CN210455233U

CN210455233U - Oil-electricity hybrid power unmanned aerial vehicle

Info

Publication number: CN210455233U
Application number: CN201921355765.1U
Authority: CN
Inventors: 毛方海; 孙桂祥; 黄桃丽; 孙永劳; 高大帅
Original assignee: Shenzhen Sunwin Intelligent Co Ltd
Current assignee: Shenzhen Sunwin Intelligent Co Ltd
Priority date: 2019-08-20
Filing date: 2019-08-20
Publication date: 2020-05-05
Anticipated expiration: 2029-08-20

Abstract

The utility model relates to a hybrid unmanned aerial vehicle, including casing, oil-electricity hybrid structure, fuselage subassembly and rotor subassembly, oil-electricity hybrid structure arranges the casing in, and oil-electricity hybrid structure includes main power component and vice power component, and main power component is connected with vice power component through first transmission assembly, and main power component is connected with the fuselage subassembly through second transmission assembly, and the fuselage subassembly is connected with the rotor subassembly through third transmission assembly; after the main power assembly outputs power, the auxiliary power assembly and the machine body assembly are driven to work, and the machine body assembly drives the rotor wing assembly to work. The utility model discloses realize that duration is strong, adopt hold-in range transmission mode, simple structure, total power consumption is low.

Description

Oil-electricity hybrid power unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned aerial vehicle, the more specifically gasoline-electric hybrid unmanned aerial vehicle that says so.

Background

An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer.

At present, a multi-rotor unmanned aerial vehicle in the civil market provides power with a pure electric engine or a pure fuel engine, and the pure electric engine is high in stability, simple to operate, wide in application range and poor in cruising ability. And pure fuel engine is relatively poor because many engines simultaneous working uniformity, hardly guarantees that each rotor rotational speed is unanimous, often influences the stability of unmanned aerial vehicle flight, causes certain defect, though there have some novel rotor fuel unmanned aerial vehicle structures on the market at present, the totality is in the theoretical verification stage, and the design is complicated, fuel engine vibratility is great, and the organism design is overweight, and total power consumption is not high, and the totality performance is not good enough.

Therefore, it is necessary to design a new unmanned aerial vehicle, and it is strong to realize duration, simple structure, and total power consumption is low.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to overcome prior art's defect, provide oil-electricity hybrid unmanned aerial vehicle.

In order to achieve the above purpose, the utility model adopts the following technical scheme: the oil-electricity hybrid unmanned aerial vehicle comprises a casing, an oil-electricity hybrid structure, a fuselage assembly and a rotor assembly, wherein the oil-electricity hybrid structure is arranged in the casing, the oil-electricity hybrid structure comprises a main power assembly and an auxiliary power assembly, the main power assembly is connected with the auxiliary power assembly through a first transmission assembly, the main power assembly is connected with the fuselage assembly through a second transmission assembly, and the fuselage assembly is connected with the rotor assembly through a third transmission assembly; through behind the main power component output power, drive vice power component work and fuselage subassembly work, fuselage subassembly drive rotor subassembly work.

The further technical scheme is as follows: the first transmission assembly comprises a first driving wheel, a first driven wheel and a first synchronous belt, the first driving wheel is connected with the main power assembly, the first driven wheel is connected with the auxiliary power assembly, and the main power assembly and the auxiliary power assembly are connected through the first synchronous belt.

The further technical scheme is as follows: the fuselage subassembly includes frame and fuselage transmission assembly, fuselage transmission assembly connect in the frame, fuselage transmission assembly includes driving shaft, fuselage action wheel, first transmission gear and second drive gear, the fuselage action wheel and first transmission gear respectively with the driving shaft is connected, the fuselage action wheel with second transmission assembly connects, second drive gear with the meshing of first transmission gear.

The further technical scheme is as follows: and a driven shaft is inserted into the second transmission gear.

