Patent ID: 11858621
Assignee: LOCKHEED MARTIN CORPORATION
Field: Transport (Mechanical engineering)
Classification: CPC B  F | IPC B  F

Claim 15:
16. A control assembly configured to reduce vibration at selected frequencies of an aircraft, the control assembly comprising:
a sensor configured to be coupled to an airframe of the aircraft, the sensor configured to measure vibrations of the airframe during flight; and
a control processor in communication with the sensor, the control processor configured to
receive a signal from the sensor representing measured vibrations of the airframe during flight,
determine a desired movement of at least one of a plurality of rotor blades of the aircraft based on the signal from the sensor, and
control an electric motor of a harmonic control actuator coupled to a swashplate assembly of the aircraft to provide the desired movement of the at least one of the plurality of rotor blades to reduce the measured vibrations in the airframe.