The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Nov. 20, 2012

Filed:

May. 16, 2011
Applicants:

Mark Jolly, Raleigh, NC (US);

Stephen Hildebrand, Apex, NC (US);

Russell Altieri, Cary, NC (US);

Matthew Ferguson, Erie, PA (US);

Douglas Ivers, Cary, NC (US);

Inventors:

Mark Jolly, Raleigh, NC (US);

Stephen Hildebrand, Apex, NC (US);

Russell Altieri, Cary, NC (US);

Matthew Ferguson, Erie, PA (US);

Douglas Ivers, Cary, NC (US);

Assignee:

Lord Corporation, Cary, NC (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F04D 29/26 (2006.01); F01D 5/26 (2006.01); B64C 11/00 (2006.01);
U.S. Cl.
CPC ...
Abstract

Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass. The electronics housing cavity contains an electronics control system which receives sensor outputs and electrically controls and drives the first motor and the second motor such that the first imbalance mass and the second imbalance mass are driven at a vibration canceling rotation frequency greater than the operational rotation frequency wherein the helicopter rotary wing hub periodic vibrations are reduced.


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