The further technical scheme is as follows: the machine body assembly further comprises a tensioning spring and a tensioning wheel, a sliding groove and a fixed rod are arranged on the machine frame, a sliding rod is arranged in the sliding groove and connected with the tensioning wheel, the tensioning spring is connected between the sliding rod and the fixed rod, and the tensioning wheel is abutted to the second transmission assembly.

The further technical scheme is as follows: the second transmission assembly comprises a second driving wheel and a second synchronous belt, the second driving wheel is connected with the machine body driving wheel through the second synchronous belt, and the tensioning wheel is abutted to the second synchronous belt.

The further technical scheme is as follows: the driving shaft and the driven shaft are respectively connected with the rotor wing assembly through the third transmission assembly.

The further technical scheme is as follows: the rotor subassembly includes left side rotor, left oar seat, right side rotor, right oar seat, left side moving axis and right moving axis, the left side rotor pass through left oar seat with the frame is connected, the right side rotor pass through right oar seat with the frame is connected, the left side rotor with the left side moving axis is connected, the right side rotor with the right side moving axis is connected, the left side moving axis and the right side moving axis respectively with the third transmission assembly is connected.

The further technical scheme is as follows: the third transmission assembly comprises a third driving wheel, a third driven wheel and a third synchronous belt, the driving shaft and the driven shaft are respectively connected with the third driving wheel, the left moving shaft and the right moving shaft are respectively connected with the third driven wheel, and the third driving wheel is connected with the driven wheel through the third synchronous belt.

The further technical scheme is as follows: the rack is provided with a limiting pulley block, the limiting pulley block comprises a first limiting pulley and a second limiting pulley, and the first limiting pulley and the second limiting pulley are arranged on two sides of the third synchronous belt.

Compared with the prior art, the utility model beneficial effect be: the utility model discloses a set up fuel engine as main power component, the generator is as driven power component, utilize first drive assembly to transmit main power component's partial power for driven power component, it is required to satisfy other supplies power of unmanned aerial vehicle, utilize second drive assembly to transmit main power component's another part power to fuselage subassembly, power transmission to the rotor subassembly by third drive assembly with fuselage subassembly again, provide power for rotor subassembly's rotation, realize duration strong, adopt hold-in range transmission mode, moreover, the steam generator is simple in structure, the total energy consumption is low.

The invention is further described with reference to the accompanying drawings and specific embodiments.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without any creative effort.

Fig. 1 is a schematic view of a three-dimensional structure of a hybrid electric unmanned aerial vehicle according to an embodiment of the present invention;

FIG. 2 is a schematic view of a portion of FIG. 1A;

fig. 3 is a schematic perspective view of a second three-dimensional structure of the hybrid electric unmanned aerial vehicle according to an embodiment of the present invention (the left connecting rod and the tension spring are removed);

FIG. 4 is a schematic view of a portion of FIG. 3B;

fig. 5 is a schematic perspective view of a fuselage assembly according to an embodiment of the present invention;

fig. 6 is an exploded view of the fuselage assembly (with the tension springs removed) according to an embodiment of the present invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention will be described in further detail with reference to the accompanying drawings and the following detailed description.

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by those skilled in the art without creative efforts belong to the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and to simplify the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.

In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "secured" are to be construed broadly and can, for example, be connected or detachably connected or integrated; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

In the present disclosure, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact between the first and second features, or may comprise contact between the first and second features not directly. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above should not be understood to necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples described in this specification can be combined and combined by one skilled in the art.

According to the specific embodiment shown in fig. 1-6, the hybrid electric unmanned aerial vehicle provided by the embodiment can be applied to an unmanned scene, and has the advantages of strong cruising ability, simple structure and low total energy consumption.

Referring to fig. 1, the hybrid electric-oil unmanned aerial vehicle includes a housing (not shown in the figure), a hybrid electric-oil structure, a fuselage assembly, and a rotor assembly, wherein the hybrid electric-oil structure is disposed in the housing, the hybrid electric-oil structure includes a main power assembly 11 and an auxiliary power assembly 12, the main power assembly 11 is connected to the auxiliary power assembly 12 through a first transmission assembly, the main power assembly 11 is connected to the fuselage assembly through a second transmission assembly, and the fuselage assembly is connected to the rotor assembly through a third transmission assembly; after the main power assembly 11 outputs power, the auxiliary power assembly 12 and the machine body assembly are driven to work, and the machine body assembly drives the rotor wing assembly to work.

