Passive rotor alignment in a free-wheeling state

Patent metadata

Field	Value
Publication number	US-11305871-B2
Application number	US-201916515340-A
Country	US
Kind code	B2
Filing date	Jul 18, 2019
Priority date	Jul 18, 2019
Publication date	Apr 19, 2022
Grant date	Apr 19, 2022

Abstract

Rotor assemblies for aircraft are described where one or more blades of the rotor assembly includes a blade alignment device that passively orients a blade in response to an airflow around the blade alignment device when the rotor assembly is free-wheeling. One embodiment comprises a method of operating a rotor assembly for aircraft. The method comprises operating the rotor assembly in a free-wheeling state, where the rotor assembly includes a rotary hub that rotates about an axis and a plurality of blades extending radially from the rotary hub. At least one of the plurality of blades includes a blade alignment device. The method further comprises aligning the at least one of the plurality of blades in response to airflow around the blade alignment device when the rotor assembly is in the free-wheeling state.

First claim

What is claimed is:

1. A method of operating a rotor assembly for aircraft, the method comprising:
operating the rotor assembly in a free-wheeling state when the aircraft is in forward flight, the rotor assembly comprising a rotary hub configured to rotate about an axis, and a plurality of blades extending radially from the rotary hub, wherein at least one of the plurality of blades includes a blade alignment device; and
aligning the at least one of the plurality of blades that includes the blade alignment device with airflow generated when the aircraft is in forward flight in response to the airflow around the blade alignment device when the rotor assembly is in the free-wheeling state,
wherein the blade alignment device comprises a spanwise fin pivotably coupled to an airfoil surface of the at least one of the plurality of blades along a longitudinal direction,
wherein the spanwise fin pivots along an edge substantially parallel with the longitudinal direction to project away from the airfoil surface in a deployed position when the rotor assembly is in the free-wheeling state, and pivots along the edge to lay flat with respect to the airfoil surface in a stowed position when the rotor assembly is driven in rotation.

2. The method of claim 1 , wherein:
the spanwise fin is held within a surface relief of the airfoil surface when in the stowed position, and pivots out of the surface relief to the deployed position.

3. The method of claim 2 , wherein:
the spanwise fin is held within the surface relief of the airfoil surface by a retaining device.

4. The method of claim 1 , wherein:
the spanwise fin passively transitions to the stowed position when a rate of rotation of the rotor assembly is greater than a first rotational rate,
the spanwise fin passively transitions to the deployed position when the rate of rotation of the rotor assembly is less than a second rotational rate, and
the first rotational rate is greater than the second rotational rate.

5. The method of claim 1 , wherein:
the spanwise fin passively transitions to the stowed position when a chordwise airflow for the at least one of the plurality of blades is greater than a first airflow rate,
the spanwise fin passively transitions to the deployed position when the chordwise airflow is less than a second airflow rate, and
the first airflow rate is greater than the second airflow rate.

6. The method of claim 1 , wherein:
the spanwise fin is disposed near a tip of the at least one of the plurality of blades.

7. A rotor assembly for aircraft, the rotor assembly comprising:
a rotary hub configured to rotate about an axis; and
a plurality of blades extending radially from the rotary hub,
wherein at least one of the plurality of blades includes a blade alignment device,
wherein the rotor assembly is configured to operate in a free-wheeling state when the aircraft is in forward flight,
wherein the blade alignment device is configured to align the at least one of the plurality of blades with airflow generated when the aircraft is in forward flight in response to airflow around the blade alignment device when the rotor assembly is in the free-wheeling state,
wherein the blade alignment device comprises a spanwise fin pivotably coupled to an airfoil surface of the at least one of the plurality of blades along a longitudinal direction,
wherein the spanwise fin pivots along an edge substantially parallel with the longitudinal direction to project away from the airfoil surface in a deployed position when the rotor assembly is in the free-wheeling state, and pivots along the edge to lay flat with respect to the airfoil surface in a stowed position when the rotor assembly is driven in rotation.

8. The rotor assembly of claim 7 , wherein:
the spanwise fin is held within a surface relief of the airfoil surface when in the stowed position, and pivots out of the surface relief to the deployed position.

9. The rotor assembly of claim 8 , wherein:
the spanwise fin is held within the surface relief of the airfoil surface by a retaining device.

10. The rotor assembly of claim 9 , wherein:
the spanwise fin is configured to project from the airfoil surface utilizing a spring.

11. The rotor assembly of claim 7 , wherein:
the spanwise fin is configured to passively transition to the stowed position when a rate of rotation of the rotor assembly is greater than a first rotational rate, and to passively transition to the deployed position when the rate of rotation is less than a second rotational rate; and
the first rotational rate is greater than the second rotational rate.

12. The rotor assembly of claim 7 , wherein:
the spanwise fin is configured to passively transition to the stowed position when a chordwise airflow for the at least one of the plurality of blades is greater than a first airflow rate, and to passively transition to the deployed position when the chordwise airflow is less than a second airflow rate; and
the first airflow rate is greater than the second airflow rate.

13. The rotor assembly of claim 7 , wherein:
the spanwise fin is disposed near a tip of the at least one of the plurality of blades.

14. The rotor assembly of claim 7 , wherein:
the airfoil surface comprises a lower surface of the at least one of the plurality of blades.

15. An aircraft, comprising:
at least one rotor assembly configured to provide lift for the aircraft, the at least one rotor assembly comprising:
a rotary hub configured to rotate about an axis; and
a plurality of blades extending radially from the rotary hub,
wherein the at least one rotor assembly is configured to operate in a free-wheeling state when the aircraft is in forward flight,
wherein at least one of the plurality of blades includes a blade alignment device, the blade alignment device configured to align the at least one of the plurality of blades with airflow generated when the aircraft is in forward flight in response to airflow around the blade alignment device when the rotor assembly is in the free-wheeling state,

wherein the blade alignment device comprises a spanwise fin pivotably coupled to an airfoil surface of the at least one of the plurality of blades along a longitudinal direction,
wherein the spanwise fin pivots along an edge substantially parallel with the longitudinal direction to project away from the airfoil surface in a deployed position when the rotor assembly is in the free-wheeling state, and pivots along the edge to lay flat with respect to the airfoil surface in a stowed position when the rotor assembly is driven in rotation.

16. The aircraft of claim 15 , wherein:
the spanwise fin is held within a surface relief of the airfoil surface when in the stowed position, and pivots out of the surface relief to the deployed position.

17. The aircraft of claim 16 , wherein:
the spanwise fin is held within the surface relief of the airfoil surface by a retaining device.

18. The aircraft of claim 15 , wherein:
the spanwise fin is configured to passively transition to the stowed position when a rate of rotation of the at least one rotor assembly is greater than a first rotational rate, and to passively transition to the deployed position when the rate of rotation is less than a second rotational rate, and
the first rotational rate is greater than the second rotational rate.

19. The aircraft of claim 15 , wherein:
the spanwise fin is configured to passively transition to the stowed position when a chordwise airflow for the at least one of the plurality of blades is greate

Assignees

• Aurora Flight Sciences Corp

Inventors

• Heafitz Andrew Mark
• Parks Robert William

Classifications

• B64C27/30 Primary

  with provision for reducing drag of inoperative rotor · CPC title

• B64C27/46

  Blades · CPC title

• B64C11/28

  Collapsible or foldable blades · CPC title

• B64C27/463

  Blade tips · CPC title

• B64C27/022

  Devices for folding or adjusting the blades · CPC title