Stiff-in-plane rotor configuration

Patent metadata

Field	Value
Publication number	US-9878782-B2
Application number	US-201514623615-A
Country	US
Kind code	B2
Filing date	Feb 17, 2015
Priority date	Jan 19, 2009
Publication date	Jan 30, 2018
Grant date	Jan 30, 2018

Abstract

A rotor assembly for a rotary-wing aircraft, the rotor having a central hub assembly with a flexure-type, twist-shank yoke with multiple arms, each arm being adapted for a rotor blade to be mounted thereto. The arms provide for pitch changes of blades attached to the yoke through twisting of portions of the arms about a corresponding pitch axis. An inboard pitch bearing associated with each arm is attached to the hub assembly and allows for rotation of the attached blade about the pitch axis, the inboard pitch bearing also allowing for out-of-plane motion of the arm relative to the hub assembly about a flapping axis. An outboard pitch bearing associated with each arm is attached to the associated arm a selected distance from the inboard pitch bearing and allows for rotation of the attached blade about the pitch axis.

First claim

What is claimed is:

1. A rotor assembly for a rotary-wing aircraft, the rotor comprising:
a central hub assembly having a flexure-type, twist-shank yoke with multiple arms, each arm being adapted for a rotor blade to be mounted thereto, the arms providing for pitch changes of blades attached to the yoke through twisting of portions of the arms about a corresponding pitch axis;
an outboard bearing support associated with each arm;
an inboard pitch bearing associated with each arm, the inboard pitch bearing being attached to the hub assembly and allowing for rotation of the attached blade about the pitch axis, the inboard pitch bearing also allowing for out-of-plane motion of the arm relative to the hub assembly about a flapping axis; and
an outboard pitch bearing associated with each arm, the outboard pitch bearing being attached to the associated arm a selected distance from the inboard pitch bearing and allowing for rotation of the attached blade about the pitch axis;
wherein each arm extends through a rectangular support aperture in the associated outboard bearing support.

2. The rotor assembly according to claim 1 , further comprising:
an inboard bearing support associated with each arm, each inboard support bearing being carried on an inboard support;
wherein each arm extends through a support aperture in the associated inboard support.

3. The rotor assembly according to claim 1 , further comprising:
an arm aperture formed in an inboard portion of each arm;
an inboard beam connected to each inboard pitch bearing and adapted to be attached to an associated blade, the beam extending through the associated arm aperture.

4. The rotor assembly according to claim 1 , further comprising:
at least one arm clamp surrounding a portion of an arm, so as to limit separation of layers of the arm;
wherein the at least one arm clamp is entirely external to the arm.

5. The rotor assembly according to claim 1 , wherein the yoke is formed from multiple layers of composite material separated by layers of elastomeric material.

6. A rotor assembly for a rotary-wing aircraft, the rotor comprising:
a hub assembly having a flexure-type yoke with multiple arms, each arm being adapted for a rotor blade to be mounted thereto;
an outboard hearing support associated with each arm;
an inboard pitch bearing and an outboard pitch bearing associated with each arm, the bearings for each arm being coaxial and defining a pitch axis extending generally along the length of the associated arm, the bearings for each arm being adapted to allow rotation of an attached blade about the pitch axis relative to the hub assembly; and

an annular brace extending between the inboard and outboard pitch bearings of each arm, each brace maintaining the associated bearings in a coaxial orientation during flapping movement of the arms relative to the hub assembly;
wherein each arm extends through a rectangular support aperture in the associated outboard hearing support.

7. The rotor assembly according to claim 6 , wherein the brace acts as an inner race for the pitch bearings of each arm.

8. The rotor assembly according to claim 6 , wherein the outboard pitch bearing is attached to the associated arm.

9. The rotor assembly according to claim 6 , wherein the inboard pitch bearing is attached to the hub assembly.

10. The rotor assembly according to claim 6 , wherein the yoke is formed from multiple layers of composite material separated by layers of elastomeric material.

Assignees

• Textron Innovations Inc

Inventors

• Stamps Frank B
• Tisdale Patrick R
• Donovan Tom
• Rauber Richard E

Classifications

• B64C27/48

  Root attachment to rotor head · CPC title

• B64C27/32

  Rotors · CPC title

• B64C27/35 Primary

  having elastomeric joints · CPC title

• B64C27/33 Primary

  having flexing arms · CPC title

• B64C27/39

  with individually articulated blades, i.e. with flapping or drag hinges · CPC title