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Active vibration control system for helicopter with improved actustor placement

  • US 6,467,723 B1
  • Filed: 10/10/2000
  • Issued: 10/22/2002
  • Est. Priority Date: 10/10/2000
  • Status: Expired due to Fees
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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