Folding concentrically mounted propeller blades for drag reduction

Patent metadata

Field	Value
Publication number	US-10843795-B2
Application number	US-201816007918-A
Country	US
Kind code	B2
Filing date	Jun 13, 2018
Priority date	Jun 13, 2018
Publication date	Nov 24, 2020
Grant date	Nov 24, 2020

Abstract

A propulsion unit includes a motor rotor, propeller blades, and a pivot stop. The motor rotor spins about a central rotational axis. The propeller blades, including first and second propeller blades, each having a proximal base mounted to the motor rotor such that the propeller blades are rotatable about the central rotational axis. The second propeller blade is pivotally attached to the motor rotor to pivot about the central rotational axis independent of the motor rotor by a limited angle. The pivot stop mechanically limits an amount of pivoting of the second propeller blade relative to the first propeller blade.

First claim

What is claimed is:

1. A propulsion unit, comprising:
a motor rotor that spins about a central rotational axis;
propeller blades, including first and second propeller blades, each having a proximal base mounted to the motor rotor such that the propeller blades are rotatable about the central rotational axis, wherein the second propeller blade is pivotally attached to the motor rotor to pivot about the central rotational axis independent of the motor rotor by a limited angle;
a pivot stop to mechanically limit an amount of pivoting of the second propeller blade relative to the first propeller blade; and
a washer flange disposed between the proximal bases of the first and second propeller blades to offset the second propeller blade relative to the first propeller blade along the center rotational axis.

2. The propulsion unit of claim 1 , wherein the propeller blades fold or unfold between a deployed position that provides propulsion and a stowed position having a reduced drag profile in a direction that is orthogonal to the central rotational axis.

3. The propulsion unit of claim 1 , wherein the first propeller blade is non-pivotally attached to the motor rotor to rotate about the central rotational axis in a fixed relation to the motor rotor.

4. The propulsion unit of claim 1 , wherein the pivot stop comprises a pair of rotationally offset protrusions extending from opposite sides of the washer flange that engage cutouts in the proximal bases of the first and second propeller blades.

5. The propulsion unit of claim 1 , further comprising:
an alignment boss attached to and extending from the washer flange about which a hole in the proximal base of the second propeller blade is located.

6. The propulsion unit of claim 5 , wherein the washer flange includes a recess that mates to and aligns with a protruding ridge on the motor rotor.

7. The propulsion unit of claim 5 , further comprising:
a retainer cap for clamping the propeller blades and the washer flange to the motor rotor; and
a mechanical fastener that inserts through holes in the retainer cap and the alignment boss to thread into the motor rotor.

8. A propulsion unit, comprising:
a motor rotor that spins about a central rotational axis;
propeller blades, including first, second, and third propeller blades, each having a proximal base mounted to the motor rotor such that the propeller blades are rotatable about the central rotational axis, wherein the second propeller blade is pivotally attached to the motor rotor to pivot about the central rotational axis independent of the motor rotor by a limited angle;
a pivot stop to mechanically limit an amount of pivoting of the second propeller blade relative to the first propeller blade; and
a second pivot stop integrated onto a second washer flange disposed to offset the proximal bases of the second and third propeller blades.

9. The propulsion unit of claim 8 , wherein the pivot stop and the second pivot stop offset rotational positions of the propeller blades relative to each other by equal angles when the propeller blades are unfolded to a deployed position.

10. The propulsion unit of claim 8 , wherein the propeller blades further include a fourth propeller blade, the propulsion unit further comprises:
a third pivot stop integrated onto a third washer flange disposed between the proximal bases of the third and fourth propeller blades.

11. An aerial vehicle, comprising:
an airframe;
a horizontal propulsion unit mounted to the airframe and oriented to provide horizontal propulsion to the aerial vehicle; and
a vertical propulsion unit mounted to the airframe and oriented to provide vertical propulsion to the aerial vehicle, the vertical propulsion unit including:
a motor rotor that spins about a central rotational axis;
propeller blades, including first and second propeller blades, each having a proximal base mounted to the motor rotor such that the propeller blades are rotatable about the central rotational axis, wherein the second propeller blade is pivotally attached to the motor rotor to pivot about the central rotational axis independent of the motor rotor by a limited angle;
a pivot stop disposed relative to the first and second propeller blades to mechanically limit an amount of pivoting of the second propeller blade relative to the first propeller blade; and
a washer flange disposed between the proximal bases of the first and second propeller blades to offset the second propeller blade relative to the first propeller blade along the center rotational axis.

12. The aerial vehicle of claim 11 , wherein the propeller blades of the vertical propulsion unit fold or unfold between a deployed position that provides the vertical propulsion and a stowed position having a reduced drag profile during a forward motion of the aerial vehicle.

13. The aerial vehicle of claim 12 , wherein the propeller blades unfold to the deployed position by engaging the pivot stop between the first and second propeller blades when the motor rotor of the vertical propulsion unit is spinning and fold to the stowed position due to a wind resistance resulting from the forward motion of the aerial vehicle when the motor rotor of the vertical propulsion unit is not spinning.

14. The aerial vehicle of claim 12 , wherein the vertical propulsion unit is adapted to apply a reverse torque impulse to initiate folding of the propeller blades to the stowed position.

15. The aerial vehicle of claim 11 , wherein the first propeller blade is non-pivotally attached to the motor rotor to rotate about the central rotational axis in a fixed relation to the motor rotor.

16. The aerial vehicle of claim 11 , wherein the pivot stop comprises a pair of rotationally offset protrusions extending from opposite sides of the washer flange that engage cutouts in the proximal bases of the first and second propeller blades.

17. The aerial vehicle of claim 11 , further comprising:
an alignment boss attached to and extending from the washer flange about which a hole in the proximal base of the second propeller blade is located.

18. The aerial vehicle of claim 17 , wherein the washer flange includes a recess that mates to and aligns with a protruding ridge on the motor rotor.

19. The aerial vehicle of claim 11 , wherein the propeller blades further include a third propeller blade, the aerial vehicle further comprises:
a second pivot stop integrated onto a second washer flange disposed between the proximal bases of the second and third propeller blades.

20. The aerial vehicle of claim 19 , wherein the pivot stop and the second pivot stop offset rotational positions of the propeller blades relative to each other by equal angles when the propeller blades are unfolded to a deployed position.

21. An aerial vehicle, comprising:
an airframe;
a horizontal propulsion unit mounted to the airframe and oriented to provide horizontal propulsion to the aerial vehicle; and
a vertical propulsion unit mounted to the airframe and oriented to provide vertical propulsion to the aerial vehicle, the vertical propulsion unit including:
a motor rotor that spins about a central rotational axis;
propeller blades, including first and second propeller blades, each having a proximal base mounted to the motor rotor such that the propeller blades are rotatable about the central rotational axis, wherein the second propeller blade is pivotally attached to the motor rotor to pivot about the central rotational axis independent of the motor rotor by a limited angle;

Assignees

• Wing Aviation Llc

Inventors

• Prager André

Classifications

• B64U10/20

  Vertical take-off and landing [VTOL] aircraft (flying platforms B64U10/13; helicopters B64U10/17) · CPC title

• B64C29/0025

  the propellers being fixed relative to the fuselage · CPC title

• B64C11/28 Primary

  Collapsible or foldable blades · CPC title

• B64C27/50 Primary

  Blades foldable to facilitate stowage of aircraft · CPC title

• B64C27/022

  Devices for folding or adjusting the blades · CPC title