive shaft 41
It is dynamic.
The line shaft 34 of the blade folder 33 and rotor 3 of the propeller blade 32 of rotor 3 is hinged；Being additionally provided with rotor 3 to adjust
Save blade folder 33 and the steering wheel 35 of the angle of line shaft 34；Steering wheel 35 is fixedly connected with blade folder 33.
Damping part 6 is provided between power set 2 and frame 1.
Shock absorbing ring 7 is provided between transmission device 4 and unilateral bearing 5.
Main beneficial effect of the present utility model：
(1) the utility model can greatly reduce the vibrations of fuel engines generation, improve the overall stabilization of unmanned plane
Property, while also increasing the heavy burden of unmanned plane, endurance.
(2) fuel tank is arranged on frame position of centre of gravity, it is ensured that will not due to flight oil consumption, cause fuel tank weight unbalanced and
The unstable situation occurred.
(3) blade folder 33 and the angle of line shaft 34 are changed by steering wheel 35, can be with so as to change the pitch of propeller aircraft
The engine damage due to being caused because of frequently engine power is changed is avoided very much, and considerably increases the manipulation of unmanned plane
Property.
(4) because engine is located at below propeller aircraft, without adding cooling fan again, alleviate unmanned plane and bear certainly
Weight.
(5) due to devising two engines, if an engine failure is stopped working in flight course, another starts
Machine is it is also ensured that unmanned plane normal flight, substantially increases the security of unmanned plane.
(6) it is simple in construction, without cumbersome design, save cost.
Brief description of the drawings
Fig. 1 is top view of the present utility model；
Fig. 2 is front view of the present utility model；
Fig. 3 is side view of the present utility model；
Fig. 4 is the enlarged drawing of the utility model rotor.
Wherein, 1- frames, 2- power set, 21- petrol engines, 22- fuel tanks, 3- rotors, 31- rotor fix bars, 32-
Blade, 33- blades folder, 34- line shafts, 35- steering wheels, 4- transmission devices, 41- final drive shafts, 42- rotary-wing transmission axles, 43- shaft couplings
Device, 44- bevel gears, 45- belt pulleys, 5- unilateral bearings, 6- damping parts, 7- shock absorbing rings.
Embodiment
As shown in figure 1, a kind of new multi-rotor unmanned aerial vehicle of the present utility model, by frame 1, power set 2, rotor 3, biography
Dynamic device 4 is constituted.
As shown in figure 3, unmanned plane each several part is fixed on corresponding site by frame 1, power set 2 are unmanned plane rotor 3
Propeller rotational provides power.The propeller of rotor 3 starts to rotate under the drive of transmission device 4.
Transmission device 4 is fixed on the top of frame 1 by unilateral bearing 5, while being set between unilateral bearing 5 and transmission device 4
There is shock absorbing ring 7.Due to the setting of shock absorbing ring 7, the vibrations produced because of petrol engine are greatly reduced.Unilateral bearing 5 with
Frame 1 is fixedly connected, and transmission device is fixed on into the top of frame 1.
Rotor 3 is fixed in frame 1 by rotor fix bar 31, reduces rotor 3 because the shake that propeller rotates and produces
It is dynamic.
As shown in Fig. 2 power set 2 are made up of two petrol engines 21, two fuel tanks 22；Petrol engine 21 is symmetrical
It is fixed on the center line between the adjacent rotor 3 in frame 1, while being provided between petrol engine 21 and frame 1；Fuel tank 22
The symmetrical position of centre of gravity for being fixed on unmanned plane frame 1, that is, be fixed on the symmetrical both sides of unilateral bearing 5 and the connecting corner of frame 1.By
It is located in engine below propeller aircraft, without adding cooling fan again, unmanned plane itself heavy burden is alleviated, while fuel tank is set
Put in frame position of centre of gravity, it is ensured that will not be due to flight oil consumption, the unstable situation for causing fuel tank weight unbalanced and occurring.
Simultaneously as unmanned plane is provided with two petrol engines 21, one is the increase in whole unmanned plane load-carrying, endurance, and two are
In flight course, if an engine failure is stopped working, another engine is it is also ensured that the safety of unmanned plane, is carried significantly
The high security of unmanned plane.
Petrol engine 21 is connected with transmission device 4, drives the propeller rotational of rotor 3.
Transmission device 4 is by final drive shaft 41, rotary-wing transmission axle 42, shaft coupling 43 and is co-axially located at final drive shaft 41
The bevel gear 44 at two ends is constituted.Belt pulley 45, the active of belt pulley 45 and petrol engine 21 are coaxially provided with final drive shaft 41
Power axle is connected by belt transmission.Petrol engine 21 drives belt pulley 45, and driving final drive shaft 41 is rotated.
Two shaft couplings 43 are arranged with final drive shaft 41.Shaft coupling 43 can be reduced further because of petrol engine 21
The vibrations of generation.