In the present embodiment, the main power assembly 11 includes a fuel engine, and the driven power assembly includes a generator; in other embodiments, the main power assembly 11 may be another power source, and the driven power assembly may be another energy conversion device.

In the embodiment, the fuel engine is used as main power, after the fuel engine is started by refueling, an output shaft of the main power assembly 11 rotates at a high speed, a part of the output shaft drives a rotor of the generator to rotate at a high speed through the first transmission assembly, and direct-current voltage is output according to the magnetic induction line principle and is supplied to other power utilization systems of the unmanned aerial vehicle; the other part of power of the fuel engine is transmitted to the fuselage assembly through the second transmission assembly, and the fuselage assembly drives the rotor transmission set to rotate.

In one embodiment, referring to fig. 1 and 2, the auxiliary power assembly 12 is connected to the housing through a mounting base 13.

In an embodiment, referring to fig. 2, the first transmission assembly includes a first driving pulley 41, a first driven pulley 43 and a first synchronous belt 42, the first driving pulley 41 is connected to the main power assembly 11, the first driven pulley 43 is connected to the secondary power assembly 12, and the main power assembly 11 and the secondary power assembly 12 are connected by the first synchronous belt 42.

Specifically, be connected with first action wheel 41 on foretell main power component 11's the output shaft, be connected with first from driving wheel 43 on the input shaft of vice power component 12, adopt the mode that first synchronous belt 42 connects with first action wheel 41 and first from driving wheel 43, realize power transmission, the transmission flexibility that uses first synchronous belt 42 is good, is applicable to in great environment such as fuel power unmanned aerial vehicle vibration, and stability is high, simple structure, and total energy consumption is low.

In an embodiment, referring to fig. 5 and 6, the above-mentioned body assembly includes a frame 21 and a body transmission assembly, the body transmission assembly is connected to the frame 21, the body transmission assembly includes a driving shaft 28, a body driving wheel 53, a first transmission gear 25 and a second transmission gear 26, the body driving wheel 53 and the first transmission gear 25 are respectively connected to the driving shaft 28, the body driving wheel 53 is connected to the second transmission assembly, and the second transmission gear 26 is engaged with the first transmission gear 25.

In addition, a driven shaft 29 is inserted into the second transmission gear 26.

The machine body assembly and the oil-electricity hybrid power structure realize power transmission through a second transmission assembly; the inside gear drive group that sets up of fuselage subassembly, this gear drive group includes first drive gear 25 and second drive gear 26, first drive gear 25 and the transmission of the 26 meshing of second drive gear, opposite direction, the rotational speed is the same, it rotates to drive the rotor subassembly from this, the rotor subassembly includes left rotor 31 and right side rotor 34, first drive gear 25 and second drive gear 26 correspond and drive left rotor 31 and right side rotor 34 and rotate, the rotor opposite direction of left side rotor 31 and right side rotor 34, offset unmanned aerial vehicle flight torsion, improve unmanned aerial vehicle's flight stability.

In an embodiment, referring to fig. 2, the above-mentioned body assembly further includes a tension spring 23 and a tension wheel 24, the frame 21 is provided with a sliding slot 211 and a fixing rod 242, the fixing rod 242 is fixedly connected to the frame 21, a sliding rod 241 is disposed in the sliding slot 211, the sliding rod 241 can slide in the sliding slot 211, the sliding rod 241 is connected to the tension wheel 24, the tension spring 23 is connected between the sliding rod 241 and the fixing rod 242, and the tension wheel 24 abuts against the second transmission assembly.

Specifically, tension springs 23 are connected to the upper and lower sides of the tension pulley 24, respectively, and the second timing belt 52 is interposed between the two tension springs 23. One end of the tension spring 23 is connected to the sliding bar 241, and the other end of the tension spring 23 is connected to the fixing bar 242.

