UNIFIED CONTROL OF MULTIPLE ACTIVE SYSTEMS FOR HELICOPTER VIBRATION SUPRESSION

摘要

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.