CN117751075A

CN117751075A - Oil-electricity hybrid unmanned aerial vehicle, power generation assembly and engine

Info

Publication number: CN117751075A
Application number: CN202180101178.3A
Authority: CN
Inventors: 陈晓宇; 姚远; 李粮; 李文浩; 闫晓坤
Original assignee: SZ DJI Technology Co Ltd
Current assignee: SZ DJI Technology Co Ltd
Priority date: 2021-08-20
Filing date: 2021-08-20
Publication date: 2024-03-22
Also published as: WO2023019580A1

Abstract

The utility model provides a hybrid unmanned aerial vehicle of oil electricity (100), power generation component and engine, hybrid unmanned aerial vehicle of oil electricity (100) include fuselage (10), engine (20), generator (30), oil tank (40), energy storage battery (50) and rectifier (60). The machine body (10) comprises a machine frame (11), a machine arm (12) and a power assembly (13), wherein the machine frame (11) comprises a main body (111) and a foot rest (112) arranged on one side of the main body (111). The engine (20) is mounted on the main body (111), the generator (30) is connected to the engine (20), and the oil tank (40) is connected to the engine (20). The energy storage battery (50) is electrically connected with the generator (30) and the power assembly (13). The rectifier (60) is connected with the generator (30), the energy storage battery (50) and the power assembly (13), and the rectifier (60) is used for converting alternating current output by the generator (30) into direct current. The engine (20) and the generator (30) are arranged on the other side of the main body (111) away from the foot rest (112).

Description

Oil-electricity hybrid unmanned aerial vehicle, power generation assembly and engine

Technical Field

The application relates to the technical field of unmanned aerial vehicles, in particular to a hybrid unmanned aerial vehicle, a power generation assembly and an engine.

Background

Because of the technical limitation of lithium batteries, the existing unmanned aerial vehicle has small vehicle weight and short endurance time, and is not suitable for some use occasions needing large load or long endurance time, such as logistics transportation, electric power inspection and the like. Therefore, the oil-electricity hybrid unmanned aerial vehicle appears on the market, and the oil-electricity hybrid unmanned aerial vehicle adopts an engine to drive a generator to run to generate electricity so as to provide electric energy, so that the carrying capacity and the long-time endurance of the unmanned aerial vehicle can be effectively improved.

The existing oil-electricity hybrid unmanned aerial vehicle on the market is provided with a plurality of engines which are arranged on a foot rest, the foot rest is not enough in rigidity and is not beneficial to the design of a vibration system, the oil-electricity hybrid engine is not provided with a starting motor generally, an external starter is required to start, an operator has to squat down when starting the engine, after the engine is ignited, the operator can easily touch a blade or a horn when away from the unmanned aerial vehicle, and potential safety hazards exist.

Disclosure of Invention

In view of this, this application has proposed oil electricity hybrid unmanned aerial vehicle, power generation module and engine.

The oil electricity that this application first aspect provided moves unmanned aerial vehicle in mixture includes:

the unmanned aerial vehicle comprises a body, a power assembly and a frame, wherein the body comprises a main body and a foot rest arranged on one side of the main body, the arm is mechanically coupled with the main body, and the power assembly is arranged on the arm and is used for providing flight power for the oil-electricity hybrid unmanned aerial vehicle;

an engine mounted to the main body;

a generator connected with the engine and driven by the engine to generate electricity;

the oil tank is connected with the engine through a pipeline and is used for supplying fuel oil to the engine;

The energy storage battery is electrically connected with the generator and the power assembly and is used for storing electric energy output by the generator or outputting electric energy to the power assembly;

the rectifier is connected with the generator, the energy storage battery and the power assembly and is used for converting alternating current output by the generator into direct current and transmitting the direct current to the power assembly or the energy storage battery;

wherein, engine and generator locate the main part is kept away from the opposite side of foot rest.

The power generation assembly that this application second aspect proposed for oil electricity mixes moves unmanned aerial vehicle, power generation assembly includes:

a generator;

the engine is connected with the generator and used for driving the generator to operate so as to generate electricity;

the air guide sleeve is arranged on the engine and comprises an airflow cavity, an air inlet and an air outlet, the air inlet and the air outlet are communicated with the airflow cavity, and a cylinder of the engine is positioned in the airflow cavity;

the fan is arranged at the air inlet or the air outlet or in the air flow cavity and is used for driving air to enter the air flow cavity from the air inlet and diffuse from the air outlet so as to radiate heat of the air cylinder.

An engine according to a third aspect of the present application, for connection to an engine and for running to generate electricity under the drive of the engine, the generator comprising:

a stator;

the rotor is rotationally connected with the stator;

the rotating shaft is rotatably arranged on the stator and is connected with the rotor;

one end of the rotating shaft is provided with a conical hole, and the conical hole is used for being matched with a conical output shaft of the engine.

From foretell technical scheme can see, the oil electricity that this application first aspect provided mixes moves unmanned aerial vehicle, through installing the engine in the main part, for the foot rest, the main part has better rigidity, does benefit to unmanned aerial vehicle vibration system's design, locates engine and generator in the main part moreover and keeps away from the one side of foot rest, and operating personnel is more convenient to leave unmanned aerial vehicle after igniting the engine, can effectively reduce the risk of bumping paddle or horn.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

Fig. 1 is a schematic structural diagram of an oil-electricity hybrid unmanned aerial vehicle according to an embodiment of the present application;

FIG. 2 is a schematic view of an assembly of a fuel tank, a lubricant tank, a fire protection plate and a main body according to an embodiment of the present application;

FIG. 3 is a schematic diagram illustrating an assembly of a stand, a container and an energy storage battery according to an embodiment of the present disclosure;

FIG. 4 is a schematic diagram illustrating an assembly of a rectifier to a horn according to an embodiment of the present application;

FIG. 5 is a schematic diagram of a heat sink according to an embodiment of the present disclosure;

FIG. 6 is an assembled schematic view of an engine and generator according to one embodiment of the present disclosure at a first perspective;

FIG. 7 is an assembled schematic view of an engine and generator according to a second perspective of an embodiment of the present application;

FIG. 8 is a schematic cross-sectional view of a generator according to an embodiment of the present application;

FIG. 9 is a schematic diagram illustrating a connection between a generator and an engine shaft according to an embodiment of the present disclosure;

fig. 10 is a schematic structural diagram of a stator clamping seat according to an embodiment of the present disclosure;

FIG. 11 is a schematic structural view of an end cap of a rotor cartridge according to an embodiment of the present disclosure;

fig. 12 is a schematic layout diagram of a power generation assembly, a fuel tank, an electric control assembly, and an energy storage battery of a hybrid unmanned aerial vehicle according to another embodiment of the present disclosure;

Fig. 13 is a schematic layout diagram of a power generation assembly, a fuel tank, an electric control assembly and an energy storage battery of a hybrid unmanned aerial vehicle according to another embodiment of the present application;

fig. 14 is a schematic layout diagram of a power generation assembly, a fuel tank, an electric control assembly, and an energy storage battery of another embodiment of the hybrid unmanned aerial vehicle on a main body of the hybrid unmanned aerial vehicle.

Detailed Description

The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.

In the description of the present application, it should be understood that the terms "center," "longitudinal," "transverse," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," etc. indicate or are based on the orientation or positional relationship shown in the drawings, merely for convenience of description and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more of the described features. In the description of the present application, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.

Some embodiments of the present application are described in detail below with reference to the accompanying drawings. The following embodiments and features of the embodiments may be combined with each other without conflict.