Specifically, the second transmission assembly includes a second driving wheel 51 and a second synchronous belt 52, the second driving wheel 51 is connected with the body driving wheel 53 through the second synchronous belt 52, the tension wheel 24 abuts against the second synchronous belt 52, and in addition, the second transmission assembly further includes the body driving wheel 53.

The machine body component connected with the oil-electricity hybrid power structure is fixed, but the oil-electricity hybrid power structure has larger vibration when working, when the two are mutually driven to work, the tension of the second synchronous belt 52 is inconsistent, the transmission efficiency is affected, even the second synchronous belt 52 with overlarge vibration is driven to slip, so that the rotor wing assembly is instantaneously stalled, the unmanned aerial vehicle can cause certain potential safety hazard to the flight, so the arrangement of the tension pulley 24 and the tension spring 23 can avoid the occurrence of the slipping phenomenon in the transmission process of the second synchronous belt 52, when the secondary timing belt 52 slips during transmission, the idler 24 is caused to slip by the secondary timing belt 52, thereby driving the sliding rod 241 to slide, the tension spring 23 generates elastic force, reset with drive take-up pulley 24, drive second hold-in range 52 and reset, improve the security and the reliability of whole unmanned aerial vehicle flight.

In an embodiment, referring to fig. 5, the upper end of the frame 21 is connected to a body cover 22, a first cavity is defined between the body cover 22 and the frame 21, and the second synchronous belt 52, the tension pulley 24, the tension spring 23, and the body driving pulley 53 are respectively disposed in the first cavity.

In one embodiment, referring to fig. 3 and 4, the driving shaft 28 and the driven shaft 29 are respectively connected to the rotor assembly through a third transmission assembly.

The number of the third transmission assemblies is two, the driving shaft 28 is connected with the rotor wing assembly through one of the third transmission assemblies, the driven wheel is connected with the rotor wing assembly through the other third transmission assembly, and then the rotor wing assembly is driven to work by the airframe assembly through the two third transmission assemblies.

In one embodiment, referring to fig. 3 to 4, the rotor assembly includes a left rotor 31, a left paddle holder 32, a right rotor 34, a right paddle holder 35, a left moving shaft 37 and a right moving shaft 38, the left rotor 31 is connected to the frame 21 through the left paddle holder 32, the right rotor 34 is connected to the frame 21 through the right paddle holder 35, the left rotor 31 is connected to the left moving shaft 37, the right rotor 34 is connected to the right moving shaft 38, and the left moving shaft 37 and the right moving shaft 38 are respectively connected to the third transmission assembly.

Fuselage subassembly passes through the third transmission subassembly and transmits power to left side rotor 31 and right side rotor 34 respectively to drive left side rotor 31 and right side rotor 34 and carry out work, in order to realize the rotation of left side rotor 31 and right side rotor 34, drive unmanned aerial vehicle's flight.

Specifically, the left paddle seat 32 is connected to the frame 21 through a left connecting rod 33, and the right paddle seat 35 is connected to the frame 21 through a right connecting rod 36.

The left and right connecting

rods

33 and 36 are hollow rods so that the third timing belt 62 is placed inside the left and right connecting

rods

33 and 36.

In one embodiment, the left rotor 31 and right rotor 34 are symmetrically distributed to provide only the lift effect of the drone and not the pitch, roll and yaw of the drone. The power of the left rotor 31 and the right rotor 34 is provided by the output shaft of the main power assembly 11 rotating at high speed and transmitting power through a plurality of groups of synchronous belts.

In addition, the rotor assembly further includes a large rotor propeller, the left rotor 31 is detachably connected to the left movable shaft 37, the detachable structure can be a fastener such as a bolt, and the right rotor 34 is detachably connected to the right movable shaft 38, the detachable structure can be a fastener such as a bolt. Big rotor screw also can adopt fasteners such as bolt to connect on axle 37 and the axle 38 of right side, and is different according to the task load, and left side rotor 31, right side rotor 34 and big rotor screw can be changed, and the rotational speed has the setting for of multiunit synchronous belt drive ratio, and the rotational speed is different, and the pulling force variation in size is decided according to actual conditions, realizes the change of different screws.

