Active vibration control system for helicopter with improved actustor placement
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Oct 22, 2002
Grant Date -
N/A
app pub date -
Oct 10, 2000
filing date -
Oct 10, 2000
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
An aircraft has a fuselage that defines an interior cabin and an exterior; a first housing located along one side of the fuselage exterior; a second housing located along the second side of the fuselage exterior; and an active vibration control system for limiting fuselage vibration, the vibration control system comprising a plurality of sensors located in the cabin; a controller in signal receiving relation with the sensor means; first actuator means located in the first housing and second actuator means located in the second housing and wherein the actuator means are in signal receiving relation with the controller.
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