As shown in fig. 1, an embodiment of the present application provides an oil-electricity hybrid unmanned aerial vehicle 100, which can be applied to application fields with heavy load or long-time sailing required, such as logistics transportation and electric inspection.

The proposed hybrid unmanned aerial vehicle 100 comprises a body 10, an engine 20, a generator 30, an oil tank 40, an energy storage battery 50 and a rectifier 60. The fuselage 10 includes frame 11, horn 12 and power pack 13, and frame 11 includes main part 111 and installs the foot rest 112 in main part 111 one side, and horn 12 and main part 111 mechanical coupling, power pack 13 install in horn 12 for the hybrid unmanned aerial vehicle 100 provides flight power. The engine 20 is mounted to the main body 111, the generator 30 is connected to the engine 20, and is operated to generate electricity by the driving of the engine 20, the fuel tank 40 is connected to the engine 20 through a pipe, and the fuel tank 40 is used to supply fuel to the engine 20. The energy storage battery 50 is electrically connected with the generator 30 and the power assembly 13, and the energy storage battery 50 is used for storing electric energy output by the generator 30 or outputting electric energy to the power assembly 13. The rectifier 60 is connected to the generator 30, the energy storage battery 50 and the power assembly 13, and the rectifier 60 is used for converting the alternating current output by the generator 30 into direct current and transmitting the direct current to the power assembly 13 or the energy storage battery 50. Wherein the engine 20 and the generator 30 are disposed on the other side of the main body 111 away from the foot stand 112.

When the unmanned aerial vehicle is in operation, an operator starts the engine 20, the engine 20 rotates to drive the generator 30 to operate to generate electricity, and alternating current generated by the generator 30 is converted into direct current through the rectifier 60 to be used by the unmanned aerial vehicle, and the direct current is at least used for driving the power assembly 13 to operate. If the electric energy generated by the generator 30 is greater than the electric power consumption of the hybrid unmanned aerial vehicle 100, a part of the electric energy generated by the generator 30 is used for charging the energy storage battery 50, and if the electric energy generated by the generator 30 is less than the electric power consumption of the unmanned aerial vehicle, the energy storage battery 50 is convenient to supplement the electric power consumption required by the hybrid unmanned aerial vehicle 100.

The hybrid unmanned aerial vehicle 100 of oil electricity that this embodiment provided, through installing engine 30 in main part 111, for foot rest 112, main part 111 has better rigidity, does benefit to unmanned aerial vehicle vibration system's design, locates engine 20 and generator 30 in main part 111 moreover and keeps away from the one side of foot rest 112, and operating personnel is more convenient to leave unmanned aerial vehicle after igniting engine 20, can effectively reduce the risk of bumping into paddle or horn 12.

In some embodiments, as shown in fig. 2, the body 111 is an annular frame structure. Through setting up main part 111 into ring frame structure, can effectively reduce the weight of main part 111 to reduce the whole weight of oil electricity hybrid unmanned aerial vehicle 100, reduce power consumption, extension duration. Of course, the main body 111 is not limited to be configured as an annular frame structure, but may be configured as a solid structure or a solid hollow structure or a truss structure, which is specifically determined according to practical design requirements.

In some embodiments, as shown in fig. 2, the body 111 is a rectangular frame structure. The rectangular frame is convenient to manufacture and facilitates the installation of other components. Of course, the frame structure is not limited to a rectangular frame structure, but can be a round frame structure, a triangular frame structure, a polygonal frame structure above a quadrangle or other irregularly shaped frame structures, and the frame structure is specifically determined according to actual design requirements.

In some embodiments, the engine 20 is removably mounted to the body 111. In this design, the engine 20 and maintenance and replacement are facilitated. Alternatively, the engine 20 may be detachably mounted to the main body 111 by screw connection or snap-fit.

In some embodiments, the oil tank 40 is mounted to the body 111. The oil tank 40 has a large weight, the main body 111 has a good rigidity, and the main body 111 can form a good support for the oil tank 40 by mounting the oil tank 40 to the main body 111.

As shown in fig. 2, in some embodiments, the oil tank 40 is disposed inside the main body 111, the main body 111 is provided with a clamping block 1111, the oil tank 40 is provided with a clamping groove 41, and the oil tank 40 is clamped to the main body 111 by the cooperation of the clamping groove 41 and the clamping block 1111. When the oil tank 40 is mounted, the oil tank 40 is moved to the top of the main body 111, the clamping groove 41 is aligned with the clamping block 1111, and then the oil tank 40 is moved downwards, so that the clamping block 1111 is clamped into the clamping groove 41, and the oil tank 40 can be clamped on the inner side wall of the main body 111.

It should be noted that the positions of the clamping block 1111 and the clamping groove 41 may be interchanged, that is, the oil tank 40 may be provided with the clamping block 1111 and the main body 111 may be provided with the clamping groove 41.

As shown in fig. 2, in some embodiments, the electro-pneumatic unmanned aerial vehicle 100 further includes a tank pressing member 70, the tank 40 is provided with a pressing portion 42, one end of the tank pressing member 70 is connected to the main body 111, and the other end of the tank pressing member 70 abuts against the pressing portion 42 to press the tank 40 to the main body 111. Wherein the latch 1111 is used to restrict downward movement of the fuel tank 40, and the fuel tank presser 70 is used to restrict upward movement of the fuel tank 40, thereby positioning the fuel tank 40 on the main body 111. In the case of disassembly, the tank presser 70 is removed from the main body 111, and then the tank 40 is lifted out from the main body 111. Of course, the connection between the oil tank 40 and the main body 111 is not limited to the above-described manner, and for example, in other embodiments, the connection between the oil tank 40 and the main body 111 may be performed by using a bolt fastening manner.

As shown in fig. 2, in some embodiments, the hybrid unmanned aerial vehicle 100 further includes an engine control assembly 80, the engine control assembly 80 being mounted to the fuel tank 40, the engine control assembly 80 being used for operational control of the engine 20. Illustratively, the engine control assembly 80 includes a circuit board and electronic components disposed on the circuit board.

In some embodiments, the outer sidewall of the fuel tank 40 is provided with a first recess 43, and the engine control assembly 80 is embedded within the first recess 43. In this way, by embedding the engine control assembly 80 in the first recess 43 of the fuel tank 40, it is possible to make the structure compact and downsize, and the fuel tank 40 can provide a protective effect to the engine control assembly 80.

Of course, the engine control unit 80 may not be mounted to the oil tank 40, and for example, the engine control unit 80 may be mounted to the frame 11 or the arm 12.

As shown in fig. 2, in some embodiments, a vibration damper 90 is provided between the oil tank 40 and the main body 111. Since the engine control assembly 80 is mounted on the fuel tank 40, the vibration absorbing member 90 is disposed between the fuel tank 40 and the main body 111, so that the vibration of the main body 111 can be reduced from being transmitted to the fuel tank 40 by the vibration absorbing member 90, the occurrence of poor contact of the engine control assembly 80 due to vibration generating components can be avoided, and the reliability of system operation can be improved.

Alternatively, the vibration damper 90 is provided between the tank presser 70 and the pressing portion 42 and between the clamping block 1111 and the bottom surface of the groove of the clamping groove 41, the vibration damper 90 between the tank presser 70 and the pressing portion 42 serves to attenuate the transmission of vibration from the tank presser 70 to the tank 40, and the vibration damper 90 between the clamping block 1111 and the bottom surface of the groove of the clamping groove 41 serves to attenuate the transmission of vibration from the clamping block 1111 to the tank 40. Alternatively, the vibration damping member 90 is a silica gel pad, rubber pad, sponge pad, spring, or the like.