In an embodiment, referring to fig. 3 and 4, the third transmission assembly includes a third driving wheel 61, a third driven wheel 63 and a third synchronous belt 62, the driving shaft 28 and the driven shaft 29 are respectively connected to the third driving wheel 61, the left moving shaft 37 and the right moving shaft 38 are respectively connected to the third driven wheel 63, and the third driving wheel 61 and the driven wheel are connected through the third synchronous belt 62.

The third synchronous belt 62 is used for power transmission between the third driving wheel 61 and the third driven wheel 63, and the flexibility is good relative to the transmission of a connecting rod gear, so that the transmission device is particularly suitable for running in a vibration environment of a fuel engine.

In an embodiment, referring to fig. 5 and fig. 6, the frame 21 is provided with a limiting pulley block, the limiting pulley block includes a first limiting pulley 24 and a second limiting pulley 27, and the first limiting pulley 24 and the second limiting pulley 27 are disposed at two sides of the third synchronous belt 62. The first limit pulley 24 and the second limit pulley 27 are used for limiting the transmission path of the synchronous belt, so that the second synchronous belt 52 is prevented from being abraded and affecting safety due to collision of high-speed transmission and other structural parts.

The first limit pulley 24 and the second limit pulley 27 are connected to the inside of the frame 21 by vertical rods, respectively.

Specifically, the number of the limiting pulley blocks is two, and of course, in other embodiments, the number of the limiting pulley blocks may be three or other values.

In an embodiment, referring to fig. 4, a left limit pulley block is disposed in the left paddle seat 32, a right limit pulley block 39 is disposed in the right paddle seat 35, the left limit pulley block abuts against the third synchronous belt 62, and the right limit pulley block 39 abuts against the third synchronous belt 62, so as to limit a transmission path of the third synchronous belt 62, and prevent the third synchronous belt 62 from being worn and affecting safety due to collision between high-speed transmission and other structural members.

In an embodiment, the frame 21 has a second cavity therein, and the first cavity is communicated with the second cavity. The fuselage transmission assembly is disposed in the second cavity.

One fuel engine is used as the main power assembly 11, and an output shaft of the main power assembly 11 rotates at a high speed when in work. The output shaft is the generator with the vice power component 12 of some transmission of power, for the power supply of other power consumption systems of whole unmanned aerial vehicle, the output shaft is with another part transmission fuselage subassembly of power, the fuselage subassembly is with the help of first drive gear 25, second drive gear 26, third action wheel 61, the third is followed driving wheel 63 and third hold-in range 62 and is transmitted power to the rotor subassembly respectively, for the rotation of left side rotor 31 and right side rotor 34 provides lift, only need a fuel engine loading capacity big, as long as fuel is abundant under the theoretical condition, unmanned aerial vehicle duration will be very long, and the while has simple structure, and the control is simple and the advantage that the energy consumption is low.

In addition, limiting pulleys are arranged on the machine body assembly, the left paddle seat 32 and the right paddle seat 35 and rotate along with the corresponding synchronous belts; the left connecting rod 33 and the right connecting rod 36 are prevented from contacting with each other in the high-speed rotation of the corresponding synchronous belt, and the safety is prevented from being affected. Adopt synchronous belt drive, simple structure, transmission efficiency is high, and for being similar to the rigid transmission of connecting rod, synchronous belt drive is flexible good, is applicable to among the great environment such as fuel power unmanned aerial vehicle vibration.

Foretell hybrid unmanned aerial vehicle, through setting up fuel engine as main power component 11, the generator is as driven power component, utilize first drive assembly to transmit main power component 11's partial power for driven power component, it is required to satisfy other power supplies of unmanned aerial vehicle, utilize second drive assembly to transmit main power component 11's another part power to fuselage subassembly, transmit fuselage subassembly's power to rotor subassembly by third drive assembly again, provide power for rotor subassembly's rotation, it is strong to realize the duration, adopt hold-in range transmission mode, moreover, the steam generator is simple in structure, total energy consumption is low.

