Aerial vehicle propulsion mechanism with coaxially aligned propellers

Patent metadata

Field	Value
Publication number	US-10526070-B2
Application number	US-201615194473-A
Country	US
Kind code	B2
Filing date	Jun 27, 2016
Priority date	Mar 23, 2016
Publication date	Jan 7, 2020
Grant date	Jan 7, 2020

Abstract

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Systems, methods, and apparatus may actively adjust the position and/or configuration of one or more propeller blades of a propulsion mechanism to generate different sounds and/or lifting forces from the propulsion mechanism.

First claim

What is claimed is:

1. An aerial vehicle apparatus comprising:
a first motor having a rotatable shaft extending from the first motor;
a first propeller having a first diameter, the first propeller coupled to a first position on the rotatable shaft;
a second propeller having a second diameter that is different than the first diameter, the second propeller coupled to a second position on the rotatable shaft, the second propeller coaxially aligned with the first propeller such that a first lifting force generated by the first propeller when rotated by the first motor and a second lifting force generated by the second propeller when rotated by the first motor are substantially in a same direction;
a third propeller having a third diameter, the third propeller coupled to a third position on the rotatable shaft, the third propeller coaxially aligned with the first propeller and the second propeller such that the first lifting force, the second lifting force, and a third lifting force generated by the third propeller when rotated by the first motor are substantially in the same direction; and
a controller configured to individually engage each of the first propeller, the second propeller, and the third propeller to be rotated by the first motor based at least in part on an operational profile associated with the aerial vehicle apparatus;
wherein each of the first propeller, the second propeller, and the third propeller are individually engaged by the controller via respective clutches or gears.

2. The aerial vehicle apparatus of claim 1 , wherein:
a first distance between the first position of the first propeller and the second position of the second propeller is selected to cause a first sound of a first induced flow from the first propeller to cause a first interference with a second sound of a second induced flow from the second propeller, the first interference resulting in a net effect sound that is a combination of the first sound and the second sound; and
a second distance between the second position of the second propeller and the third position of the third propeller is selected to cause a third sound of a third induced flow from the third propeller to cause a second interference with the net effect sound, the second interference resulting in a combined net effect sound that is a combination of the third sound and the net effect sound.

3. The aerial vehicle apparatus of claim 2 , wherein the combined net effect sound has at least one of a lower frequency or a lower amplitude than the first sound.

4. The aerial vehicle apparatus of claim 2 , wherein:
the first interference is destructive interference; and
the second interference is destructive interference.

5. The aerial vehicle apparatus of claim 1 , wherein the first diameter is smaller than the second diameter.

6. A propulsion apparatus, comprising:
a motor including a housing and a shaft, the motor configured to rotate the shaft at a revolutions per minute (RPM);
a first propeller having a first diameter, the first propeller coupled to the shaft at a first position, the first propeller including:
a first propeller blade having a first pitch; and
a second propeller blade having the first pitch;

a second propeller having a second diameter, the second propeller coupled to the shaft at a second position, the second propeller including:
a third propeller blade having a second pitch; and
a fourth propeller blade having the second pitch;

a third propeller having a third diameter, the third propeller coupled to the shaft at a third position, the third propeller including:
a fifth propeller blade having a third pitch; and
a sixth propeller blade having the third pitch; and

a controller configured to individually engage each of the first propeller, the second propeller, and the third propeller to be rotated by the motor based at least in part on an operational profile;
wherein each of the first propeller, the second propeller, and the third propeller are individually engaged by the controller via respective clutches or gears.

7. The propulsion apparatus of claim 6 , wherein the first diameter is different than at least one of the second diameter or the third diameter.

8. The propulsion apparatus of claim 6 , wherein:
the first position is closest to the motor along a length of the shaft;
the third position is furthest from the motor along the length of the shaft; and
the second position is between the first position and the third position.

9. The propulsion apparatus of claim 8 , wherein:
the first diameter is larger than the second diameter; and
the second diameter is larger than the third diameter.

10. The propulsion apparatus of claim 6 , wherein:
each of the first propeller, the second propeller, and the third propeller rotate in a same direction.

11. The propulsion apparatus of claim 6 , wherein:
a first distance between the first position and the second position is determined based at least in part on:
a first sound profile expected to be generated by the first propeller when rotated by the motor at the RPM; and
a second sound profile expected to be generated by the second propeller when rotated by the motor at the RPM.

12. The propulsion apparatus of claim 11 , wherein the first distance is further selected such that a first expected sound expected to be generated by the first propeller when rotated by the motor at the RPM will cause a first interference with a second expected sound expected to be generated by the second propeller when rotated by the motor at the RPM, the first interference resulting in an expected net effect sound that is representative of a combination of the first expected sound and the second expected sound.

13. The propulsion apparatus of claim 12 , wherein:
a second distance between the second position and the third position is determined based at least in part on:
the expected net effect sound; and
a third expected sound expected to be generated by the third propeller when rotated by the motor at the RPM.

14. The propulsion apparatus of claim 13 , wherein the second distance is further selected such that the expected net effect sound will cause a second interference with the third expected sound expected to be generated by the third propeller when rotated by the motor at the RPM, the second interference resulting in an expected combined net effect that is representative of a combination of the expected net effect sound and the third expected sound.

15. The propulsion apparatus of claim 6 , wherein at least one of the first pitch, the second pitch, or the third pitch are different.

16. The propulsion apparatus of claim 6 , wherein the operational profile comprises at least one of a desired efficiency, a commanded lifting force, a desired agility, and a desired sound profile.

17. An unmanned aerial vehicle (“UAV”) apparatus, comprising:
a body;
a propulsion mechanism coupled to the body, including:
a motor;
a shaft coupled to and extending from the motor;
a first propeller coupled to the shaft and rotatable by the shaft in a first direction;
a second propeller coupled to the shaft and coaxially aligned with the first propeller and rotatable in the first direction; and
a third propeller coupled to the shaft and coaxially aligned with the first propeller and rotatable in the first direction; and

a controller configured to individually engage each of the first propeller, the second propeller, and the third propeller to be rotated by the motor based at least in part on an operational profile associated with the UAV apparatus;
wherein each

Assignees

• Amazon Tech Inc

Inventors

• Beckman Brian C
• Brodie John Raymond
• Coralic Vedran
• Grenier Taylor David
• Kimchi Gur
• Shiosaki Dominic Timothy
• Welsh Ricky Dean
• Whitlock Richard Philip

Classifications

• B64C11/28 Primary

  Collapsible or foldable blades · CPC title

• B64C3/54

  Varying in area · CPC title

• B64C3/141

  Circulation Control Airfoils · CPC title

• B64C3/46

  by inflatable elements · CPC title

• B64C11/48 Primary

  Units of two or more coaxial propellers · CPC title