As shown in fig. 2, in some embodiments, the electro-pneumatic unmanned aerial vehicle 100 further includes a fire protection plate 110, the fire protection plate 110 being disposed between the fuel tank 40 and the engine 20. By providing the fire protection plate 110 to separate the engine 20 and the fuel tank 40, heat generated during operation of the engine 20 or other factors that are detrimental to the fuel tank 40 can be prevented from being transferred to the fuel tank 40, and safety performance can be improved.

In some embodiments, the engine control assembly 80 is disposed on a side of the fuel tank 40 facing the engine 20, and a flame retardant panel 110 is mounted to the fuel tank 40 and covers at least the engine control assembly 80. By locating the engine control assembly 80 on the side of the fuel tank 40 facing the engine 20, wiring between the engine control assembly 80 and the engine 20 is facilitated, although the engine control assembly 80 is not limited to being located on the side of the fuel tank 40 facing the engine 20, and may be located in other orientations of the fuel tank 40, depending on the actual design requirements. The fire protection plate 110 covers the engine control assembly 80, and may reduce the influence of heat generated when the engine 20 is operated on the engine control assembly 80. In other embodiments, the fire protection plate 110 covers one side of the fuel tank 40, completely separating the fuel tank 40 from the engine 20.

As shown in fig. 2, in some embodiments, the electro-hybrid unmanned aerial vehicle 100 further includes a lubricant tank 120, the lubricant tank 120 being connected to the engine 20 by a pipe, the lubricant tank 120 being configured to supply lubricant to the engine 20.

In some embodiments, the outer sidewall of the oil tank 40 is provided with a second groove 44, and the oil tank 120 is embedded in the second groove 44. In this design, the lubricant tank 120 and the oil tank 40 may be combined to form a single body, resulting in a compact structure.

Of course, the outer side wall of the oil tank 40 may not be provided with the second groove 44, and the oil tank 120 may be directly mounted on the outer side wall of the oil tank 40 in an exposed manner. For example, in other embodiments, the oil tank 120 may be mounted to the frame 11 or the arm 12.

In some embodiments, the center of gravity of the whole of the engine 20, the generator 30, and the oil tank 40 is located in a central region of the main body 111. The engine 20, the generator 30 and the oil tank 40 have large weight, and the overall gravity center of the engine, the generator 30 and the oil tank 40 is arranged in the central area of the main body 111, so that the unmanned aerial vehicle has high stability when flying, and is beneficial to flying control. The central area refers to an area formed by drawing a circle with a preset radius by taking the center of the main body 111 as a center, and optionally, the size of the central area is within one tenth of the outline of the main body 111, which definition is used below.

As shown in fig. 1, in some embodiments, the hybrid unmanned aerial vehicle 100 further includes an avionics module 130, the avionics module 130 being mounted to the main body 111, the avionics module 130 being used for flight control of the hybrid unmanned aerial vehicle 100. Of course, avionics module 130 is not limited to being mounted to body 111, and avionics module 130 may be mounted to horn 12 or foot rest 112, for example.

In some embodiments, avionics module 130 is disposed on a side of generator 30 facing away from engine 20. In this design, avionics module 130 and fuel tank 40 are disposed on opposite sides of engine 20 to provide weight balancing. Alternatively, the center of gravity of the whole of the engine 20, the generator 30, the fuel tank 40 and the avionics module 130 is located in the central region of the main body 111. Similarly, the center of gravity of the whole formed by the engine 20, the generator 30, the oil tank 40 and the avionics module 130 is located in the center region of the main body 111, so that the unmanned aerial vehicle has high stability when flying, and is beneficial to flight control.

As shown in fig. 1 and 3, in some embodiments, the hybrid unmanned aerial vehicle 100 further includes a cargo box 140, where the cargo box 140 is disposed below the main body 111 and connected to the foot stand 112, and the cargo box 140 is used to carry cargo. By providing the cargo box 140, the oil-electricity hybrid unmanned aerial vehicle 100 can be suitable for the field of logistics transportation. If the hybrid unmanned aerial vehicle 100 is used in the field of electric power inspection and the like, the container 140 may not be provided.

Illustratively, the number of the stand 112 is two, the two stand 112 are disposed on two opposite sides of the main body 111, each stand 112 includes two support columns 1121 and a cross bar 1122 connected to bottom ends of the two support columns 1121, and top ends of the support columns 1121 are connected to the main body 111. The hybrid unmanned aerial vehicle 100 further includes four lifting lugs 150, one end of each lifting lug 150 is connected with one of the support columns 1121, and the other end of the lifting lug 150 is connected with the cargo box 140, so that the cargo box 140 is fixed on the foot stand 112.

In some embodiments, the energy storage battery 50 is mounted on top of the cargo box 140.

As shown in fig. 3, optionally, a fixing bracket 160 is provided at the top of the cargo box 140, and the energy storage battery 50 is fixedly mounted to the fixing bracket 160.

Illustratively, the fixing bracket 160 includes a first bracket 161 and a second bracket 162, and the first bracket 161 and the second bracket 162 enclose to form an accommodating space for accommodating the energy storage battery 50. Optionally, the first bracket 161 is provided with a limiting part for limiting the displacement of the energy storage battery 50 in the Y/Z direction, and the second bracket 162 is used for now displacing the energy storage battery 50 in the X direction. Of course, the energy storage battery 50 is not limited to being mounted to the cargo box 140 by the fixing bracket 160, for example, in other embodiments, the energy storage battery 50 may be directly mounted to the cargo box 140 by bolting.

Optionally, the first bracket 161 and/or the second bracket 162 are configured to be removably coupled to the cargo box 140 to facilitate maintenance or replacement of the energy storage battery 50.

In some embodiments, the center of gravity of the cargo box 140 is located approximately on the centerline of the body 111, and the energy storage battery 50 is located in a middle region at the top of the cargo box 140. With this design mode, stability is high when unmanned aerial vehicle flies, does benefit to the flight control.

As shown in fig. 4, in some embodiments, the power assembly 13 includes a motor 131 and a propeller 132, the motor 131 is mounted on the horn 12, the propeller 132 is mounted on the motor 131, and the propeller 132 rotates to form a propeller disc, wherein the rectifier 60 is mounted on one of the horn 12 and is located in the propeller disc area, so that the airflow formed by the rotation of the propeller 132 blows toward the rectifier 60 for heat dissipation. With this design mode, the air current that has rationally utilized screw 132 to form dispel the heat to rectifier 60, and on the one hand rectifier 60 radiating effect is good, and on the other hand does not need additionally to add the fan and dispel the heat to rectifier 60, simplifies the structure, reduce cost.

In some embodiments, the hybrid unmanned aerial vehicle 100 further includes a heat sink 170, the heat sink 170 is mounted to the horn 12, and the rectifier 60 is mounted to the heat sink 170. Alternatively, the heat sink 170 is a heat sink 170 made of a metal material, such as copper, aluminum, and copper aluminum alloy. Through setting up the radiator 170, the heat that the rectifier 60 produced when the operation can be transmitted fast to the radiator 170 on, and the air current that the rethread screw 132 is rotatory forms takes away the heat on the radiator 170 to play better radiating effect. Of course, the hybrid unmanned aerial vehicle 100 may be provided without the heat sink 170.

