WO2016054863A1

WO2016054863A1 - Multi-rotor air vehicle

Info

Publication number: WO2016054863A1
Application number: PCT/CN2014/094293
Authority: WO
Inventors: 杨华东
Original assignee: 杨华东
Priority date: 2014-10-11
Filing date: 2014-12-19
Publication date: 2016-04-14
Also published as: CN104290904A

Abstract

A multi-rotor air vehicle comprises a bracket (10) and a main motor (20) mounted on the bracket. The main motor comprises a first main motor (21) and a second main motor (22) that are coaxially disposed. The first main motor and the second main motor are respectively connected to a first main screw propeller (31) and a second main screw propeller (32). At least three secondary screw propellers (40) surround each main motor. The secondary screw propellers are mounted on the bracket. The main motors drive large screw propellers, so that the lifting efficiency is high; the main motors are coaxially disposed, and the two main screw propellers rotate in opposite directions, so that the large torque is offset; the main motors are disposed in the center of an air vehicle body, so that the vibration influence is minimized; the secondary motors control the attitudes and actions of the air vehicle body, so that the power consumption is reduced; if the air vehicle accidently crashes in the takeoff and landing stages, the maintenance cost and difficulty are reduced.

Description

Multi-rotor aircraft

Technical field

This application belongs to the field of aerial vehicles, and more particularly to a multi-rotor aircraft.

Background technique

Unmanned aerial vehicles are characterized by small size, light weight, low cost, flexible operation and high safety. They can be widely used in aerial photography, monitoring, search and rescue, resource exploration and other fields.

In the prior art, an unmanned aerial vehicle generally includes a plurality of rotors, each of which is driven by a motor, and has the disadvantages of:

1. Since a plurality of motors are provided, the motor is evenly arranged in the horizontal direction according to the center of the fuselage, so that the unmanned aerial vehicle as a whole is relatively heavy;

2. Multiple motors work together, and the high-frequency vibration generated by them easily affects the accuracy of aerial photography;

3. The existing multi-axis aircraft uses multiple motors to directly drive the respective propellers. In order to maintain balance during flight of the aircraft, the flight control system needs to frequently change the motor speed. This frequent change in speed can cause the motor to expedite power consumption. Moreover, each motor has working efficiency, and the more the number of motors, the lower the working efficiency of the whole machine.

4. The existing type of multi-motor driven aircraft is difficult to achieve large size, because the larger the motor, the greater the vibration during operation. And the increase in the cost of a single motor has led to a significant increase in the cost of the entire machine.

In view of this, it is necessary to provide a new type of unmanned aerial vehicle.

Summary of the invention

It is an object of the present invention to provide a multi-rotor aircraft that overcomes the deficiencies of the prior art.

To achieve the above object, the present invention provides the following technical solutions:

The embodiment of the present application discloses a multi-rotor aircraft, including a bracket and a main motor mounted on the bracket, the main motor including a first main motor and a second main motor disposed coaxially, the first main The motor and the second main motor are respectively connected to the first main propeller and the second main propeller, and the main motor is wound around at least three sub propellers, and the sub propeller is mounted on the bracket.

Preferably, in the multi-rotor aircraft described above, each of the sub-propellers is driven by a separate sub-motor.

Preferably, in the multi-rotor aircraft described above, the first main propeller and the second main propeller are respectively disposed on upper and lower sides of the bracket.

Preferably, in the multi-rotor aircraft described above, the first main propeller and the second main propeller are both disposed above the bracket or both are disposed below the bracket.

Preferably, in the multi-rotor aircraft, the output shaft of the first main motor is sleeved outside the output shaft of the second main motor, and the output shaft of the first main motor and the first main propeller Fixed, the output shaft of the second main motor is fixed to the second main propeller.

Preferably, in the above multi-rotor aircraft, the bracket includes a seat and a strut mounted on the support, and each of the auxiliary propellers is respectively mounted at an end of the strut, the main A motor is mounted on the support.

Preferably, in the above-described multi-rotor aircraft, the number of the sub-propellers is an even number, and the sub-propellers are symmetrically distributed around the support.

Preferably, in the multi-rotor aircraft described above, the number of the sub-propellers is four, and the four sub-propellers are equally spaced around the support.

Preferably, in the multi-rotor aircraft described above, the first main propeller and the second main propeller respectively have three blades.

The advantages of the present invention over the prior art are:

1. The main motor (engine) drives a large propeller with high lift efficiency;

2. The main motor is coaxially arranged, and the two main propellers rotate in opposite directions to offset the large torque;

3. The main motor is arranged in the center of the fuselage to minimize the influence of vibration;

4, the secondary motor controls the attitude and movement of the fuselage, and the power consumption is reduced;

5. During the take-off and landing phases, if the aircraft crashes unexpectedly, the first to be damaged is the auxiliary motor and small propeller in the periphery. The main motor and the main propeller in the center of the fuselage can be protected, which greatly reduces the maintenance cost and difficulty.

DRAWINGS

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings to be used in the embodiments or the prior art description will be briefly described below. Obviously, the drawings in the following description are only It is a few embodiments described in the present application, and other drawings can be obtained from those skilled in the art without any creative work.

1 is a perspective view showing a multi-rotor aircraft according to a first embodiment of the present invention;

2 is a schematic exploded view of a multi-rotor aircraft according to a first embodiment of the present invention;

Fig. 3 is a perspective view showing a multi-rotor aircraft according to a second embodiment of the present invention.

detailed description

The technical solutions in the embodiments of the present invention are described in detail below with reference to the accompanying drawings in the embodiments of the present invention. It is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention without creative efforts are within the scope of the present invention.

Referring to Figures 1 and 2, the multi-rotor aircraft includes a bracket 10, a main motor 20 mounted on the bracket 10, a main propeller 30 driven by the main motor 20, and four sub-distributors around the main motor 20. Propeller 40.

The bracket 10 includes a seat 11 on which four struts 12 are symmetrically distributed, and four sub-propellers 40 are respectively mounted to the ends of the four struts 12 by a separate sub motor 41. Four auxiliary propellers The 40 is driven by separate sub-motors, so that the rotational speed of each sub-propeller 40 can be independently controlled. Each of the sub motors 41 is detachably mounted to the end of the strut 12 via a mounting seat 42, respectively.

The four secondary propellers 40 are preferably equally spaced around the support 11, i.e., the adjacent two struts 12 are perpendicular. In other embodiments, the two adjacent struts 12 may also be non-perpendicular.

The main motor 20 includes a first main motor 21 and a second main motor 22 that are superposed, and an output shaft of the first main motor 21 is sleeved outside the output shaft of the second main motor 22. The main motor 20 is fixed above the support 11.

The main propeller 30 includes a second main propeller 32 and a first main propeller 31 disposed above and below, wherein the first main propeller 31 is fixed to the output shaft of the first main motor 21, and the output of the second main propeller 32 and the second main motor 22 is output. The shaft is fixed. The number of the blades of the first main propeller 31 and the second main propeller 32 is preferably three. It should be noted that the number of each main propeller blade is not limited in the invention, and may be two, for example.

In this embodiment, the four auxiliary propellers 40 can also be driven by the same motor, and the driving of the same motor can keep each of the secondary propellers 40 having the same rotational speed, which can be applied to indoors, etc., without wind, which can affect its stability, and An environment where no panning or rotation is required.

In this embodiment, the first main propeller and the second main propeller may also be disposed under the support at the same time.

In this embodiment, the two struts 12 that are symmetrically disposed may also be an elongated rod that is integrally disposed, and the round rod is disposed in the middle of the support 11 .

In this embodiment, the number of the sub-propellers 40 can also be set to 3 or more. When set to 3, the 3 sub-propellers are mainly used to achieve balance stability of the aircraft, and the aircraft is mainly used for vertical lifting without The field of application that requires translation, if needed to rotate, can be achieved by changing the speed or pitch of the secondary propeller 40. The number of the secondary propellers 40 is preferably an even number, which is symmetrically distributed around the main motor 30, and can be translated or rotated by changing the rotational speed of the sub-propeller 40 in the symmetrical position.

The working principle of the multi-rotor aircraft in this embodiment will be described below:

The rotation directions of the two main propellers are opposite, and the rotation directions of the four sub propellers are the same in the direction of rotation of the propeller on the diagonal, and the rotation directions of the two adjacent propellers are opposite.

Let the main motor (main engine) located in the middle of the whole machine drive two large-sized propellers rotating in opposite directions to generate 70-90% of the weight of the whole machine. At the same time, four sub-motors are used to drive four small propellers to generate the whole. The weight of the machine removes the rest of the lift of the main propeller lift and controls the attitude and movement of the complete machine.

The advantage of this solution is that the main propeller driven by the main motor (main engine) has a large size and high lift efficiency. And unlike the conventional scheme, the conventional scheme increases the size of the motor. Since the motor is arranged in the center circumference of the fuselage, this structure causes the larger the motor, the greater the vibration in the flying state. The large-sized motor of this embodiment is disposed in the center of the fuselage, so that the influence of the large motor on the vibration generated by the whole machine is minimized. Two main propellers rotating in opposite directions also counteract the high torque effect produced by the use of a single large propeller. The four sub-motors drive the small propellers, and the four sub-motors are arranged in the same manner as the conventional one, and are arranged along the central circumference of the fuselage.

The secondary motor is mainly responsible for controlling the posture and movement of the whole machine. The working mode is as follows:

During the lifting process, four auxiliary propellers are used to control the balance stability of the aircraft;

During the rotation process, the relative rotational speeds of the two secondary propellers at the diagonal position are changed;

When moving horizontally, the rotational speed of two of the secondary propellers at the diagonal position increases, and the rotational speeds of the other two secondary propellers decrease.

As shown in FIG. 3, in the second embodiment, the first main propeller and the second main propeller may also be respectively disposed on the upper and lower sides of the bracket.

It should be noted that, in this context, relational terms such as first and second are used merely to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply such entities or operations. There is any such actual relationship or order between them. Moreover, the terms "including" and "package" "including" or any other variation thereof is intended to encompass a non-exclusive inclusion, such that a process, method, article, or device that comprises a plurality of elements includes not only those elements but also other elements not specifically listed, or An element that is inherent to such a process, method, article, or device. Without further limitation, an element defined by the phrase "comprising a ..." is not excluded from the process, method, or article including the element. Or there are other identical elements in the device.

The above description is only a specific embodiment of the present application, and it should be noted that those skilled in the art can also make several improvements and retouchings without departing from the principles of the present application. It should be considered as the scope of protection of this application.

Claims

A multi-rotor aircraft characterized by comprising a bracket and a main motor mounted on the bracket, the main motor comprising a first main motor and a second main motor disposed coaxially, the first main motor and the first The two main motors are respectively connected to the first main propeller and the second main propeller, and the main motor is wound around at least three sub propellers, and the sub propeller is mounted on the bracket.
The multi-rotor aircraft of claim 1 wherein each of said sub-propellers is driven by a separate sub-motor.
The multi-rotor aircraft according to claim 1, wherein the first main propeller and the second main propeller are respectively disposed on upper and lower sides of the bracket.
The multi-rotor aircraft according to claim 1, wherein the first main propeller and the second main propeller are both disposed above the bracket or both are disposed below the bracket.
The multi-rotor aircraft according to claim 4, wherein an output shaft of the first main motor is sleeved outside the output shaft of the second main motor, and an output shaft of the first main motor is The first main propeller is fixed, and an output shaft of the second main motor is fixed to the second main propeller.
The multi-rotor aircraft according to claim 1, wherein said bracket includes a seat and a strut mounted on said seat, said sub-propellers being respectively mounted at an end of said strut The main motor is mounted on the support.
The multi-rotor aircraft according to claim 6, wherein the number of the sub-propellers is an even number, and the sub-propellers are symmetrically distributed around the support.
The multi-rotor aircraft according to claim 7, wherein the number of the sub-propellers is four, and the four sub-propellers are equally spaced around the support.
The multi-rotor aircraft according to claim 1, wherein said first main propeller and said second main propeller each have three blades.