DUAL RACK AND PINION ROTATIONAL INERTER SYSTEM AND METHOD FOR DAMPING MOVEMENT OF A FLIGHT CONTROL SURFACE OF AN AIRCRAFT

WIPO Patent Application WO/2019/139654

A1

There is provided a dual rack and pinion rotational inerter system (500) for damping movement (694) of a flight control surface (122) of an aircraft (100). The system (500) has a flexible holding structure (506) disposed between the flight control surface (122) and a support structure (116) of the aircraft (100). The system (500) has a dual rack and pinion assembly (550) held by and between the flexible holding structure (506). The dual rack and pinion assembly (550) has a first rack (552a), a second rack (552b), and a pinion (596) engaged to and between the racks (552a, 552b). The system (500) has a first terminal (502) coupled to the first rack (552a) and coupled to the flight control surface (122), via a pivot element (127), and a second terminal (503) coupled to the second rack (552b), and coupled to the support structure (116). The system (500) has a pair of inertia wheels (660) adjacent the flexible holding structure (506). The system (500) has an axle element (612) inserted through the inertial wheels (660), the flexible holding structure (506), and the pinion (596).

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FOX MICHAEL THOMAS (US)
ROACH JEFFREY MICHAEL (US)
HOWELL ERIC ANTON (US)

PCT/US2018/055361

July 18, 2019

October 11, 2018

Click for automatic bibliography generation  

BOEING CO (US)

B64C9/02; B64C13/34; B64C13/40; F16F7/10

WO2013105868A1	2013-07-18
WO2013104437A1	2013-07-18

US7882941B2	2011-02-08
EP3246593A1	2017-11-22
US20150217855A1	2015-08-06

None

KRASNOW, David M. (US)

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