As shown in fig. 5, in some embodiments, the heat dissipation member 170 includes a heat dissipation member body 171 and heat dissipation fins 172, the rectifier 60 is mounted on the heat dissipation member body 171, and the heat dissipation fins 172 are disposed on the heat dissipation member body 171, wherein the propeller 132 rotates to form an air flow, and the extending direction of the heat dissipation fins 172 is consistent with the flowing direction of the air flow. The heat dissipation fins 172 can play a role of increasing the heat dissipation area of the heat dissipation member 170, further accelerating the heat dissipation effect, and facilitate the operation of the air flow by setting the extending direction of the heat dissipation fins 172 to be consistent with the flowing direction of the air flow, thereby facilitating the heat dissipation.

As shown in fig. 6 and 7, in some embodiments, the engine 20 is in vibration damping connection with the body 111. When the engine 20 is running, it is a huge vibration source, which has an important effect on other modules of the whole hybrid unmanned aerial vehicle 100, and especially easily causes the problems of sensor failure or element-to-element connection failure. By providing the engine 20 and the main body 111 in vibration-damping connection, it is possible to effectively reduce transmission of vibrations generated when the engine 20 is operated to the main body 111.

In some embodiments, the hybrid unmanned aerial vehicle 100 further includes an adapter plate 180 and a fixing member 190, the engine 20 is mounted on the adapter plate 180, one end of the fixing member 190 is mounted on the main body 111, and the other end of the fixing member 190 is in vibration damping connection with the adapter plate 180.

In some embodiments, the hybrid unmanned aerial vehicle 100 further includes an elastic bushing 210, one end of the elastic bushing 210 is connected with the fixing member 190, and the other end of the elastic bushing 210 is connected with the adapter plate 180.

Illustratively, the number of the elastic bushings 210 and the fixing members 190 is four, and four elastic bushings 210 are mounted at the bottom of the adapter plate 180 and distributed at four corners of the adapter plate 180, and one end of each fixing member 190 is connected to one elastic bushing 210 and the other end is connected to the main body 111. In this way, a balanced vibration damping effect can be achieved for the engine 20, and the vibration damping effect is good. Of course, the number of the elastic bushings 210 and the fixing members 190 is not limited to four, but may be three, five or more, depending on the actual design. The elastic bushing 210 may include a rubber bushing.

It should be noted that the vibration damping connection between the engine 20 and the main body 111 is not limited to the manner of using the elastic bushing 210, for example, in other embodiments, the adapter plate 180 is connected to the main body 111 through a spring to perform vibration damping function, or a vibration damping ball connection is used between the adapter plate 180 and the main body 111 to perform vibration damping function, or a vibration damping pad is provided between the adapter plate 180 and the main body 111 to perform vibration damping function.

As shown in fig. 6 and 7, in some embodiments, the hybrid unmanned aerial vehicle 100 further includes a pod 220 and a fan 230, the pod 220 is sleeved outside the cylinder of the engine 20, the fan 230 is mounted on the pod 220, and the fan 230 is used for driving the air to flow in the pod 220 so as to dissipate heat from the cylinder of the engine 20. By providing the pod 220 and the fan 230, a good heat dissipation effect can be achieved for the engine 20.

Specifically, the air guide sleeve 220 includes an air flow cavity, an air inlet 222 communicating with the air flow cavity, and an air outlet 223 communicating with the air flow cavity, the cylinder of the engine 20 is located in the air flow cavity, the fan 230 is installed at the air inlet 222, and the fan 230 drives the air flow to enter the air flow cavity from the air inlet 222 and to diffuse out from the air outlet 223, so as to carry heat generated during operation of the cylinder of the engine 20. Of course, the fan 230 is not limited to be disposed at the air inlet 222, but may be disposed at the air outlet 223 or disposed inside the airflow chamber, as long as the fan 230 can drive the airflow to enter the airflow chamber from the air inlet 222 and diffuse out from the air outlet 223.

In some embodiments, the air inlet 222 is oriented toward the nose of the hybrid unmanned aerial vehicle 100. In this design, the hybrid unmanned aerial vehicle 100 is advantageous for a large amount of air to flow into the airflow cavity from the air inlet 222 during flight, so as to achieve a better heat dissipation effect on the cylinder of the engine 20.

In some embodiments, the engine 20 includes a cylinder, the number of the fairings 220 is two, the two fairings 220 are respectively installed on two sides of the cylinder to dissipate heat from two sides of the cylinder, the two fairings 220 are spaced apart, and the generator 30 is located between the two fairings 220. In this design mode, two kuppe 220 can follow the both sides of cylinder and dispel the heat to the engine, and the cylinder dispels the heat evenly, and the radiating effect is good, and moreover, engine 20, generator 30, kuppe 220 adopt foretell overall structure, and overall structure is compact, can effectively reduce the volume.

In some embodiments, the engine 20 includes two cylinders, two cylinders are distributed on two sides of the generator 30, the number of the fairings 220 is two, the two fairings 220 are respectively disposed on two sides of the generator 30, and one fairing 220 is sleeved outside each cylinder.

In some embodiments, the engine 20 further includes an exhaust pipe 20a, the exhaust pipe 20a including a connection end and an exhaust end, the connection end being connected with the cylinder, the exhaust end extending toward a first direction, the first direction being an extension direction of a pitch axis of the hybrid unmanned aerial vehicle 100. In this design, the hot air coming out of the exhaust pipe 20a is diffused out from the side of the hybrid unmanned aerial vehicle 100, and is not directly discharged to the oil tank 40 located behind the engine 20, so that the potential safety hazard can be reduced.

It will be appreciated that when the number of cylinders of the engine 20 is two, the number of exhaust pipes 20a is also two, and the two exhaust pipes 20a may extend to the same side of the hybrid unmanned aerial vehicle 100 in the first direction, or to opposite sides of the hybrid unmanned aerial vehicle 100, respectively.

Alternatively, two cylinders are defined as a first cylinder and a second cylinder, the first cylinder and the second cylinder being aligned in a first direction, one of the exhaust pipes 20a being connected to the first cylinder and extending in the first direction to a side of the second cylinder facing away from the first cylinder, and the other exhaust pipe 20a being connected to the second cylinder and extending in the first direction to a side of the first cylinder facing away from the second cylinder.

In some embodiments, the exhaust end of the exhaust pipe 20a is located below the body 111.

As shown in fig. 8 to 11, in some embodiments, the generator 30 includes a stator 31, a rotor 32 and a rotating shaft 33, the rotor 32 is rotatably connected with the stator 31, the rotating shaft 33 is rotatably mounted on the stator 31, the rotor 32 is connected with the rotating shaft 33, the output shaft 21 of the engine 20 is connected with the rotating shaft 33, wherein a conical hole 331 is provided at one end of the rotating shaft 33, the output shaft 21 of the engine 20 is conical, and the output shaft 21 of the engine 20 is inserted into the conical hole 331 and connected with the rotating shaft 33. Through setting up the conical surface cooperation of bell mouth 331 and toper output shaft 21, can make the output shaft 21 and the pivot 33 laminating of engine 20 inseparable, firm in connection is difficult to take place relative rotation for the rotation of output shaft 21 can be maximally transmitted to the pivot 33 of generator 30. Of course, it is also possible that the output shaft 21 of the engine 20 is provided in a cylindrical shape with a cylindrical hole at one end of the rotation shaft 33.

