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Rotorcraft autopilot system, components and methods

  • US 9,586,681 B2
  • Filed: 09/18/2015
  • Issued: 03/07/2017
  • Est. Priority Date: 02/10/2012
  • Status: Active Grant
First Claim
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1. In an autopilot system that is configured for automated control of a helicopter by actuating a cyclic control of the helicopter which cyclic control is subject to a cyclic vibration frequency responsive to rotation of a rotor of the helicopter, an apparatus comprising:

  • a cyclic vibration isolator that is removably supported by said actuator shaft for co-rotation therewith and coupled to the cyclic control of the helicopter to exhibit a resonant frequency that is at least approximately matched to the cyclic vibration frequency for movement of the cyclic control relative to the actuator shaft such that the cyclic vibration frequency is attenuated at the actuator shaft and output rotations of the actuator shaft below the resonant frequency are coupled to the cyclic control.

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