WO2019052530A1

WO2019052530A1 - Hybrid electric unmanned aerial vehicle

Info

Publication number: WO2019052530A1
Application number: PCT/CN2018/105664
Authority: WO
Inventors: 陈翔斌; 王敏
Original assignee: 深圳市旗客智能技术有限公司
Priority date: 2017-09-15
Filing date: 2018-09-14
Publication date: 2019-03-21
Also published as: CN107444630A

Abstract

Disclosed is a hybrid electric unmanned aerial vehicle, comprising a primary frame (1) and two secondary frames (2), two primary rotors (3) respectively arranged at two ends of the primary frame (1), four secondary rotors (4) respectively arranged on the four ends of the two secondary frames (2), a fuel engine, and a plurality of electric engines, wherein the two primary rotors (3) are both powered by the fuel engine; and each of the secondary rotors (4) is respectively powered by one electric engine. The hybrid electric unmanned aerial vehicle cooperatively uses the fuel engine and the electric engines, and the fuel engine drives the two primary rotors (3), so as to provide a lift force and forward power to the unmanned aerial vehicle. The electric engines drive the four secondary rotors (4) to control the attitude of the aerial vehicle, such as pitch, roll and yaw. Only one fuel engine is used to control the two main primary rotors (3), so that various parameters such as the rotational speed of the two primary rotors (3) can easily be consistent, and there is no need to cooperatively use a complex control system for adjusting. The unmanned aerial vehicle has the advantages of having a great load-bearing capacity and a long operable duration. At the same time, the unmanned aerial vehicle has a simple structure and is simple to control, thereby greatly reducing the development and manufacturing cost.

Description

Hybrid electric drone

Technical field

The present application relates to the field of drones, and in particular to an oil-electric hybrid drone.

Background technique

The UAVs currently used in the civilian market are mainly multi-axis (also known as multi-rotor) drones.

The commonly used small drones are powered by pure electric or pure fuel engines. The pure electric engine is easy to handle and has high stability, but its endurance is poor. Pure-fuel engines have high oxygen concentration requirements and poor sensitivity to response control, making it difficult to apply to high-altitude high-speed and areas that require precise positioning or stabilization of aircraft.

If multiple fuel engines are combined with multiple electric engines, because of the poor consistency of the fuel engine, even for the same type of fuel engine, the same throttle controller will be input, and the power output between the fuel engines will be better. Great difference, so it is difficult to accurately control and coordinate the pitch and speed of the rotor driven by the oil machine, which causes the shortcoming of the drone to be less stable.

technical problem

The existing oil-electric hybrid drone has poor stability.

Technical solution

In order to solve the above technical problem, the present application provides an oil-electric hybrid drone, which specifically includes:

a fuselage, the fuselage comprising a main frame and two sub-racks;

a rotor group comprising two main rotors respectively disposed at two ends of the main frame, and four auxiliary rotors, wherein the four auxiliary rotors are respectively disposed at four ends of the two sub-frames;

a power system including a fuel engine and a plurality of electric engines;

Both of the main rotors are powered by the fuel engine; each of the secondary rotors is powered by an electric motor.

Preferably, a battery is also included for powering the electric engine.

Preferably, the fuel engine is also used to power the electric engine.

Preferably, the output shaft of the fuel engine is provided with two timing pulleys, which are respectively driven by belts with the central axes of the two main rotors.

Preferably, the output shaft of the fuel engine is horizontally placed, the central axis of the main rotor is perpendicular thereto, and the twist directions of the two belts are identical, so that the rotation directions of the two main rotors are opposite.

Preferably, the fuel engine and the main rotor are driven by a turbine worm.

Preferably, the main frame includes symmetrically disposed left and right rack bars, and the two sub-frames are vertically connected to the left and right frame bars, respectively, and the two of the pair The racks are symmetrical to each other.

Preferably, a control system is further included for controlling the operations of the drone.

Beneficial effect

The application not only maintains the advantages of heavy fuel load and long battery life, but also has the advantages of simple structure and simple control, which greatly reduces the development and manufacturing cost of the drone.