In some embodiments, the other end of the rotary shaft 33 is provided with a fitting hole 332 communicating with the tapered hole 331, the fitting hole 332 being for other components to be connected to the output shaft 21 of the engine 20 through the fitting hole 332. For example, a starter of the engine 20 may be connected to the output shaft 21 of the engine 20 through the fitting hole 332, an operator may start the engine 20 through the starter, or a dynamometer flange may be connected to the output shaft 21 of the engine 20 through the fitting hole 332 to test the operation of the engine 20.

In some embodiments, the stator 31 includes a stator holder 311 and a stator winding 312, the stator holder 311 is provided with a through hole 3111, the rotating shaft 33 is rotatably disposed through the through hole 3111, the stator winding 312 is disposed around the periphery of the stator holder 311, and the stator holder 311 is provided with heat dissipation ribs 3112. In this design, by providing the heat dissipation ribs 3112 on the stator holder 311, the heat dissipation ribs 3112 can function to increase the heat dissipation area, so that heat generated when the generator 30 is operated can be rapidly transferred.

Alternatively, the stator holder 311 includes a first annular portion 3113 and a second annular portion 3114 disposed inside the first annular portion 3113, the first annular portion 3113 is connected to the second annular portion 3114, and the second annular portion 3114 encloses the through hole 3111. The number of the heat dissipation ribs 3112 is plural, and the plurality of heat dissipation ribs 3112 are arranged on the inner side wall of the first annular portion 3113 in a spacing and annularly extend towards the second annular portion 3114. In this design, through being equipped with heat dissipation rib 3112 at stator cassette 311, heat dissipation rib 3112 can play the effect of increase radiating area for the heat that produces when generator 30 is operated can be transmitted away fast, can reduce the use of stator cassette 311 material moreover, reduces the weight of stator cassette 311. Of course, the plurality of heat dissipating ribs 3112 may be disposed to be spaced around the outer sidewall of the second annular portion 3114 and extend toward the first annular portion 3113.

Alternatively, the stator holder 311 is fixed to the housing 22 of the engine 20 by bolts. Thereby mounting the generator 30 to the engine 20.

Optionally, the stator clamping seat 311 further includes a plurality of connection ribs 3115, the plurality of connection ribs 3115 are disposed between the first annular portion 3113 and the second annular portion 3114 at intervals, one end of the connection rib 3115 is connected to the first annular portion 3113, and the other end of the connection rib 3115 is connected to the second annular portion 3114. The heat dissipation ribs 3112 are disposed at intervals from the second annular portion 3114. Illustratively, the number of the connection ribs 3115 is three, and the three connection ribs 3115 are disposed at equal intervals. Alternatively, the bolts fasten the stator holder 311 to the housing 22 of the engine 20 by connecting the connection ribs 3115 and the housing 22 of the engine 20.

In some embodiments, the hybrid unmanned aerial vehicle 100 further includes a bearing assembly 240, the bearing assembly 240 is embedded in the through hole 3111, and the rotating shaft 33 is connected with an inner ring of the bearing assembly 240. In this embodiment, the bearing assembly 240 is provided, so that the rotation between the rotating shaft 33 and the stator clamping seat 311 is stable, which is beneficial to controlling the electromagnetic air gap and the unbalance amount of the rotor, maintaining the electromagnetic performance and reducing the vibration of the generator 30.

Optionally, the bearing assembly 240 includes a first bearing 2401 and a second bearing 2402, the first bearing 2401 is disposed on a side of the stator holder 311 away from the engine 20, and the second bearing 2402 is disposed on a side of the stator holder 311 near the engine 20. Of course, the bearing assembly 240 is not limited to be configured to include two bearings, but may include three or more bearings, depending on the actual design requirements.

In some embodiments, the outer side wall of the rotating shaft 33 is provided with a step 333, and the first bearing 2401 abuts against the step 333. The step 333 may act as a pre-load stop for the first bearing 2401. Optionally, the first bearing 2401 and the step 333 are fixed by glue when mounted. One end of the shaft 33 near the engine 20 may be provided with a copper ring 334 and a snap spring 335 to limit the second bearing 2402, i.e. the step 333, the copper ring 334 and the snap spring 335 together define the bearing assembly 240 on the shaft 33.

In some embodiments, the rotor 32 includes a rotor holder 321 and a permanent magnet 322, the rotor holder 321 is connected to the rotating shaft 33, the permanent magnet 322 is disposed on an inner side wall of the rotor holder 321, and centrifugal fan blades 3211 are disposed on the rotor holder 321, and the centrifugal fan blades 3211 are used for forming an airflow for dissipating heat of the generator 30.

Optionally, the rotor holder 321 includes a cover 3212 and a surrounding wall 3213, the surrounding wall 3213 is disposed around the stator 11, and the permanent magnets 322 are opposite to the stator windings 312. The end cover 3212 is mounted on one end of the rotating shaft 33 far from the engine 20, the end cover 3212 is perpendicular to the extending direction of the rotating shaft 33, and the centrifugal fan blades 3211 are arranged on one side of the end cover 3212 facing the engine 20. Optionally, the number of the centrifugal fan blades 3211 is plural, the centrifugal fan blades 3211 extend along the radial direction of the end cover 3212, and the centrifugal fan blades 3211 are circumferentially spaced around the end cover 3212. When the rotating shaft 33 rotates, the rotor clamping seat 321 is driven to rotate, the rotating rotor clamping seat 321 drives the centrifugal fan blade 3211 to rotate, and the centrifugal fan blade 3211 drives the air to form air flow.

As shown in fig. 12, the embodiment of the present application further provides an oil-electric hybrid unmanned aerial vehicle, where the difference between the oil-electric hybrid unmanned aerial vehicle provided in the present embodiment and the oil-electric hybrid unmanned aerial vehicle described above lies in: in this embodiment, the engine 20 and the generator 30 are combined to form the power generation assembly 500, and the center of gravity of the power generation assembly 500 is located in the center region of the main body 111. The power generation assembly 500 includes a first side 501 and a second side 502 opposite the first side 501, with the fuel tank 40 mounted on top of the body 111 and located on the first side 501 of the power generation assembly 500. The avionics module 130 and the rectifier 60 combine to form an electrical control assembly 600, the electrical control assembly 600 and the energy storage battery 50 being mounted to the body 111 and located on the second side 502 of the power generation assembly.

Alternatively, the center of gravity of the whole of the power generation assembly 500, the electronic control assembly 600, the fuel tank 40, and the energy storage battery 50 is located in the center region of the main body 111.

It should be noted that, during the flying process of the hybrid unmanned aerial vehicle, since the fuel oil in the fuel tank 40 is gradually reduced, the center of gravity of the whole of the power generation assembly 500, the electric control assembly 600, the fuel tank 40 and the energy storage battery 50 is gradually shifted toward the second side 502 of the main body 111, and if the center of gravity of the whole of the power generation assembly 500, the electric control assembly 600, the fuel tank 40 and the energy storage battery 50 is shifted out of the center area of the main body 111, the balance of the hybrid unmanned aerial vehicle is not facilitated. In this embodiment, the center of gravity of the whole of the power generation assembly 500, the electric control assembly 600, the fuel tank 40 and the energy storage battery 50 can be adjusted to be located at the central area of the main body 111 and biased to one side of the fuel tank 40 by fine adjustment of the positions, so that the center of gravity of the whole of the power generation assembly 500, the electric control assembly 600, the fuel tank 40 and the energy storage battery 50 can be gradually shifted to the midpoint of the central area of the main body 111 and then shifted to the second side 502 of the main body 111 during the flying process of the hybrid unmanned aerial vehicle. In this design manner, the center of gravity of the whole of the power generation assembly 500, the electric control assembly 600, the oil tank 40 and the energy storage battery 50 can be always located in the central area of the main body 111, which is beneficial to the balance and flight control design of the hybrid unmanned aerial vehicle.

