Pitch-fold lock

Patent metadata

Field	Value
Publication number	US-11511848-B2
Application number	US-202016879114-A
Country	US
Kind code	B2
Filing date	May 20, 2020
Priority date	May 20, 2020
Publication date	Nov 29, 2022
Grant date	Nov 29, 2022

Abstract

Embodiments are directed to a blade lock comprising a fold lock adapted to prevent folding of a rotor blade in a fold-lock position and to allow folding of the rotor blade in a pitch-lock position. The blade lock further comprises a pitch lock adapted to allow pitch movement of a rotor blade in a fold-lock position and to prevent pitch movement of the rotor blade in the pitch-lock position. A spring-loaded link pivotally connects both the fold lock and the pitch lock and is adapted to provide passive, overcenter locking in the fold-lock position. An actuator is coupled to the pitch lock and is adapted to move the pitch lock and the fold lock between the fold-lock and pitch-lock positions.

First claim

What is claimed is:

1. A blade lock for a tiltrotor aircraft to enable and disable a folding degree of freedom and a pitching degree of freedom of a rotor blade, the blade lock comprising:
a fold lock adapted to prevent folding of a rotor blade in a fold-lock position and to allow folding of the rotor blade in a pitch-lock position;
a pitch lock adapted to allow pitch movement of a rotor blade in a fold-lock position and to prevent pitch movement of the rotor blade in the pitch-lock position;
a spring-loaded link pivotally connected to both the fold lock and the pitch lock and adapted to provide passive, overcenter locking in the fold-lock position; and
an actuator coupled to the pitch lock and adapted to move the pitch lock and the fold lock between the fold-lock and pitch-lock positions, wherein the actuator is a low-profile rotary actuator having an actuator arm and an activation linkage that is coupled to the pitch lock, and wherein the actuator arm and the activation linkage are adapted to provide passive, overcenter locking in the pitch-lock position.

2. The blade lock of claim 1 , wherein the actuator is a rotary actuator having an actuator arm and an overslung activation linkage that is coupled to the pitch lock, wherein the actuator arm and overslung activation linkage are adapted to provide passive, overcenter locking in the pitch-lock position.

3. The blade lock of claim 1 , wherein the actuator comprises a rotary actuator having an actuator arm and an underslung activation linkage that is coupled to the pitch lock, wherein the actuator arm and underslung activation linkage are adapted to provide passive, overcenter locking in the pitch-lock position.

4. The blade lock of claim 1 , further comprising:
a blade-fold link coupled to the rotor blade, wherein the fold lock enables and disables the folding degree of freedom by unlocking and locking the blade-fold link.

5. The blade lock of claim 1 , further comprising:
a rotor cuff tab and a blade-stop tab, wherein the pitch lock enables and disables the pitching degree of freedom by unlocking and locking the rotor cuff tab and the blade-stop tab together.

6. The blade lock of claim 1 , further comprising:
an attachment point on the pitch lock, the attachment point separated from a pivot axis of the pitch lock by a specified distance, wherein both the spring-loaded link and the actuator are pivotally connected to the attachment point.

7. The blade lock of claim 1 , further comprising:
a first attachment point on the pitch lock, the first attachment point separated from a pivot axis of the pitch lock by a first distance; and
a second attachment point on the pitch lock, the second attachment point separated from the pivot axis of the pitch lock by a second distance that is shorter than the first distance;
wherein the spring-loaded link is pivotally connected to the first attachment point and the actuator is pivotally connected to the second attachment point.

8. The blade lock of claim 1 , further comprising:
a first attachment point on the pitch lock, the first attachment point separated from a pivot axis of the pitch lock by a first distance; and
a second attachment point on the pitch lock, the second attachment point separated from the pivot axis of the pitch lock by a second distance that is longer than the first distance;
wherein the spring-loaded link is pivotally connected to the first attachment point and the actuator is pivotally connected to the second attachment point.

9. A method for enabling and disabling a folding degree of freedom and a pitching degree of freedom of a rotor blade of a tiltrotor aircraft, the method comprising:
rotating a blade lock assembly comprising a spring-loaded link pivotally connecting a pitch lock to a fold lock from a pitch-lock position to a fold-lock position, wherein in the fold-lock position the spring-loaded link provides passive, overcenter locking to the fold lock;
and rotating the blade lock assembly from the fold-lock position to the pitch-lock position, wherein in the pitch-lock position a blade lock actuator provides passive, overcenter locking to the pitch lock.

10. The method of claim 9 , wherein the actuator comprises a flat rotary actuator having an actuator arm and an activation linkage that is coupled to the pitch lock, wherein the actuator arm and the activation linkage are adapted to provide the passive, overcenter locking in the pitch-lock position.

11. The method of claim 9 , wherein the actuator comprises a rotary actuator having an actuator arm and an overslung activation linkage that is coupled to the pitch lock, wherein the actuator arm and the overslung activation linkage are adapted to provide the passive, overcenter locking in the pitch-lock position.

12. The method of claim 9 , wherein the actuator comprises a rotary actuator having an actuator arm and an underslung activation linkage that is coupled to the pitch lock, wherein the actuator arm and the underslung activation linkage are adapted to provide the passive, overcenter locking in the pitch-lock position.

13. The method of claim 9 , wherein the actuator comprises a linear actuator having an actuator shaft that is coupled to the pitch lock.

14. The method of claim 9 , further comprising:
in the fold-lock position, locking a blade-fold link coupled to the rotor blade to disable the folding degree of freedom.

15. The method of claim 9 , further comprising:
in the pitch-lock position, locking a rotor cuff tab and a blade-stop tab together to disable the pitching degree of freedom.

16. The method of claim 9 , wherein the pitch lock further comprises an attachment point separated from a pivot axis of the pitch lock by a specified distance, and wherein both the spring-loaded link and the actuator are pivotally connected to the attachment point.

17. The method of claim 9 , wherein the pitch lock further comprises a first attachment point separated from a pivot axis of the pitch lock by a first distance and a second attachment point separated from the pivot axis of the pitch lock by a second distance that is shorter than the first distance; and wherein the spring-loaded link is pivotally connected to the first attachment point and the actuator is pivotally connected to the second attachment point.

18. The method of claim 9 , wherein the pitch lock further comprises a first attachment point separated from a pivot axis of the pitch lock by a first distance and a second attachment point separated from the pivot axis of the pitch lock by a second distance that is longer than the first distance; and wherein the spring-loaded link is pivotally connected to the first attachment point and the actuator is pivotally connected to the second attachment point.

Assignees

• Bell Textron Inc
• Textron Innovations Inc

Inventors

• Cravener Kyle Thomas
• Maresh Andrew Ryan
• Atkins Brady Garrett
• Schulte Kynn J
• Schank Troy

Classifications

• B64C11/28 Primary

  Collapsible or foldable blades · CPC title

• B64C11/06

  for variable-pitch blades · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C11/065

  variable only when stationary · CPC title