DRAWINGS

1 is a schematic structural view of an embodiment of a hybrid electric unmanned aerial vehicle of the present application;

2 is a schematic view showing the belt connection between the output shaft of the fuel engine and the central shaft of the main rotor of the present application;

3 is a schematic structural view of a power system;

4 is a schematic diagram showing the relative positions of the main frame and the sub-rack of the present application;

FIG. 5 is a schematic diagram showing the relative position of another main frame and a sub-rack according to the present application.

Embodiment of the present application

In order to explain the technical solutions of the present application more clearly, the technical solutions of the embodiments of the present application will be described in detail below with reference to the accompanying drawings.

The present application proposes an oil-electric hybrid drone, as shown in FIG. 1 and FIG. 3, the hybrid electric drone includes:

a fuselage, the fuselage comprising a main frame 1 and two sub-frames 2;

a rotor group comprising two main rotors 3 respectively disposed at two ends of the main frame 1, and four sub-rotors 4, the four sub-rotors 4 being respectively disposed at four ends of the two sub-frames 2 ;

a power system, the power system comprising a fuel engine 6 and a plurality of electric engines 7;

Both of the main rotors 3 are powered by the fuel engine 6; each of the sub-rotors 4 is powered by an electric motor 7 respectively.

In this embodiment, in order to maintain the symmetrical structure of the drone, the fuel engine 6 is disposed at the center of the fuselage to provide power to the two main rotors 3 at both ends of the main frame 1 for providing lift and forward for the drone. power. The four auxiliary rotors 4 are respectively equipped with independent power generators, which are mainly used to control the attitude of the aircraft in pitch, roll and yaw. The main and auxiliary rotors cooperate with each other to help accurately control the flight attitude and trajectory of the drone, and have the advantages of long battery life and heavy load.

In this application, only one fuel engine 6 is used to control the two main rotors 3. The parameters of the rotational speeds of the two main rotors 3 can be easily achieved, and it is not necessary to adjust with precise attitude detecting sensors and complicated control systems. . Therefore, the application not only maintains the advantages of heavy carrying capacity and long battery life, but also has the advantages of simple structure and simple control, and greatly reduces the development and manufacturing cost of the drone.

In a preferred embodiment, the hybrid electric vehicle includes a battery for powering the electric motor 7. When the drone rises to a high altitude, the oxygen content in the air is low, and the fuel engine 6 is affected. At this time, the electric motor 7 functions as a battery life. Therefore, the present application is less restricted by the air oxygen content and the flying height, and the application is more For a wide range.

In a preferred embodiment, the fuel engine 6 is also used to power the electric engine. The fuel engine 6 generates electricity during the fueling process, and can supply power to the electric engine to prevent the use of the auxiliary rotor 4 when the battery is exhausted, further increasing the battery life.

In a preferred embodiment, as shown in FIG. 2, the output shaft 61 of the fuel engine 6 is provided with two timing pulleys, which are respectively driven by the belts 5 with the central shafts 31 of the two main rotors 3.

The output shaft 61 of the fuel engine 6 is horizontally placed, the central axis 31 of the main rotor 3 is perpendicular thereto, and the twist directions of the two belts 5 are identical, so that the rotation directions of the two main rotors 3 are opposite.

In the present embodiment, the position of the fuel engine 6 is in the center of the fuselage, the main rotor 3 is at both ends of the main frame 1, the output shaft 61 of the fuel engine 6 is horizontally placed, and the central axis 31 of the main rotor 3 is relatively vertical, that is, The output shaft 61 of the fuel engine 6 is perpendicular to the plane formed by the central axes 31 of the two main rotors 3. The timing pulleys provided on the fuel engine 6 are fixed to each other, and the rotation speeds and the like are completely identical. The timing pulleys of the main shafts 31 of each of the main rotors 3 can be respectively arranged, and each belt 5 is respectively sleeved on the synchronous pulley of the fuel engine 6. The main rotor 3 is connected to the fuel engine 6 on the timing pulley of the main rotor 3.

Since the output shaft 61 and the central axis 31 of the main rotor 3 are perpendicular to each other, the belt 5 needs to be twisted by 90 degrees; as shown in FIG. 2, with one side as a reference direction, the twist directions of the two belts 5 are identical, so that they are the same Under the driving of the output shaft 61, the two central shafts 31 rotate in opposite directions, that is, the two main rotors 3 rotate in opposite directions, thereby mutually canceling the counter torque generated when the rotor rotates.

