US 12,214,869 B2
Vibration control assembly
William A. Welsh, New Haven, CT (US); Yuriy Gmirya, Woodbridge, CT (US); and Damaris R. Zachos, Lyme, CT (US)
Assigned to LOCKHEED MARTIN CORPORATION, Bethesda, MD (US)
Filed by Lockheed Martin Corporation, Bethesda, MD (US)
Filed on Oct. 17, 2023, as Appl. No. 18/488,320.
Application 18/488,320 is a division of application No. 16/852,698, filed on Apr. 20, 2020, granted, now 11,794,883.
Prior Publication US 2024/0059405 A1, Feb. 22, 2024
Int. Cl. B64C 27/00 (2006.01); F16F 15/22 (2006.01); F16F 15/30 (2006.01)
CPC B64C 27/001 (2013.01) [F16F 15/223 (2013.01); F16F 15/30 (2013.01); F16F 2222/08 (2013.01)] 17 Claims
OG exemplary drawing
 
1. An aircraft comprising:
an airframe;
a main rotor system mounted to the airframe, wherein the main rotor system is rotatable about a rotor axis and which imparts a vibration into the airframe; and
at least one vibration control assembly operably coupled to at least one of the main rotor system and the airframe to suppress the vibration, the at least one vibration control assembly including:
a housing having an interior region;
an inner mass disposed within the interior region of the housing, the inner mass rotatable about a first axis and including a second portion rotatable about a second axis; and
a driving source mounted within the interior region of the housing, the driving source operable to interact with a magnetic field of the inner mass to rotate the inner mass about the first axis;
wherein the driving source is operable to drive rotation of the second portion about the second axis, wherein the driving source is configured to control a rotational speed of the second portion about the second axis and a rotational speed of the inner mass about the first axis, wherein the rotational speed of the second portion does not depend on the rotational speed of the inner mass.