Rotorcraft flapping lock

Patent metadata

Field	Value
Publication number	US-11014659-B2
Application number	US-201816042706-A
Country	US
Kind code	B2
Filing date	Jul 23, 2018
Priority date	May 22, 2013
Publication date	May 25, 2021
Grant date	May 25, 2021

Abstract

A method of selectively preventing flapping of a rotor hub includes providing a flapping lock proximate to a rotor hub and shaft assembly and moving the flapping lock from an unlocked position to a locked position, the flapping lock operable in the locked position to prevent at least some flapping movement of the rotor hub relative to the shaft, the flapping lock operable in the unlocked position to allow the at least some flapping movement of the rotor hub relative to the shaft.

First claim

What is claimed is:

1. A method of selectively preventing flapping of a rotor hub, comprising:
providing a flapping lock proximate to the rotor hub and shaft assembly;
moving the flapping lock from an unlocked position to a locked position, the flapping lock operable in the locked position to prevent at least some flapping movement of the rotor hub relative to the shaft, the flapping lock operable in the unlocked position to allow the at least some flapping movement of the rotor hub relative to the shaft;
wherein moving the flapping lock from the unlocked position to the locked position comprises moving a downstop in mechanical communication with the shaft towards a flapping stop in mechanical communication with the rotor hub.

2. The method of claim 1 , further comprising supporting a load absorber positioned between the downstop and the flapping stop.

3. A method of folding a rotor blade of a rotorcraft, comprising:
supporting a blade at an axis of rotation;
reducing torque generated by the rotor blade;
preventing flapping of the rotor blade;
slowing rotation of the rotor blade;
locking a rotational position of the rotor blade to a predetermined azimuth angle;
preventing pitch displacements of the rotor blade; and
pivoting the blade about the axis of rotation by repositioning a swashplate in mechanical communication with the blade.

4. The method of claim 3 , wherein:
reducing torque generated by the rotor blade comprises repositioning the swashplate to a first position;

preventing flapping motions of the rotor blade comprises locking a hub in mechanical communication with the rotor blade at a substantially fixed flapping angle;
slowing rotation of the rotor blade comprises repositioning the swashplate to a second position;
preventing pitch displacements of the rotor blade comprises locking a grip associated with the rotor blade to the hub; and

pivoting the rotor blade about the axis of rotation comprises repositioning the swashplate to a third position.

5. The method of claim 4 , wherein pivoting the rotor blade about the axis of rotation comprises repositioning the swashplate to the third position further comprises:
allowing folding movement of a linkage in mechanical communication with the swashplate by unlocking the linkage from the grip; and

repositioning the swashplate to the third position such that the linkage pivots the rotor blade about the axis of rotation.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Schank Troy
• Stamps Frank B

Classifications

• B64C11/28

  Collapsible or foldable blades · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C27/615

  including flaps mounted on blades · CPC title

• B64C27/32

  Rotors · CPC title

• B64C27/52

  Tilting of rotor bodily relative to fuselage (of see-saw type construction B64C27/43) · CPC title