Rotor hub vibration attenuator
First Claim
Patent Images
1. A vibration attenuator for a rotor hub of an aircraft, the rotor hub being configured for being driven in rotation by a mast about an axis of rotation, the vibration attenuator comprising:
- a first weight adapted to be mounted in a rotating system of a rotor hub of an aircraft, each the first weight also being adapted to be rotatable about an axis of rotation of the hub relative to the hub and motor means for rotating each the first weight about the axis of rotation at a selected speed during operation;
wherein during operation each the first weight is driven in rotation for creating oscillatory shear forces for attenuation of rotor-induced vibrations having a selected frequency;
wherein the location of the first weight is selectively movable between an inner radial position and an outer radial position, the location being between a center of mass of the first weight and the axis of rotation, the inner radial position providing minimal shear forces, the outer radial position providing maximum shear forces, the first weight positioned above the rotor hub and mounted on said motor means.
2 Assignments
0 Petitions
Accused Products
Abstract
A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency.
-
Citations
17 Claims
-
1. A vibration attenuator for a rotor hub of an aircraft, the rotor hub being configured for being driven in rotation by a mast about an axis of rotation, the vibration attenuator comprising:
-
a first weight adapted to be mounted in a rotating system of a rotor hub of an aircraft, each the first weight also being adapted to be rotatable about an axis of rotation of the hub relative to the hub and motor means for rotating each the first weight about the axis of rotation at a selected speed during operation; wherein during operation each the first weight is driven in rotation for creating oscillatory shear forces for attenuation of rotor-induced vibrations having a selected frequency; wherein the location of the first weight is selectively movable between an inner radial position and an outer radial position, the location being between a center of mass of the first weight and the axis of rotation, the inner radial position providing minimal shear forces, the outer radial position providing maximum shear forces, the first weight positioned above the rotor hub and mounted on said motor means. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
-
-
9. A vibration attenuator for a rotor hub of an aircraft, the rotor hub being configured for being driven in rotation by a mast about an axis of rotation, the vibration attenuator comprising:
-
a first set of weights, the first set comprising at least two weights, each weight being adapted to be mounted in a rotating system of a rotor hub of an aircraft, each weight also being adapted to be rotatable about an axis of rotation of the hub relative to the hub and to each other weight, each weight having a center of mass located a distance from the axis of rotation; and motor means for rotating each weight about the axis of rotation at a selected speed during operation; wherein during operation the weights of the first set may be angularly positioned about the axis of rotation relative to each other, so as to create oscillatory shear forces for attenuation of rotor-induced vibrations having a selected frequency; wherein the location of the first set of weights are selectively movable between an inner radial position and an outer radial position, the location being between a center of mass of the first set and the axis of rotation, the inner radial position providing minimal shear forces, the outer radial position providing maximum shear forces, the first set positioned above the rotor hub and mounted on said motor means. - View Dependent Claims (10, 11, 12, 13, 14)
-
-
15. A method of attenuating vibrations in an aircraft having at least one rotor having blades, the rotor having a rotor hub configured for being driven in rotation by a mast about an axis of rotation, the method comprising:
-
(a) locating a first rotatable weight in a rotating system of a rotor hub, the first rotatable weight positioned above the rotor hub and mounted to a motor means; (b) rotating each the first weight with said motor at a selected speed about an axis of rotation of the hub, each the first weight rotating relative to the hub; and (c) controlling the rotation of each the first weight for creating oscillatory shear forces that oppose rotor-induced vibrations having a selected frequency; and (d) selectively positioning the first weight between an inner radial position and an outer radial position, the inner radial position providing minimal shear forces, the outer radial position providing maximum shear forces, the location being between a center of mass of the weight and the axis of rotation. - View Dependent Claims (16, 17)
-
Specification