CN110857144A

CN110857144A - Power system and aircraft comprising same

Info

Publication number: CN110857144A
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: 2020-03-03
Anticipated expiration: 2038-08-23
Also published as: CN110857144B

Abstract

The invention discloses an aircraft with a power system machine. This driving system includes: a motor, a reducer and a propeller; the speed reducer is used for inputting the rotation of high rotating speed and low torque and outputting the rotation of low rotating speed and high torque; the rotating shaft of the motor is connected to the input end of the speed reducer, and the propeller is connected to 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 size, the weight and the cost of the whole power system are reduced. The aircraft adopting the power system can also reduce the volume, the weight and the 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, a large motor is mostly adopted in an electric aircraft power system to directly drive a large blade, and a direct-drive mode is adopted, so that the power-weight ratio (the ratio of power to weight) is lower. Because a large torque is needed for driving a large blade, the output torque of the generally adopted motor is large, but the motor with the large output torque has a correspondingly large volume, a large weight and a high price, so that 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 same.

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

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

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

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

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

Preferably, the power system further comprises: a connecting shaft and a 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 paddle fixing seat, and the paddle fixing seat is fixedly connected with the propeller.

Preferably, the blade mount comprises a central portion and a flange portion disposed around the central portion;

a plurality of first mounting holes used for being connected with the propeller are formed in the periphery of the flange part;

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

Preferably, the side surfaces of the insertion portion are recessed inward to form one or more recessed portions, and the second mounting hole is disposed adjacent to the recessed portions.

In this scheme, form the depressed part in the inserted part, can make the inserted part form the shape structure of easily jointing and leave the space of stepping down for the second mounting hole 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 second mounting hole in position.

Preferably, an insertion hole is provided at 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 axle can improve joint strength.

An aircraft comprising a power system as described above.

Preferably, the aircraft is a multi-rotor drone.

The positive progress effects of the invention are as follows: 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 size, the weight and the cost of the whole power system are reduced. The aircraft adopting the power system can also reduce the volume, the weight and the cost.

Drawings

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

Fig. 2 is an exploded view schematically illustrating 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 side view schematically illustrating a blade fixing base according to a preferred embodiment of the present invention.

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

Fig. 7 is a partial sectional structural view showing a fitting relationship of a connecting shaft and a blade fixing seat 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.

Description of reference numerals:

power system 100

Propeller 110

Blade holder 120

Flange part 121

The center portion 122

Hollow-out part 123

Recess 124

First mounting hole 125

Second mounting hole 126

Bearing seat 130

Bearing 140

Connecting shaft 150

Connection hole 151

Decelerator 160

Input terminal 161

Output 162

Fixed housing 170

Motor 180

Rotating shaft 181

Bolt 190

Aircraft 200

Detailed Description

The present invention is further illustrated by way of example and not by way of limitation in the scope of the following examples in connection with the accompanying drawings.

As shown in fig. 1-2, power system 100 includes: motor 180, reduction gear 160, propeller 110.

Reduction gear 160 is used to input high-speed and low-torque rotation and output low-speed and high-torque rotation. The high and low rotation speeds and the low and high torques in the present application do not refer to a certain rotation speed range or a certain rotation speed value and a certain torque range or a certain torque value, but are relative concepts that the speed reducer 160 can output rotation lower than the original rotation speed and higher than the original torque.

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

In the present embodiment, the rotational axis 181 of the motor 180 is coaxial with the rotational 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 also be non-coaxial, such as at a 90 degree angle, for example, coupled by a bevel gear.

The power system 100 further includes: a connecting shaft 150 and a paddle mount 120.

One end of the connecting shaft 150 is inserted into the output end 162 of the speed reducer 160, 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 to 5, the blade mount 120 includes a central portion 122 and a flange portion 121 disposed around the 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 mount 120.

The flange 121 is provided at an outer circumferential portion thereof with four first mounting holes 125 for connection to the propeller 110. Of course, the number of the first mounting holes 125 can be arbitrarily set by those skilled in the art as needed. The propeller 110 also has 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 fixing base 120 to the propeller 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 connecting shaft 150.

Preferably, the sides of the insertion portion are recessed inward to form one or more recesses 124, and the second mounting holes 126 are disposed adjacent to the recesses 124.

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

The propeller 110 is provided at the center thereof with an insertion hole having a shape corresponding 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 connecting shaft 150 is provided with teeth, and the other end of the connecting shaft 150 is provided with a coupling hole 151, the coupling hole 151 corresponding to the second mounting hole 126. The bolt 190 is inserted into the connection hole 151 from the second mounting hole 126 and is threadedly coupled with the connection hole 151 to fixedly couple the connection shaft 150 and the blade holder 120. One end of the connecting shaft 150 with teeth is inserted into an output end 162 of the decelerator 160.

The connecting 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, wherein the bearing 140 seat 130 is used for accommodating the bearing 140 and fixedly connecting with the fixed housing 170, the speed reducer 160 is accommodated in the fixed housing 170, and the fixed housing 170 is fixedly connected with the motor 180. By interconnecting the above components, the power system 100 forms a compact assembly as shown in FIG. 1.

As shown in fig. 8, aircraft 200 includes power system 100 as described above. Aircraft 200 is a multi-rotor drone.

The power system 100 uses the reducer 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 whole power system 100. Aircraft 200 employing the power system 100 may also reduce volume, weight, and cost.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, are merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore, should not be construed as limiting the present invention unless otherwise specified 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 that 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 spirit and scope of the invention, and these changes and modifications are within the scope of the invention.

Claims

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

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

3. The power system of claim 1, further comprising: a connecting shaft and a blade fixing seat;

4. The power system of claim 3, wherein the blade mount comprises a central portion and a flange portion disposed about the central portion;

5. The powertrain system of claim 4, wherein the sides of the insert are recessed inwardly to form one or more recesses, the second mounting hole being disposed adjacent to the recesses.

6. The power system according to claim 4, 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 corresponding to the second mounting hole.

7. The power system according to claim 4, wherein the propeller is provided at a center thereof with an insertion hole having a shape corresponding to a shape of the insertion portion.

8. The power system of claim 3, wherein the connecting shaft is a steel shaft.

9. An aircraft, characterized in that the aircraft comprises a power system according to any one of claims 1-8.

10. The aircraft of claim 9, wherein said aircraft is a multi-rotor drone.