Patent ID: 6416016
Filing Date: 2002-07-09
Classification: B64C,F16F

Abstract:
An actuator for an active vibration and noise control system in an aircraft, the actuator for attaching to a vibrating component within the aircraft, the control system adapted to actuate the actuator to isolate vibratory load transmissions, the actuator comprising:a housing for mounting to the aircraft, the housing having a recess formed in it; a mounting member for attaching to the vibrating component; a lap-fit piston arrangement attached to the housing, the lap-fit piston arrangement including a piston slidably disposed within the housing; a bearing assembly engaged with the mounting member and the piston, the bearing assembly adapted to transmit axial motions between the mounting member and the piston, the bearing assembly also adapted to isolate moment and shear loads from the mounting member to the housing, and adapted to permit rotational movement of the inner bearing member relative to the piston.