Translational inerter assembly and method for damping movement of a flight control surface
AssigneeThe Boeing Company
InventorsMichael T. Fox, Jeffrey M. Roach, Eric A. Howell
Life of this patent
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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.
Claims20
A translational inerter assembly for damping movement of a flight control surface of an aircraft with a support structure, the translational inerter assembly comprising:
- a press fit element rotatably disposed within the flight control surface;
- an inertia element disposed in the press fit element;
- and
- 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.
An aircraft, comprising:
- a flight control surface pivotably coupled to a support structure;
- one or more actuators actuating the flight control surface;
- and
- at least one translational inerter assembly for damping movement of the flight control surface, the at least one translational inerter assembly comprising:
- a press fit element rotatably disposed within the flight control surface;
- an inertia element disposed in the press fit element;
- and
- a torsion bar coupled to the inertia element and to the support structure, such that when the flight control surface rotates, the inertia element translates, and movement of the flight control surface is dampened.
A method for damping movement of a flight control surface of an aircraft having a support structure, the method comprising the steps of:
- attaching at least one translational inerter assembly to the flight control surface, the at least one translational inerter assembly comprising:
- a press fit element rotatably disposed within the flight control surface;
- an inertia element disposed in the press fit element;
- and
- a torsion bar coupled to the inertia element and to the support structure of the aircraft;
- rotating the flight control surface using one or more actuators, to cause the inertia element, via the press fit element, to translate along a hinge axis of the flight control surface, and to translate along the torsion bar;
- and
- damping movement of the flight control surface, using the at least one translational inerter assembly.
Dependencies are inferred from the claim text.