Power assembly and aircraft

Patent metadata

Field	Value
Publication number	US-10759526-B2
Application number	US-201816193271-A
Country	US
Kind code	B2
Filing date	Nov 16, 2018
Priority date	Nov 18, 2016
Publication date	Sep 1, 2020
Grant date	Sep 1, 2020

Abstract

The present invention provides a power assembly, including: a motor, a fixing base and a propeller. The fixing base is sleeved over a motor rotation shaft and is fastened to a base body of the motor, and the fixing base is provided with a first clamping portion. The propeller includes a base portion and a blade extending from the base portion, and the base portion is provided with a second clamping portion clamped to the first clamping portion. The propeller is detachably connected to the motor by engaging the first clamping portion with the second clamping portion, so that the propeller can be effectively prevented from loosening from the motor during the vibration or acceleration, and is easy to disassemble/assemble and carry.

First claim

What is claimed is:

1. A power assembly, comprising:
a motor, comprising a base body and a motor rotation shaft connected to the base body;
a fixing base, sleeved over the motor rotation shaft and connected to the base body, wherein the fixing base is provided with a first clamping portion; and
a propeller, comprising a base portion and a blade extending from the base portion, wherein the base portion is provided with a second clamping portion clamped to the first clamping portion, and the base portion is sleeved over the rotation shaft and is connected to the fixing base by clamping engagement between the first clamping portion and the second clamping portion;
wherein the power assembly further comprises an elastic component sleeved over the motor rotation shaft, the elastic component is a variable-diameter spring;
wherein one end of the elastic component abuts against a bottom surface of the base portion facing the base body, and the other end of the elastic component abuts against a base body of the motor;
wherein the power assembly further comprises a blocking ring sleeved over the motor rotation shaft and located above the elastic component, wherein one side of the blocking ring abuts against the base portion, and the other side of the blocking ring abuts against one end of the elastic component;
wherein a through hole is provided at the center of the blocking ring, and two arc-shaped gaps are further provided in the circumference of the blocking ring.

2. The power assembly according to claim 1 , wherein along a circumference of the top surface facing the surface of the accommodating space, a plurality of first projections are disposed at intervals, wherein a fixing groove is formed between any two adjacent first projections, and wherein the first clamping portion is the fixing groove.

3. The power assembly according to claim 1 , wherein the second clamping portion is a stopper disposed on the base portion.

4. The power assembly according to claim 1 , wherein the base portion comprises a pedestal and a connection shaft connected to the pedestal, and the second clamping portion is disposed on the connection shaft.

5. The power assembly according to claim 4 , wherein the through hole comprises a circular portion for passing through by the connection shaft and an extending portion in communication with the circular portion, and the shape of the extending portion is the same as that of the second clamping portion.

6. The power assembly according to claim 3 , wherein the stopper is disposed at the bottom of the base portion, and the stopper comprises a vertical portion connected to the bottom of the base portion and a blocking portion extending from the vertical portion in a bending way.

7. The power assembly according to claim 6 , wherein the through hole comprises a first through hole matching the shape of the blocking portion and a second through hole in communication with the first through hole, and the second through hole is arc-shaped.

8. An aircraft, comprising an aircraft body, an aircraft arm connected to the aircraft body and a power assembly disposed on the aircraft arm, wherein the power assembly comprises:
a motor, comprising a base body and a motor rotation shaft connected to the base body;
a fixing base, sleeved over the motor rotation shaft and connected to the base body, wherein the fixing base is provided with a first clamping portion; and
a propeller, comprising a base portion and a blade extending from the base portion, wherein the base portion is provided with a second clamping portion clamped to the first clamping portion, and the base portion is sleeved over the rotation shaft and is connected to the fixing base by clamping engagement between the first clamping portion and the second clamping portion;
wherein the power assembly further comprises an elastic component sleeved over the motor rotation shaft, the elastic component is a variable-diameter spring;
wherein one end of the elastic component abuts against a bottom surface of the base portion facing the base body, and the other end of the elastic component abuts against a base body of the motor;
wherein the power assembly further comprises a blocking ring sleeved over the motor rotation shaft and located above the elastic component, wherein one side of the blocking ring abuts against the base portion, and the other side of the blocking ring abuts against one end of the elastic component;
wherein a through hole is provided at the center of the blocking ring, and two arc-shaped gaps are further provided in the circumference of the blocking ring.

9. The aircraft according to claim 8 , wherein along a circumference of the top surface facing the surface of the accommodating space, a plurality of first projections are disposed at intervals, wherein a fixing groove is formed between any two adjacent first projections, and wherein the first clamping portion is the fixing groove.

10. The aircraft according to claim 8 , wherein the second clamping portion is a stopper disposed on the base portion.

11. The aircraft according to claim 8 , wherein the base portion comprises a pedestal and a connection shaft connected to the pedestal, and the second clamping portion is disposed on the connection shaft.

12. The aircraft according to claim 11 , wherein the through hole comprises a circular portion for passing through by the connection shaft and an extending portion in communication with the circular portion, and the shape of the extending portion is the same as that of the second clamping portion.

13. The aircraft according to claim 10 , wherein the stopper is disposed at the bottom of the base portion, and the stopper comprises a vertical portion connected to the bottom of the base portion and a blocking portion extending from the vertical portion in a bending way.

14. The aircraft according to claim 13 , wherein the through hole comprises a first through hole matching the shape of the blocking portion and a second through hole in communication with the first through hole, and the second through hole is arc-shaped.

Assignees

• Autel Robotics Co Ltd

Inventors

• Hu Liangjun
• Qiu Longxue

Classifications

• B64C27/14 Primary

  Direct drive between power plant and rotor hub · CPC title

• F16D1/112 Primary

  the interengaging parts comprising torque-transmitting surfaces, e.g. bayonet joints · CPC title

• B64U10/14

  with four distinct rotor axes, e.g. quadcopters · CPC title

• B64U50/19

  using electrically powered motors · CPC title

• B64C2027/003

  mounted on rotor hub, e.g. a rotary force generator · CPC title