Title:
MOTION CONTROLLED HELICOPTER AND ROTATION RATE SWITCHED FLUID LEAD LAG DAMPER
Document Type and Number:
WIPO Patent Application WO/2013/152300
Kind Code:
A3
Abstract:
A method for controlling helicopter ground resonance and air resonance motions as well as centrifugal force switching dampers are disclosed. A helicopter lead-lag damper (30) has a first ground resonance motion damping rate stage (FDR) and a second air resonance motion damping rate stage (SDR). The damper (30) includes a centrifugal force switch (52). The damper (30) is oriented relative to the rotary wing rotation axis (26) and helicopter blade (24). An in-flight rotation rate of the centrifugal force switching damper (30) actuates the centrifugal force switch (52) with the damper switching from the first ground resonance motion damping rate stage (FDR) to the second air resonance motion damping rate stage (SDR).
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Inventors:
FUHRER ZACHARY (US)
JOLLY MARK (US)
MARR CONOR (US)
JOLLY MARK (US)
MARR CONOR (US)
Application Number:
PCT/US2013/035468
Publication Date:
December 27, 2013
Filing Date:
April 05, 2013
Export Citation:
Assignee:
LORD CORP (US)
FUHRER ZACHARY (US)
JOLLY MARK (US)
MARR CONOR (US)
FUHRER ZACHARY (US)
JOLLY MARK (US)
MARR CONOR (US)
International Classes:
B64C27/51; F16F9/504
Domestic Patent References:
WO2012019117A2 | 2012-02-09 |
Foreign References:
US20100247288A1 | 2010-09-30 | |||
US2993691A | 1961-07-25 | |||
EP1972785A1 | 2008-09-24 |
Attorney, Agent or Firm:
MILLER, Richard G. (111 Lord DriveCary, North Carolina, US)
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