Rotor hub for use with high-inertia blades
A rotor hub has a yoke with radial arms allowing flapping of connected blades about a flap axis. A grip is rigidly attached to each blade, and a lead-lag bearing connects each grip to one of the arms, the bearing defining a lead-lag axis outboard of the flap axis. Each arm has a pair of straps located on opposite sides of the rotor plane for transferring centrifugal force from the blades to the central portion of the yoke. A pair of lead-lag dampers is provided for each grip, the dampers of each pair being located on opposite sides of the rotor plane and connecting an inboard end portion of the grip to the adjacent strap. In-plane motion of a blade causes rotation of the attached grip about the lead-lag axis, causing opposite motion of an inboard end portion of the grip. The dampers act to oppose rotation of the grip.
1. A rotor hub for an aircraft, the rotor hub connecting outboard rotor blades to an inboard central mast for rotation with the mast, the blades defining a rotor plane, the rotor hub comprising:
a yoke having flexure arms extending radially outboard from a central portion of the yoke, each arm allowing for flapping of the associated blade about a flap axis;
a plurality of blade grips, an outboard end portion of each grip being rigidly attached to one of the blades;
a lead-lag bearing connecting a central portion of each grip to an outboard end portion of one of the arms, the lead-lag bearing defining a lead-lag axis generally normal to the rotor plane and outboard of the flapping axis;
a pair of straps for each arm, the straps being located on opposite sides of the rotor plane and adapted to transfer centrifugal force from the blades to the central portion of the yoke, such that each arm is substantially free of centrifugal force from the associated blade; and
a pair of lead-lag dampers for each grip, the dampers of each being located on opposite sides of the rotor plane and connecting an inboard end portion of the associated grip to the adjacent associated strap;
wherein in-plane lead or lag motion of one of the blades causes rotation of the attached grip about the associated lead-lag axis and causes motion in an opposite direction of an inboard end portion of the grip, and the associated dampers oppose rotation of the grip and the lead-lag motion of the attached blade.
2. The rotor hub of claim 1 , further comprising:
a spherical bearing connecting inboard end portions of each in a pair of straps to the central portion of the yoke.
3. The rotor hub of claim 1 , wherein the dampers are elastomeric.
4. The rotor hub of claim 1 , wherein the dampers comprise a hydraulic damping system.
5. The rotor hub of claim 1 , wherein the dampers comprise a pneumatic damping system.
6. The rotor hub of claim 1 , wherein the dampers comprise an electric damping system.
7. The rotor hub of claim 1 , wherein the dampers are actively controlled.
8. The rotor hub of claim 1 , wherein the lead-lag bearing is elastomeric.
9. A method of damping in-plane motion of blades connected to a rotor hub of an aircraft, the rotor hub connecting outboard rotor blades to an inboard central mast for rotation with the mast, the blades defining a rotor plane, the method comprising:
(a) providing a yoke having flexure arms extending radially outboard from a central portion of the yoke, each arm allowing for flapping of the associated blade about a flap axis;
(b) providing a plurality of blade grips, an outboard end portion of each grip being rigidly attached to one of the blades;
(c) providing a lead-lag bearing connecting a central portion of each grip to an outboard end portion of one of the arms, the lead-lag bearing defining a lead-lag axis generally normal to the rotor plane and outboard of the flapping axis;
(d) providing a pair of straps for each arm, the straps being located on opposite sides of the rotor plane and adapted to transfer centrifugal force from the blades to the central portion of the yoke, such that each arm is substantially free of centrifugal force from the associated blade;
(e) providing a pair of lead-lag dampers for each grip, the dampers of each being located on opposite sides of the rotor plane and connecting an inboard end portion of the associated grip to the adjacent associated strap;
(f) damping in-plane lead or lag motion of each blade by opposing rotation of the attached grip with the associated dampers.
10. An aircraft, comprising a rotor hub connecting outboard rotor blades to an inboard central mast for rotation with the mast, the blades defining a rotor plane, the rotor hub comprising:
a yoke having flexure arms extending radially outboard from a central portion of the yoke, each arm allowing for flapping of the associated blade about a flap axis;
a plurality of blade grips, an outboard end portion of each grip being rigidly attached to one of the blades;
a lead-lag bearing connecting a central portion of each grip to an outboard end portion of one of the arms, the lead-lag bearing defining a lead-lag axis generally normal to the rotor plane and outboard of the flapping axis;
a pair of straps for each arm, the straps being located on opposite sides of the rotor plane and adapted to transfer centrifugal force from the blades to the central portion of the yoke, such that each arm is substantially free of centrifugal force from the associated blade; and
a pair of lead-lag dampers for each grip, the dampers of each being located on opposite sides of the rotor plane and connecting an inboard end portion of the associated grip to the adjacent associated strap;
wherein in-plane lead or lag motion of one of the blades causes rotation of the attached grip about the associated lead-lag axis and causes motion in an opposite direction of an inboard end portion of the grip, and the associated dampers oppose rotation of the grip and the lead-lag motion of the attached blade.
11. The aircraft of claim 10 , further comprising:
a spherical bearing connecting inboard end portions of each in a pair of straps to the central portion of the yoke.
12. The aircraft of claim 10 , wherein the dampers comprise a hydraulic damping system.
13. The aircraft of claim 10 , wherein the dampers comprise a pneumatic damping system.
14. The aircraft of claim 10 , wherein the dampers comprise an electric damping system.
15. The aircraft of claim 10 , wherein the dampers are actively controlled.
16. The aircraft of claim 10 , wherein the lead-lag bearing is elastomeric.