Active vibration control system for helicopter with improved actustor placement
First Claim
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1. An aircraft comprising:
- g) a fuselage that defines interior cockpit and cabin sections and an exterior;
h) at least one housing along the exterior of the fuselage; and
i) an active vibration control system for limiting fuselage vibration, the system comprising;
(i) sensor means for sensing the vibration;
(ii) controller means in signal receiving relation with the sensor means; and
(iii) actuator means located in the at least one housing, said actuator means being in signal receiving relation with controller means, said actuator being actuated by signals received by said actuator means from said controller as required to cancel a vibratory disturbance having a magnitude within a predetermined range of frequencies and occurring at one of a plurality of predetermined locations in the aircraft fuselage.
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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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Citations
16 Claims
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1. An aircraft comprising:
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g) a fuselage that defines interior cockpit and cabin sections and an exterior;
h) at least one housing along the exterior of the fuselage; and
i) an active vibration control system for limiting fuselage vibration, the system comprising;
(i) sensor means for sensing the vibration;
(ii) controller means in signal receiving relation with the sensor means; and
(iii) actuator means located in the at least one housing, said actuator means being in signal receiving relation with controller means, said actuator being actuated by signals received by said actuator means from said controller as required to cancel a vibratory disturbance having a magnitude within a predetermined range of frequencies and occurring at one of a plurality of predetermined locations in the aircraft fuselage. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16)
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Specification