A vibration control system for a rotorcraft includes at least one of an integrated actuator and an intermediate actuator associated with a first source of vibration, a sensor configured to sense vibration from the first source of vibration, a dedicated actuator configured for association with a fuselage, and a controller configured to receive information from the sensor and configured to control the dedicated actuator and the at least one of the integrated actuator and the intermediate actuator.
UNIFIED CONTROL OF MULTIPLE ACTIVE SYSTEMS FOR HELICOPTER VIBRATION SUPPRESSION
2017-03-30
Patent
Elektronische Ressource
Englisch
UNIFIED CONTROL OF MULTIPLE ACTIVE SYSTEMS FOR HELICOPTER VIBRATION SUPRESSION
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