Title:
TRANSLATIONAL INERTER ASSEMBLY AND METHOD FOR DAMPING MOVEMENT OF A FLIGHT CONTROL SURFACE
Document Type and Number:
WIPO Patent Application WO/2019/139653
Kind Code:
A1
Abstract:
There is provided a translational inerter assembly (500) for damping movement (606) of a flight control surface (122) of an aircraft (100). The assembly (500) has a press fit element (510) fixedly disposed within a first end (502a) of the flight control surface (122) and rotatably movable with the flight control surface (122). The assembly (500) further has an inertia element (512) coupled to and installed in the press fit element (510). The assembly (500) further has a torsion bar (514) having a torsion bar first end (564a) coupled to and installed in the inertia element (512), and having a torsion bar second end (564b) fixedly attached to a support structure (116) of the aircraft (100). Rotation of the flight control surface (122) causes translational movement (604) of the inertia element (512), via the press fit element (510), along a hinge axis (126) of the flight control surface (122) and along the torsion bar (514), resulting in the translational inerter assembly (500) damping movement (606) of the flight control surface (122).
Inventors:
FOX MICHAEL THOMAS (US)
ROACH JEFFREY MICHAEL (US)
HOWELL ERIC ANTON (US)
ROACH JEFFREY MICHAEL (US)
HOWELL ERIC ANTON (US)
Application Number:
PCT/US2018/055344
Publication Date:
July 18, 2019
Filing Date:
October 11, 2018
Export Citation:
Assignee:
BOEING CO (US)
International Classes:
B64C9/02; F16F7/10; F16F7/116; F16F15/12; F16F15/121; F16F15/14; B64C13/38; B64C13/40
Domestic Patent References:
| WO2005070761A2 | 2005-08-04 |
Foreign References:
| DE102011120095A1 | 2013-06-06 | |||
| US20160024747A1 | 2016-01-28 | |||
| JP2017026074A | 2017-02-02 | |||
| EP3246593A1 | 2017-11-22 |
Other References:
None
Attorney, Agent or Firm:
KRASNOW, David M. (US)
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