Alternatively, in the present embodiment, the electronic control unit 600 is located at the top of the main body 111, and the energy storage battery 50 is located at the bottom of the main body 111. It should be noted that the positions of the electric control assembly 600 and the energy storage battery 50 may be interchanged, that is, it is also possible that the electric control assembly 600 is located at the bottom of the main body 111 and the energy storage battery 50 is located at the top of the main body 111.

Optionally, the engine 20 is close to the electric control assembly 600, the generator 30 is close to the oil tank 40, the electric control assembly 600 is located at one side of the advancing direction of the hybrid unmanned aerial vehicle during flight, the engine 20 is slightly higher than the electric control assembly 600, in this design mode, the air can directly strike the engine 20 during flight of the hybrid unmanned aerial vehicle, the engine 20 is cooled, and the electric control assembly 600 does not affect the air intake of the engine 20. It should be noted that, when the energy storage battery 50 is disposed at the top of the main body 111, the engine 20 may also be disposed slightly higher than the energy storage battery 50.

The components and connection relationships of the power generation assembly 500, the fuel tank 40, the electric control assembly 600, and the energy storage battery 50, and other components and connection relationships of the energy storage battery 50 in this embodiment may refer to the above embodiments, and are not described herein.

As shown in fig. 13, the embodiment of the present application further provides an oil-electric hybrid unmanned aerial vehicle, where the difference between the oil-electric hybrid unmanned aerial vehicle provided in the present embodiment and the oil-electric hybrid unmanned aerial vehicle described above lies in: the engine 20 and the generator 30 combine to form a power generation assembly 500, with the center of gravity of the power generation assembly 500 being located in a central region of the main body 111. The power generation assembly 500 includes a first side 501 and a second side 502 opposite the first side 501, and the energy storage cell 50 is mounted to the body 111 and located on the first side 501 of the power generation assembly 500. The avionics module 130 and the rectifier 60 combine to form an electronic control assembly 600, the electronic control assembly 600 being mounted to the body 111 and located on the second side 502 of the power generation assembly 500. The oil tank 40 is mounted to the main body 111, and the center of gravity of the oil tank 40 is located in the center region of the main body 111.

With the layout mode, the unmanned aerial vehicle can play a role in balancing the oil-electricity hybrid unmanned aerial vehicle, and is beneficial to flight control design. Moreover, since the fuel in the fuel tank 40 is gradually reduced when the hybrid unmanned aerial vehicle flies, the gravity center of the hybrid unmanned aerial vehicle may be changed, which is not beneficial to the flight control design. By locating the center of gravity of the fuel tank 40 in the center region of the main body 111, even if the fuel in the fuel tank 40 is reduced, the center of gravity will not be greatly shifted, which plays an important role in balancing the hybrid unmanned aerial vehicle.

Alternatively, the center of gravity of the whole of the power generation assembly 500, the electronic control assembly 600, the fuel tank 40, and the energy storage battery 50 is located at the center region of the main body 111.

Alternatively, the number of the oil tanks 40 may be one or more. When the number of the fuel tanks 40 is one, the energy storage battery 50 and the electronic control unit 600 may be provided at the top of the main body 111, the fuel tank 40 may be provided at the bottom of the main body 111, and the fuel tank 40 may be installed at the middle of the main body 111 such that the center of gravity of the fuel tank 40 is located at the center region of the main body 111. When the number of the oil tanks 40 is plural, the plurality of oil tanks 40 may be disposed at the bottom of the main body 111, the plurality of oil tanks 40 are symmetrically disposed with respect to the center of the main body 111, and the plurality of oil tanks 40 are communicated through pipes.

Illustratively, the number of fuel tanks 40 is two, including a first fuel tank 40a and a second fuel tank 40b, the first fuel tank 40a is mounted on the main body 111 and located on the first side 501 of the power generation assembly 500, the second fuel tank 40b is mounted on the main body 111 and located on the second side 502 of the power generation assembly 500, wherein the energy storage battery 50 is located on top of the main body 111, the first fuel tank 40a is located on the bottom of the main body 111, the electrical control assembly 600 is located on top of the main body 111, and the second fuel tank 40b is located on the bottom of the main body 111. The first tank 40a and the second tank 40b are connected by a pipe. The first oil tank 40a and the second oil tank 40b are symmetrically disposed with respect to the center of the main body 111.

It should be noted that the positions of the energy storage battery 50 and the first oil tank 40 may be interchanged, that is, the energy storage battery 50 is located at the bottom of the main body 111, and the first oil tank 40 is located at the top of the main body 111.

It should be noted that the positions of the electronic control assembly 600 and the second oil tank 40 may be interchanged, that is, the electronic control assembly 600 is located at the bottom of the main body 111, and the second oil tank 40 is located at the top of the main body 111.

As shown in fig. 14, the embodiment of the present application further provides an oil-electric hybrid unmanned aerial vehicle, where the difference between the oil-electric hybrid unmanned aerial vehicle provided in the present embodiment and the oil-electric hybrid unmanned aerial vehicle described above lies in: in the present embodiment, the main body 111 includes a first side 111a and a second side 111b opposite to the first side 111a, and the engine 20 and the generator 30 are combined to form a power generation assembly 500, and the power generation assembly 500 is located at the first side 111a of the main body 111. By arranging the power generation assembly 500 to be located on the first side 111a of the main body 111, the engine 20 can directly strike wind when the hybrid unmanned aerial vehicle flies, and a good heat dissipation effect can be achieved on the air cylinder of the engine 20.

Alternatively, in the present embodiment, the energy storage battery 50 is mounted to the main body 111 and located at the second side 111b of the main body 111.

Optionally, in this embodiment, the hybrid unmanned aerial vehicle further includes an avionics module 130, where the avionics module 130 and the rectifier 60 are combined to form an electronic control assembly 600, and the electronic control assembly 600 is mounted on the main body 111 and located on the second side 111b of the main body 111, where the energy storage battery 50 is located on top of the main body 111, and the electronic control assembly 600 is located on bottom of the main body 111. It should be noted that the positions of the energy storage battery 50 and the electric control assembly 600 may be interchanged, that is, the energy storage battery 50 is located at the bottom of the main body 111, and it is also possible that the electric control assembly 600 is located at the top of the main body 111.

Alternatively, in the present embodiment, the oil tank 40 is mounted to the main body 111 and is located between the power generation assembly 500 and the energy storage battery 50. By installing the oil tank 40 between the power generation assembly 500 and the energy storage battery 50, the oil tank 40 can be disposed near the central region of the main body 111, and the problem of serious center of gravity shift of the hybrid unmanned aerial vehicle due to weight reduction of the oil tank 40 can be avoided.

Alternatively, the center of gravity of the whole of the power generation assembly 500, the electronic control assembly 600, the fuel tank 40, and the energy storage battery 50 is located in the center region of the main body 111. With the above design, the whole mass of the power generation assembly 500, the oil tank 40, the electric control assembly 600 and the energy storage battery 50 can be balanced, so that the hybrid unmanned aerial vehicle is stable during flight, and is beneficial to flight control.