The technical content of the present invention is further described by the embodiments only, so that the reader can understand it more easily, but the embodiments of the present invention are not limited thereto, and any technical extension or re-creation according to the present invention is protected by the present invention. The protection scope of the present invention is subject to the claims.

Claims

1. The oil-electricity hybrid unmanned aerial vehicle is characterized by comprising a casing, an oil-electricity hybrid structure, a fuselage assembly and a rotor assembly, wherein the oil-electricity hybrid structure is arranged in the casing, the oil-electricity hybrid structure comprises a main power assembly and an auxiliary power assembly, the main power assembly is connected with the auxiliary power assembly through a first transmission assembly, the main power assembly is connected with the fuselage assembly through a second transmission assembly, and the fuselage assembly is connected with the rotor assembly through a third transmission assembly; through behind the main power component output power, drive vice power component work and fuselage subassembly work, fuselage subassembly drive rotor subassembly work.

2. The hybrid unmanned aerial vehicle of claim 1, wherein the first transmission assembly comprises a first driving wheel, a first driven wheel, and a first synchronous belt, the first driving wheel is connected with the main power assembly, the first driven wheel is connected with the secondary power assembly, and the main power assembly and the secondary power assembly are connected through the first synchronous belt.

3. The hybrid electric unmanned aerial vehicle of claim 2, characterized in that, the fuselage subassembly includes frame and fuselage transmission assembly, the fuselage transmission assembly connect in the frame, the fuselage transmission assembly includes driving shaft, fuselage action wheel, first transmission gear and second transmission gear, the fuselage action wheel and first transmission gear respectively with the driving shaft is connected, the fuselage action wheel with the second transmission assembly is connected, second transmission gear with the meshing of first transmission gear.

4. The hybrid unmanned aerial vehicle of claim 3, wherein a driven shaft is inserted into the second transmission gear.

5. The hybrid unmanned aerial vehicle of claim 3 or 4, wherein the body assembly further comprises a tension spring and a tension pulley, the frame is provided with a sliding groove and a fixing rod, the sliding groove is internally provided with a sliding rod, the sliding rod is connected with the tension pulley, the tension spring is connected between the sliding rod and the fixing rod, and the tension pulley abuts against the second transmission assembly.

6. The hybrid unmanned aerial vehicle of claim 5, wherein the secondary transmission assembly comprises a secondary driving wheel and a secondary synchronous belt, the secondary driving wheel is connected with the body driving wheel through the secondary synchronous belt, and the tension wheel abuts against the secondary synchronous belt.

7. The hybrid unmanned aerial vehicle of claim 4, wherein the drive shaft and the driven shaft are connected to the rotor assembly through the third transmission assembly, respectively.

8. The hybrid unmanned aerial vehicle of claim 7, wherein the rotor assembly comprises a left rotor, a left paddle mount, a right rotor, a right paddle mount, a left moving shaft, and a right moving shaft, the left rotor is coupled to the frame via the left paddle mount, the right rotor is coupled to the frame via the right paddle mount, the left rotor is coupled to the left moving shaft, the right rotor is coupled to the right moving shaft, and the left moving shaft and the right moving shaft are coupled to the third transmission assembly, respectively.

9. The hybrid unmanned aerial vehicle of claim 8, wherein the third transmission assembly comprises a third driving wheel, a third driven wheel and a third synchronous belt, the driving shaft and the driven shaft are respectively connected with the third driving wheel, the left moving shaft and the right moving shaft are respectively connected with the third driven wheel, and the third driving wheel is connected with the driven wheel through the third synchronous belt.

10. The hybrid unmanned aerial vehicle of claim 9, wherein the frame is provided with a limiting pulley block, the limiting pulley block comprises a first limiting pulley and a second limiting pulley, and the first limiting pulley and the second limiting pulley are disposed on two sides of the third synchronous belt.