In a preferred embodiment, the fuel engine 6 and the main rotor 3 are driven by a turbine worm or by a drive shaft or a bevel gear. The purpose is to avoid the slippage of the belt and improve the accuracy of the transmission.

In a preferred embodiment, the main frame 1 includes symmetrically disposed left and right rack bars 11 and 12, and the two sub-racks 2 and the left and right racks, respectively. The rods 12 are vertically connected, and the two sub-frames 2 are symmetrical to each other. As shown in Fig. 1, the symmetrical grass heads are "艹" shaped, which makes the drone flight more stable.

The application may also be as follows: as shown in FIG. 4, the main frame 1 is set as a symmetric left frame bar 11 and a right frame bar 12, and the two sub-frames 2 are fixed at the center of the fuselage, and are arranged in a cross. Taking the center of the fuselage as a symmetrical point, the main frame 1 and the two sub-frames 2 are axisymmetric and centrally symmetrical. Or, as shown in FIG. 5, the two sub-frames 2 are respectively in a "T" shape and are vertically connected to the main frame 1.

All of the above are applicable to this application. When the present application satisfies two conditions: 1. The main frame and the sub-frame are respectively axisymmetric with the central axis of the fuselage as the axis of symmetry; 2. All the rotors do not interfere with each other. It can ensure the drone flight is stable, and the settings of the main frame and sub-rack can be adjusted according to actual needs.

In a preferred embodiment, the hybrid electric vehicle includes a control system for controlling various operations of the drone, such as adjusting the lift and blade angle of each rotor, and the fuel engine 6 The output power of the electric engine and the mutual switching between the two.

It should be noted that the technical solutions between the various embodiments of the present application may be combined with each other, but must be based on what can be implemented by those skilled in the art, and should be considered as a technical solution when the combination of technical solutions is contradictory or impossible to implement. The combination does not exist and is not within the scope of the claims.

The above description is only a part or the preferred embodiment of the present application, and the text and the drawings are not intended to limit the scope of the present application, and the contents of the present application and the drawings are utilized in the overall concept of the present application. Equivalent structural transformations, or direct/indirect applications, are included in the scope of the present application.

Claims

An oil-electric hybrid drone characterized by comprising:

a fuselage, the fuselage comprising a main frame and two sub-racks;

a rotor group comprising two main rotors respectively disposed at two ends of the main frame, and four auxiliary rotors, wherein the four auxiliary rotors are respectively disposed at four ends of the two sub-frames;

a power system including a fuel engine and a plurality of electric engines;

Both of the main rotors are powered by the fuel engine; each of the secondary rotors is powered by an electric motor.
The hybrid electric vehicle according to claim 1, further comprising a battery for supplying power to said electric motor.
The hybrid electric drone of claim 1 wherein said fuel engine is further for powering said electric engine.
The hybrid electric vehicle according to claim 1, wherein two timing pulleys are disposed on the output shaft of the fuel engine, and are respectively driven by belts with the central axes of the two main rotors.
The hybrid electric vehicle according to claim 4, wherein the output shaft of the fuel engine is horizontally placed, the central axis of the main rotor is perpendicular thereto, and the twist directions of the two belts are the same. The rotation directions of the two main rotors are reversed.
The hybrid electric vehicle according to claim 1, wherein said fuel engine and said main rotor are driven by a turbine vortex.
The hybrid electric unmanned aerial vehicle of claim 1 , wherein the main frame comprises symmetrically disposed left and right rack bars, and the two sub-frames and the left machine respectively The mast and the right rack bar are vertically connected, and the two sub-racks are symmetrical to each other.
The hybrid electric vehicle according to any one of claims 1 to 7, further comprising a control system for controlling the operations of the drone.
The hybrid electric drone according to claim 1, wherein the sub-frame has a T-shaped structure, and the two sub-frames are respectively vertically connected to the main frame, and the vertical connection point is located The center of the main frame.
The hybrid electric unmanned aerial vehicle according to claim 1, wherein said sub-frame is a flat structure, and said two sub-frames are fixed to a center of said body, said The center of the fuselage is a symmetrical point, and the main frame and the two sub-frames are axisymmetric and centrally symmetric.