The bevel gear 44 at the two ends of final drive shaft 41 is engaged with the gear of the one end of rotary-wing transmission axle 42；The one end of rotary-wing transmission axle 42
Engaged with bevel gear 44, the other end is engaged with the gear of rotor 3, the spiral of each rotor 3 is driven under the drive of final drive shaft 41
Oar is rotated.
As shown in figure 4, the line shaft 34 of the blade folder 33 and rotor 3 of the propeller blade 32 of rotor 3 is hinged；On rotor 3 also
Provided with blade folder 33 and the steering wheel 35 of the angle of line shaft 34 can be adjusted；Steering wheel 35 is fixedly connected with blade folder 33.
The setting of the propeller of rotor 3, can make unmanned plane by adjusting blade folder 33 with the angle of line shaft 34 to complete to fly
Capable various states, without reducing engine power, damage are caused to engine so as to avoid, also increase unmanned plane can
It is handling.
Described above is only preferred embodiment of the present utility model, it is noted that for the common skill of the art
Art personnel, on the premise of the utility model principle is not departed from, can also make some improvement and supplement, and these improve and supplemented
Also it should be regarded as protection domain of the present utility model.
Claims (8)
1. a kind of new multi-rotor unmanned aerial vehicle, including frame (1), power set (2), rotor (3), it is characterised in that：Also include
Transmission device (4), transmission device (4) is fixed on above frame (1) by unilateral bearing (5)；The rotor (3) is by rotor fix bar
(31) it is fixed in frame (1)；The power set (2) are fixedly connected with frame (1)；The power set (2) are by two vapour
Oil turbine (21), two fuel tank (22) compositions；The petrol engine (21) is symmetrically fixed on the adjacent rotor in frame (1)
(3) on the center line between；The fuel tank (22) is symmetrically fixed on the position of centre of gravity of unmanned plane frame (1)；The petrol engine
(21) it is connected with transmission device (4), the propeller rotational of driving rotor (3).
2. a kind of new multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：The transmission device (4) is by leading
Power transmission shaft (41), rotary-wing transmission axle (42), shaft coupling (43) and the bevel gear for being co-axially located at final drive shaft (41) two ends
(44) constitute.
3. a kind of new multi-rotor unmanned aerial vehicle according to claim 2, it is characterised in that：It is same on the final drive shaft (41)
Axle is provided with belt pulley (45), and belt pulley (45) is connected with the main power shaft of petrol engine (21) by belt transmission.
4. a kind of new multi-rotor unmanned aerial vehicle according to claim 2, it is characterised in that：The final drive shaft (41) on pair
Claim provided with two shaft couplings (43).
5. a kind of new multi-rotor unmanned aerial vehicle according to claim 2, it is characterised in that：Final drive shaft (41) two ends
Bevel gear (44) engaged with the gear of rotary-wing transmission axle (42) one end；Nibbled with bevel gear (44) rotary-wing transmission axle (42) one end
Close, the other end is engaged with the gear of rotor (3), the propeller rotational of driving rotor (3) under final drive shaft (41) drive.
6. a kind of new multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：Rotor (3) the propeller oar
The blade folder (33) and the line shaft (34) of rotor (3) of leaf (32) are hinged；Blade folder (33) can be adjusted by being additionally provided with rotor (3)
With the steering wheel (35) of line shaft (34) angle；Steering wheel (35) is fixedly connected with blade folder (33).
7. a kind of new multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：The power set (2) and machine
Damping part (6) is provided between frame (1).
8. a kind of new multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：The transmission device (4) and list
To between bearing (5) be provided with shock absorbing ring (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621437672.XU CN206407120U (en) | 2016-12-26 | 2016-12-26 | A kind of new multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621437672.XU CN206407120U (en) | 2016-12-26 | 2016-12-26 | A kind of new multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206407120U true CN206407120U (en) | 2017-08-15 |
Family
ID=59552260
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621437672.XU Expired - Fee Related CN206407120U (en) | 2016-12-26 | 2016-12-26 | A kind of new multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206407120U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109484629A (en) * | 2018-09-13 | 2019-03-19 | 嘉兴职业技术学院 | A kind of feather quadrotor |
-
2016
- 2016-12-26 CN CN201621437672.XU patent/CN206407120U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109484629A (en) * | 2018-09-13 | 2019-03-19 | 嘉兴职业技术学院 | A kind of feather quadrotor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170807 Address after: 710075 Shaanxi city of Xi'an province high tech Zone two new road No. 14 Xi'an city public record demonstration block room A107 room 002 Patentee after: Xi'an ice intelligent Aviation Technology Co. Ltd. Address before: High tech Zone 710000 Shaanxi city of Xi'an Province Tang Yan Road East Plaza Garden - Xi'an (two) fourth building 2 unit Patentee before: Xi'an ice innovative Aviation Technology Co. Ltd. |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170815 Termination date: 20191226 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |