CN110857144B

CN110857144B - Power system and aircraft comprising same

Info

Publication number: CN110857144B
Application number: CN201810968993.XA
Authority: CN
Inventors: 金鹏
Original assignee: Shanghai Autoflight Co Ltd
Current assignee: Shanghai Autoflight Co Ltd
Priority date: 2018-08-23
Filing date: 2018-08-23
Publication date: 2023-05-23
Anticipated expiration: 2038-08-23
Also published as: CN110857144A

Abstract

The invention discloses an aircraft with a power system machine. The power system includes: a motor, a speed reducer and a propeller; the speed reducer is used for inputting high-speed and low-torque rotation and outputting low-speed and high-torque rotation; the rotating shaft of the motor is connected with the input end of the speed reducer, and the propeller is connected with the output end of the speed reducer. The power system adopts the speed reducer to improve the output torque, so that a small motor with low torque can be selected, and the volume, weight and cost of the whole power system are reduced. The aircraft employing the power system may also be reduced in size, weight, and cost.

Description

Power system and aircraft comprising same

Technical Field

The invention relates to a power system and an aircraft comprising the same.

Background

In the prior art, the power system of the electric aircraft mostly adopts a large motor to directly drive a large blade, and adopts a direct driving mode to have lower power-weight ratio (ratio of power to weight). Because of the large torque required to drive large blades, the torque output by the commonly used motors is large, but the volume of the motors with large output torque is correspondingly large, the weight is large, the price is high, the total volume and the weight of the aircraft are increased, and the cost is increased.

Disclosure of Invention

The invention aims to overcome the defects of large total volume, weight and cost of an aircraft caused by a large motor in the prior art, and provides a power system and the aircraft comprising the power system.

The invention solves the technical problems by the following technical scheme:

a power system, comprising: a motor, a speed reducer and a propeller;

the speed reducer is used for inputting high-speed and low-torque rotation and outputting low-speed and high-torque rotation;

the rotating shaft of the motor is connected with the input end of the speed reducer, and the propeller is connected with the output end of the speed reducer.

Preferably, the axis of rotation of the motor and the axis of rotation of the propeller are coaxial.

Preferably, the power system further comprises: the connecting shaft and the blade fixing seat;

one end of the connecting shaft is inserted into the output end of the speed reducer, the other end of the connecting shaft is fixedly connected with the blade fixing seat, and the blade fixing seat is fixedly connected with the propeller.

Preferably, the blade holder includes a central portion and a flange portion disposed around the central portion;

the outer periphery of the flange part is provided with a plurality of first mounting holes for connecting with the propeller;

the center portion has an axially protruding insertion portion and a second mounting hole provided around the insertion portion for connection with the connection shaft.

Preferably, the side of the insert is recessed inwardly to form one or more recesses, and the second mounting hole is disposed adjacent to the recesses.

In this scheme, form the depressed part in the insert portion, can make the insert portion form the shape structure that easily joins and for the space of stepping down of second installation Kong Liuchu for the structure of paddle fixing base is compacter, small and exquisite.

Preferably, one end of the connecting shaft is provided with teeth, the other end of the connecting shaft is provided with a connecting hole, and the connecting hole corresponds to the position of the second mounting hole.

Preferably, an insertion hole is provided in the center of the propeller, and the shape of the insertion hole corresponds to the shape of the insertion portion.

Preferably, the connecting shaft is a steel shaft.

In this scheme, adopt the steel shaft can improve joint strength.

An aircraft comprising a power system as described above.

Preferably, the aircraft is a multi-rotor unmanned aircraft.

The invention has the positive progress effects that: the power system adopts the speed reducer to improve the output torque, so that a small motor with low torque can be selected, and the volume, weight and cost of the whole power system are reduced. The aircraft employing the power system may also be reduced in size, weight, and cost.

Drawings

Fig. 1 is a schematic structural view of a power system according to a preferred embodiment of the present invention.

Fig. 2 is an exploded structural view of a power system according to a preferred embodiment of the present invention.

Fig. 3 is a schematic perspective view of a blade holder according to a preferred embodiment of the present invention.

Fig. 4 is a schematic top view of a blade holder according to a preferred embodiment of the present invention.

Fig. 5 is a schematic side view of a blade holder according to a preferred embodiment of the present invention.

Fig. 6 is a schematic perspective view of a connecting shaft according to a preferred embodiment of the present invention.

Fig. 7 is a schematic view showing a partial cross-sectional structure of a mating relationship of a connection shaft and a blade holder according to a preferred embodiment of the present invention.

Fig. 8 is a schematic structural view of an aircraft according to a preferred embodiment of the invention.

Reference numerals illustrate:

power system 100

Propeller 110

Blade holder 120

Flange portion 121

Center portion 122

Hollowed-out portion 123

Recess 124

First mounting hole 125

Second mounting hole 126

Bearing support 130

Bearing 140

Connecting shaft 150

Connection hole 151

Speed reducer 160

Input terminal 161

Output 162

Fixed housing 170

Motor 180

Rotating shaft 181

Bolt 190

Aircraft 200

Detailed Description

The invention will be further illustrated by way of example with reference to the accompanying drawings, without thereby limiting the scope of the invention to the examples described below.

As shown in fig. 1-2, the power system 100 includes: motor 180, decelerator 160, and propeller 110.

The decelerator 160 is used to input a high-rotation-speed, low-torque rotation and output a low-rotation-speed, high-torque rotation. The high rotational speed and low torque and high torque in the present application do not refer specifically to a certain rotational speed range or a certain rotational speed value and a certain torque range or a certain torque value, but are relative concepts meaning that the speed reducer 160 is capable of outputting a rotation lower than the original rotational speed and higher than the original torque.

The rotation shaft 181 of the motor 180 is coupled to the input 161 of the decelerator 160, and the propeller 110 is coupled to the output 162 of the decelerator 160.

In the present embodiment, the rotation axis 181 of the motor 180 is coaxial with the rotation axis 181 of the propeller 110. In other embodiments, the axis of rotation 181 of the motor 180 and the axis of rotation 181 of the propeller 110 may be different, such as at a 90 degree angle, coupled by a bevel gear, for example.

The power system 100 further includes: a connection shaft 150 and a blade holder 120.

One end of the connecting shaft 150 is inserted into the output end 162 of the decelerator 160, and the other end of the connecting shaft 150 is fixedly connected to the blade fixing base 120, and the blade fixing base 120 is fixedly connected to the propeller 110.

As shown in fig. 3-5, blade holder 120 includes a central portion 122 and a flange portion 121 disposed around central portion 122. The flange portion 121 is provided with a plurality of hollowed-out portions 123 so as to reduce the weight of the blade fixing base 120.

The outer peripheral portion of the flange portion 121 is provided with four first mounting holes 125 for connection with the propeller 110. Of course, those skilled in the art can also arbitrarily set the number of the first mounting holes 125 as needed. The screw 110 is also provided with a corresponding screw hole, and the bolt 190 is inserted into both the first mounting hole 125 and the screw hole to fix the blade holder 120 to the screw 110.

The central portion 122 has an axially protruding insertion portion and a second mounting hole 126 provided around the insertion portion, the second mounting hole 126 being for connection with the connection shaft 150.

Preferably, the sides of the insert are recessed inwardly to form one or more recesses 124, and the second mounting hole 126 is disposed adjacent to the recesses 124.

The recess 124 is formed in the insertion portion, so that the insertion portion can form a shape structure that is easy to be engaged and a space is left for the second mounting hole 126, so that the blade fixing base 120 is more compact and small in structure.

The propeller 110 is provided with an insertion hole at the center thereof, and the shape of the insertion hole corresponds to the shape of the insertion portion.

When the propeller 110 and the blade holder 120 are assembled, the insertion portion is engaged with the insertion hole, and then the bolt 190 is inserted into the first mounting hole 125 to be fixed.

As shown in fig. 6 to 7, one end of the connection shaft 150 is provided with teeth, the other end of the connection shaft 150 is provided with a connection hole 151, and the connection hole 151 corresponds to the position of the second mounting hole 126. The bolts 190 are inserted into the connection holes 151 from the second mounting holes 126 and are screwed into the connection holes 151 to fixedly connect the connection shaft 150 and the blade fixing base 120. The toothed end of the connecting shaft 150 is inserted into the output 162 of the reducer 160.

The connection shaft 150 is a steel shaft. The steel shaft can improve the connection strength.

The power system 100 further includes a bearing 140, a bearing 140 seat 130, and a fixed housing 170, where the bearing 140 seat 130 is configured to accommodate the bearing 140 and fixedly connect with the fixed housing 170, and the reducer 160 is accommodated in the fixed housing 170, and the fixed housing 170 is fixedly connected with the motor 180. By the interconnection of the above components, the power system 100 forms a compact assembly structure as in fig. 1.

As shown in fig. 8, an aircraft 200 includes a power system 100 as described above. The aircraft 200 is a multi-rotor unmanned aerial vehicle.

The power system 100 employs the decelerator 160 to increase the output torque so that a small motor 180 with low torque can be selected, thereby reducing the volume, weight and cost of the entire power system 100. Aircraft 200 employing the power system 100 may also be reduced in volume, weight, and cost.

In the description of the present invention, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operate in a specific orientation, and thus should not be construed as limiting the invention unless otherwise indicated herein.

While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.

Claims

1. A power system, comprising: a motor, a speed reducer and a propeller;

the rotating shaft of the motor is connected with the input end of the speed reducer, and the propeller is connected with the output end of the speed reducer;

the power system further includes: the connecting shaft and the blade fixing seat;

one end of the connecting shaft is inserted into the output end of the speed reducer, the other end of the connecting shaft is fixedly connected with the blade fixing seat, and the blade fixing seat is fixedly connected with the propeller;

the blade fixing seat comprises a central part and a flange part arranged around the central part;

the central part is provided with an inserting part protruding axially and a second mounting hole arranged around the inserting part, and the second mounting hole is used for being connected with the connecting shaft;

the side of the insert is recessed inwardly to form one or more recesses, and the second mounting hole is disposed adjacent to the recesses.

2. The power system of claim 1, wherein the axis of rotation of the motor and the axis of rotation of the propeller are coaxial.

3. The power system of claim 1, wherein the outer peripheral portion of the flange portion is provided with a plurality of first mounting holes for connection with a propeller.

4. The power system of claim 1, wherein one end of the connecting shaft is provided with teeth, and the other end of the connecting shaft is provided with a connecting hole, and the connecting hole corresponds to the position of the second mounting hole.

5. The power system according to claim 1, wherein an insertion hole is provided in a center of the propeller, and a shape of the insertion hole corresponds to a shape of the insertion portion.

6. The power system of claim 1, wherein the connecting shaft is a steel shaft.

7. An aircraft, characterized in that it comprises a power system according to any one of claims 1-6.

8. The aerial vehicle of claim 7 wherein the aerial vehicle is a multi-rotor unmanned aerial vehicle.