Soft in-plane tiltrotor hub

• US 7,828,525 B2
• Filed: 08/27/2004
• Issued: 11/09/2010
• Est. Priority Date: 08/27/2003
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Newman, Thomas J., Corso, Lawrence M., Schellhase, Ernst C., Baskin, Bryan, Hollimon, Charles L., Robertson, Daniel B., Bothwell, Christopher M., Braswell, James L. Jr., Campbell, Thomas C., Stamps, Frank B., Smith, Michael R., Popelka, David A.
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US10/567,886
• Publication Number:
  US 20080247876A1
• Time in Patent Office: 2,265 Days
• Field of Search: 416/106, 416/107, 416/134.A, 416/140, 416/141, 416148-150, 244/17.11, 188/282.1, 188/322.15, 188/299.1, 188/319.2, 188/283, 188/266.3
• US Class Current: 416/134.00A
• CPC Class Codes: B64C 27/35 having elastomeric joints
• CPC Class Codes: B64C 27/39 with individually articulated blades, i.e. with flapping or drag hinges
• CPC Class Codes: B64C 27/51 Damping of blade movements
• CPC Class Codes: F16F 13/08 the plastics spring forming at least a part of the wall of the fluid chamber of the damper F16F13/20 - F16F13/24 take precedence
• CPC Class Codes: F16F 13/24 the central part of the unit being supported by one element and both extremities of the unit being supported by a single other element, i.e. double acting mounting
• CPC Class Codes: F16F 13/26 characterised by adjusting or regulating devices responsive to exterior conditions F16F13/101 takes precedence
• CPC Class Codes: F16F 2230/30 Sealing arrangements

Abstract

A rotor hub assembly for a rotary-wing aircraft has a central member and a plurality of blade grips adapted for attaching rotor blades to the central member. The blade grips are pivotally attached to the central member and are capable of pivoting about a pivot axis generally normal to a plane of rotation of the blades. The pivoting allows for in-plane motion of the blades relative to the central member. A damper is operably connected to each blade grip for damping the in-plane motion of the associated blade, each damper being selectively switchable between at least two spring rates.

Claims

1. A rotor for a rotary-wing aircraft, the rotor assembly comprising:

a central member;

a plurality of blade attachment members adapted for attaching rotor blades to the central member, the blade attachment members being pivotally attached to the central member and capable of pivoting about a pivot axis generally normal to a plane of rotation of the blades, the pivoting allowing for in-plane motion of the blades relative to the central member; and

a damper having a housing and a piston movably carried within the housing, the piston having fluid passages therethrough and valve means for controlling the flow of fluid through at least one of the passages, the piston being sealingly connected to an inner surface of the housing with deformable elements, the deformable elements allowing movement of the piston relative to the housing through elastic shearing of the deformable elements, the deformable elements also being deformable by a force exerted by the piston on a fluid in communication with the deformable elements through bulging deformation of the deformable elements, the valve means allowing for selective switching between a first spring rate, in which elastic shearing provides a dominant spring force, and a second spring rate, in which bulging deformation provides the dominant spring force;

wherein each damper is operably connected to an inner end of each blade attachment member for damping the in-plane motion of the associated blade.