In the description of the present application, it should be noted that, unless explicitly stated and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected. Either mechanically or electrically. Can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be.

In this application, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, and may also include the first and second features not being in direct contact but being in contact with each other by way of additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.

The above disclosure provides many different embodiments or examples for implementing different structures of the present application. The components and arrangements of specific examples are described above in order to simplify the disclosure of this application. Of course, they are merely examples and are not intended to limit the present application. Furthermore, the present application may repeat reference numerals and/or letters in the various examples, which are for the purpose of brevity and clarity, and which do not in themselves indicate the relationship between the various embodiments and/or arrangements discussed. In addition, the present application provides examples of various specific processes and materials, but one of ordinary skill in the art may recognize the application of other processes and/or the use of other materials.

In the description of the present specification, reference to the terms "one embodiment," "some embodiments," "illustrative embodiments," "examples," "specific examples," or "some examples," etc., means 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 present application. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

While embodiments of the present application have been shown and described, it will be understood by those of ordinary skill in the art that: many changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the application, the scope of which is defined by the claims and their equivalents.

Claims

An oil-electricity hybrid unmanned aerial vehicle, which is characterized by comprising:

the unmanned aerial vehicle comprises a body, a power assembly and a frame, wherein the body comprises a main body and a foot rest arranged on one side of the main body, the arm is mechanically coupled with the main body, and the power assembly is arranged on the arm and is used for providing flight power for the oil-electricity hybrid unmanned aerial vehicle;

An engine mounted to the main body;

a generator connected with the engine and driven by the engine to generate electricity;

the oil tank is connected with the engine through a pipeline and is used for supplying fuel oil to the engine;

the energy storage battery is electrically connected with the generator and the power assembly and is used for storing electric energy output by the generator or outputting electric energy to the power assembly;

the rectifier is connected with the generator, the energy storage battery and the power assembly and is used for converting alternating current output by the generator into direct current and transmitting the direct current to the power assembly or the energy storage battery;

wherein, engine and generator locate the main part is kept away from the opposite side of foot rest.
The hybrid unmanned aerial vehicle of claim 1, wherein the body is an annular frame structure.
The hybrid unmanned aerial vehicle of claim 1, wherein the engine is removably mounted to the main body.
The hybrid unmanned aerial vehicle of claim 1, wherein the oil tank is mounted to the body.
The hybrid unmanned aerial vehicle of claim 4, wherein the oil tank is disposed on a side of the engine facing away from the generator.
The hybrid unmanned aerial vehicle of claim 4, further comprising:

and the engine control assembly is arranged on the oil tank and is used for controlling the operation of the engine.
The hybrid unmanned aerial vehicle of claim 6, wherein the outer sidewall of the oil tank is provided with a first recess, and the engine control assembly is embedded in the first recess.
The hybrid unmanned aerial vehicle of claim 6, wherein a vibration damper is disposed between the oil tank and the main body.
The hybrid unmanned aerial vehicle of claim 6, further comprising:

and the fireproof plate is arranged between the oil tank and the engine.
The hybrid unmanned aerial vehicle of claim 9, wherein the engine control assembly is disposed on a side of the oil tank facing the engine, and the flame retardant panel is mounted to the oil tank and covers at least the engine control assembly.
The hybrid unmanned aerial vehicle of claim 4, wherein the main body is an annular frame structure, the oil tank is arranged on the inner side of the main body, one of the main body and the oil tank is provided with a clamping groove, the other of the main body and the oil tank is provided with a clamping block, and the oil tank is clamped on the main body through the matching of the clamping groove and the clamping block.
The hybrid unmanned aerial vehicle of claim 11, further comprising:

the oil tank casting die, the oil tank is equipped with the clamping part, the one end of oil tank casting die with the main part is connected, the other end butt of oil tank casting die clamping part with the oil tank compress tightly in the main part.
The hybrid unmanned aerial vehicle of claim 1, further comprising:

and the lubricating oil tank is connected with the engine through a pipeline and is used for supplying lubricating oil to the engine.
The hybrid unmanned aerial vehicle of claim 13, wherein the outer sidewall of the oil tank is provided with a second groove, and the oil tank is embedded in the second groove.
The hybrid unmanned aerial vehicle of claim 1, wherein the center of gravity of the entirety formed by the engine, the generator, and the oil tank is located in a central region of the main body.
The hybrid unmanned aerial vehicle of claim 1, further comprising:

and the avionics module is arranged on the main body and is used for controlling the flight of the oil-electricity hybrid unmanned aerial vehicle.
The hybrid unmanned aerial vehicle of claim 16, wherein the avionics module is disposed on a side of the generator facing away from the engine.
The hybrid unmanned aerial vehicle of claim 1, further comprising:

and the cargo box is arranged below the main body and connected with the foot rest, and is used for bearing cargoes.
The hybrid unmanned aerial vehicle of claim 18, wherein the energy storage battery is mounted on top of the cargo box.
The hybrid unmanned aerial vehicle of claim 19, wherein the center of gravity of the cargo box is located approximately on the centerline of the main body, and the energy storage battery is located in a middle region of the top of the cargo box.
The hybrid unmanned aerial vehicle of claim 1, wherein the power assembly comprises:

the motor is arranged on the horn;

the propeller is arranged on the motor and rotates to form a propeller disc;

the rectifier is arranged on one of the horn arms and is positioned in the propeller disc area, so that air flow formed by rotating the propeller blows to the rectifier to dissipate heat.
The hybrid unmanned aerial vehicle of claim 21, further comprising:

and the radiator is arranged on the horn, and the rectifier is arranged on the radiator.
The hybrid unmanned aerial vehicle of claim 22, wherein the heat sink comprises:

The rectifier is arranged on the radiating piece body;

the radiating fins are arranged on the radiating piece body;

the propeller rotates to form air flow, and the extending direction of the radiating fins is consistent with the flowing direction of the air flow.
The hybrid unmanned aerial vehicle of claim 1, wherein the engine is in vibration damping connection with the main body.
The hybrid unmanned aerial vehicle of claim 24, further comprising:

the adapter plate is arranged on the engine;

and one end of the fixing piece is arranged on the main body, and the other end of the fixing piece is connected with the adapter plate in a vibration reduction way.
The hybrid unmanned aerial vehicle of claim 25, further comprising:

and one end of the elastic bushing is connected with the fixing piece, and the other end of the elastic bushing is connected with the adapter plate.
The hybrid unmanned aerial vehicle of claim 1, further comprising:

the air guide sleeve is sleeved outside the cylinder of the engine;

and the fan is arranged in the air guide sleeve and used for driving gas to flow in the air guide sleeve so as to radiate heat of a cylinder of the engine.
The hybrid unmanned aerial vehicle of claim 1, wherein the generator comprises:

