A vibration control system 200 for a rotorcraft 100 includes at least one of an integrated actuator 208 and an intermediate actuator 210 associated with a first source of vibration, a sensor configured to sense vibration from the first source of vibration, a dedicated actuator 212 configured for association with a fuselage 106, and a controller 204 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 SUPRESSION
VEREINHEITLICHTE STEUERUNG VON MEHREREN AKTIVEN SYSTEMEN ZUR UNTERDRÜCKUNG VON HUBSCHRAUBERSCHWINGUNGEN
COMMANDE UNIFIÉE DE MULTIPLES SYSTÈMES ACTIFS DE SUPPRESSION DES VIBRATIONS D'UN HÉLICOPTÈRE
2021-06-16
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
UNIFIED CONTROL OF MULTIPLE ACTIVE SYSTEMS FOR HELICOPTER VIBRATION SUPPRESSION
European Patent Office | 2017
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