Patent · US Active

Translational inerter assembly and method for damping movement of a flight control surface

US10808789B2 · kind B2 · utility

0Cited by

74References

20Claims

0Family size

Assignee

The Boeing Company · US

Inventors

Michael T. Fox · Holden, US
Jeffrey M. Roach · Saint Charles, US
Eric Anton Howell · Ballwin, US

Key dates

Filing date	Oct 13, 2018
Grant date	Oct 20, 2020
Priority date	—
Expiry date	Feb 15, 2039

Classification

Technology area (CPC Y)Emerging Cross-Sectional Technologies
CPC primaryY02T50/40
WIPO fieldMechanical elements
WIPO sectorMechanical engineering

Abstract

There is provided a translational inerter assembly for damping movement of a flight control surface of an aircraft with a support structure. The translational inerter assembly includes a press fit element rotatably disposed within the flight control surface. The translational inerter assembly further includes an inertia element disposed in the press fit element. The translational inerter assembly further includes a torsion bar coupled to the inertia element and to the support structure of the aircraft, such that when the flight control surface rotates, the inertia element translates, and movement of the flight control surface is dampened.

Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.