A stator;

the rotor is rotationally connected with the stator;

the rotating shaft is rotatably arranged on the stator, the rotor is connected with the rotating shaft, and an output shaft of the engine is connected with the rotating shaft;

the rotary shaft is characterized in that one end of the rotary shaft is provided with a conical hole, an output shaft of the engine is conical, and the output shaft of the engine penetrates through the conical hole and is connected with the rotary shaft.
The hybrid unmanned aerial vehicle of claim 28, wherein the other end of the shaft is provided with a mounting hole in communication with the tapered hole, the mounting hole being for other components to pass through the mounting hole and connect with the output shaft of the engine.
The hybrid unmanned aerial vehicle of claim 28, wherein the stator comprises:

the stator clamping seat is provided with a through hole, and the rotating shaft can be rotatably arranged through the through hole;

the stator winding is annularly arranged on the periphery of the stator clamping seat;

wherein, the stator cassette is equipped with the heat dissipation rib.
The hybrid unmanned aerial vehicle of claim 30, further comprising:

and the bearing assembly is embedded in the through hole, and the rotating shaft is connected with the inner ring of the bearing.
The hybrid unmanned aerial vehicle of claim 31, wherein the outer sidewall of the shaft is provided with a step, and the bearing assembly comprises at least two bearings, wherein one of the bearings abuts the step.
The hybrid unmanned aerial vehicle of claim 28, wherein the rotor comprises:

the rotor clamping seat is annular;

the permanent magnet is arranged on the inner side wall of the rotor clamping seat;

the rotor clamping seat is provided with centrifugal fan blades, and the centrifugal fan blades are used for forming air flow for radiating the generator.
The hybrid unmanned aerial vehicle of claim 1, wherein the engine and the generator combine to form a power generation assembly, the power generation assembly being located in a central region of the body.
The hybrid unmanned aerial vehicle of claim 34, wherein the power generation assembly comprises a first side and a second side opposite the first side, and wherein the oil tank is mounted to the top of the body and is located on the first side of the power generation assembly.
The hybrid unmanned aerial vehicle of claim 35, further comprising an avionics module, the avionics module and the rectifier in combination forming an electrical control assembly, the electrical control assembly and the energy storage battery each mounted to the main body and located on a second side of the power generation assembly;

wherein one of the electrical control assembly and the energy storage battery is located at the top of the main body, and the other of the electrical control assembly and the energy storage battery is located at the bottom of the main body.
The hybrid unmanned aerial vehicle of claim 36, further comprising:

and the container is arranged below the main body and is connected with the foot rest.
The hybrid unmanned aerial vehicle of claim 34, wherein the power generation assembly comprises a first side and a second side opposite the first side, the energy storage battery being mounted to the body and located on the first side of the power generation assembly.
The hybrid unmanned aerial vehicle of claim 38, further comprising an avionics module, the avionics module and the rectifier in combination forming an electrical control assembly mounted to the main body and located on a second side of the power generation assembly.
The hybrid unmanned aerial vehicle of claim 39, wherein the oil tank comprises:

a first oil tank mounted to the main body and located at a first side of the power generation assembly;

a second oil tank mounted to the main body and located at a second side of the power generation assembly;

wherein one of the energy storage battery and the first oil tank is located at the top of the main body, the other of the energy storage battery and the first oil tank is located at the bottom of the main body, one of the electric control assembly and the second oil tank is located at the top of the main body, and the other of the electric control assembly and the second oil tank is located at the bottom of the main body.
The hybrid unmanned aerial vehicle of claim 40, further comprising:

and the container is arranged below the main body and is connected with the foot rest.
The hybrid unmanned aerial vehicle of claim 1, wherein the body comprises a first side and a second side opposite the first side, the engine and the generator in combination forming a power generation assembly, the power generation assembly being located on the first side of the body.
A hybrid unmanned aerial vehicle as recited in claim 42, wherein the energy storage battery is mounted to the main body and located on a second side of the main body.
The hybrid unmanned aerial vehicle of claim 43, further comprising an avionics module, the avionics module and the rectifier in combination forming an electronic control assembly, the electronic control assembly mounted to the main body and located on a second side of the main body;

wherein one of the energy storage battery and the electrical control assembly is located at the top of the main body, and the other of the energy storage battery and the electrical control assembly is located at the bottom of the main body.
The hybrid unmanned aerial vehicle of claim 44, wherein the oil tank is mounted to the body and is located between the power generation assembly and the energy storage battery.
The hybrid unmanned aerial vehicle of claim 45, further comprising:

and the container is arranged below the main body and is connected with the foot rest.
A power generation assembly for a hybrid unmanned aerial vehicle, the power generation assembly comprising:

a generator;

the engine is connected with the generator and used for driving the generator to operate so as to generate electricity;

the air guide sleeve is arranged on the engine and comprises an airflow cavity, an air inlet and an air outlet, the air inlet and the air outlet are communicated with the airflow cavity, and a cylinder of the engine is positioned in the airflow cavity;

the fan is arranged at the air inlet or the air outlet or in the air flow cavity and is used for driving air to enter the air flow cavity from the air inlet and diffuse from the air outlet so as to radiate heat of the air cylinder.
The power generation assembly of claim 47, wherein the air inlet is oriented toward a nose of the hybrid unmanned aerial vehicle.
The power generation assembly of claim 48, wherein said engine includes a cylinder, said number of said fairings being two, said fairings being mounted on respective sides of said cylinder, said fairings being spaced apart, said generator being located between said fairings.
The power generation assembly of claim 48, wherein said engine comprises two cylinders, said two cylinders being disposed on opposite sides of said generator, said number of said fairings being two, said fairings being disposed on opposite sides of said generator, respectively, one said fairing being disposed over each said cylinder.
The power generation assembly of claim 47, wherein the engine further comprises an exhaust pipe, the exhaust pipe comprising a connection end and an exhaust end, the connection end being connected to the cylinder, the exhaust end extending to a side of the electro-hybrid unmanned aerial vehicle in a first direction, the first direction being a direction of extension of a pitch axis of the electro-hybrid unmanned aerial vehicle.
The power generation assembly of claim 51, wherein said engine includes two cylinders, two of said exhaust pipes, one of said exhaust pipes being connected to each of said cylinders, two of said exhaust pipes extending in said first direction to opposite sides of said hybrid unmanned aerial vehicle.
A generator for connection to an engine and for operating to generate electricity upon actuation of the engine, the generator comprising:

A stator;

the rotor is rotationally connected with the stator;

the rotating shaft is rotatably arranged on the stator and is connected with the rotor;

one end of the rotating shaft is provided with a conical hole, and the conical hole is used for being matched with a conical output shaft of the engine.
The generator of claim 53, wherein the other end of said shaft is provided with a mounting hole in communication with said tapered bore, said mounting hole for other components to pass through said mounting hole for connection with an output shaft of said engine.
The generator of claim 53, wherein said stator comprises:

stator cassette is equipped with the through-hole, the pivot rotatable wear to locate the through-hole:

the stator winding is annularly arranged on the periphery of the stator clamping seat;

wherein, the stator cassette is equipped with the heat dissipation rib.
The generator of claim 55, wherein said stator cartridge comprises:

a first annular portion;

the second annular part is arranged on the inner side of the first annular part and is connected with the first annular part;

the number of the radiating ribs is a plurality, and the radiating ribs are arranged on the inner side wall of the first annular part in a spacing mode and extend towards the second annular part, or the radiating ribs are arranged on the outer side wall of the second annular part in a spacing mode and extend towards the first annular part.
The generator of claim 55, further comprising a bearing assembly embedded within said throughbore, said shaft coupled to an inner race of said bearing assembly.
The generator of claim 53, wherein said rotor comprises:

the rotor clamping seat is connected with the rotating shaft;

the permanent magnet is arranged on the inner side wall of the rotor clamping seat;

the rotor clamping seat is provided with centrifugal fan blades, and the centrifugal fan blades are used for forming heat dissipation air flow.
The generator of claim 58, wherein said rotor cartridge comprises an end cap mounted to an end of said shaft remote from said engine, said centrifugal fan blades being disposed on a side of said end cap facing said engine.