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

Patent metadata

Field	Value
Publication number	US-10145434-B2
Application number	US-201815867940-A
Country	US
Kind code	B2
Filing date	Jan 11, 2018
Priority date	May 19, 2016
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

There is provided a translational inerter assembly for damping movement of a flight control surface of an aircraft. The assembly has a press fit element fixedly disposed within a first end of the flight control surface and rotatably movable with the flight control surface. The assembly further has an inertia element coupled to and installed in the press fit element. The assembly further has a torsion bar having a torsion bar first end coupled to and installed in the inertia element, and having a torsion bar second end fixedly attached to a support structure of the aircraft. Rotation of the flight control surface causes translational movement of the inertia element, via the press fit element, along a hinge axis of the flight control surface and along the torsion bar, resulting in the translational inerter assembly damping movement of the flight control surface.

First claim

What is claimed is:

1. A translational inerter assembly for damping movement of a flight control surface of an aircraft, the translational inerter assembly comprising:
a press fit element fixedly disposed within a first end of the flight control surface and rotatably movable with the flight control surface;
an inertia element coupled to and installed in the press fit element, the inertia element having a plurality of exterior helical splines corresponding to a plurality of interior helical splines of the press fit element; and
a torsion bar having a torsion bar first end coupled to and installed in the inertia element, and having a torsion bar second end fixedly attached to a support structure of the aircraft, the torsion bar further having a plurality of exterior linear splines corresponding to a plurality of interior linear splines of the inertia element,
wherein rotation of the flight control surface causes translational movement of the inertia element, via the press fit element, along a hinge axis of the flight control surface and along the torsion bar, resulting in the translational inerter assembly damping movement of the flight control surface.

2. The translational inerter assembly of claim 1 further comprising a splined attachment element coupled to the torsion bar, the splined attachment element having a plurality of interior linear splines corresponding to the plurality of exterior linear splines of the torsion bar.

3. The translational inerter assembly of claim 2 wherein the torsion bar second end is fixedly attached to the support structure of the aircraft, via a first torsion bar bearing attached to the splined attachment element.

4. The translational inerter assembly of claim 3 wherein the first torsion bar bearing constrains the torsion bar in six (6) degrees of freedom.

5. The translational inerter assembly of claim 1 further comprising a first bearing attaching the first end of the flight control surface to the support structure, and a second bearing attaching a second end of the flight control surface to the support structure, wherein the first bearing and the second bearing constrain the flight control surface in five (5) degrees of freedom and allow rotation about the hinge axis.

6. The translational inerter assembly of claim 1 wherein the press fit element comprises an outer face having a plurality of fastener holes configured to attach, via a plurality of fasteners, a horn element and a bearing for surface position control using one or more actuators.

7. The translational inerter assembly of claim 1 wherein the inertia element comprises an inertia element body comprising a helical spline portion integral with a shaft portion.

8. The translational inerter assembly of claim 1 wherein the plurality of exterior helical splines of the inertia element comprise one of, right hand direction helical splines, or left hand direction helical splines.

9. The translational inerter assembly of claim 1 wherein the flight control surface comprises an aileron, and the support structure comprises a wing, a wing portion support structure, or a wing spar.

10. An aircraft, comprising:
a flight control surface pivotably coupled to a support structure;
one or more actuators configured to actuate 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 attached to a first end of the flight control surface and comprising:
a press fit element fixedly disposed within the first end of the flight control surface and rotatably movable with the flight control surface;
an inertia element coupled to and installed in the press fit element, the inertia element having a plurality of exterior helical splines corresponding to a plurality of interior helical splines of the press fit element; and
a torsion bar having a torsion bar first end coupled to and installed in the inertia element, and having a torsion bar second end fixedly attached to the support structure of the aircraft, the torsion bar further having a plurality of exterior linear splines corresponding to a plurality of interior linear splines of the inertia element,

wherein rotation of the flight control surface causes translational movement of the inertia element, via the press fit element, along a hinge axis of the flight control surface and along the torsion bar, resulting in the at least one translational inerter assembly damping movement of the flight control surface.

11. The aircraft of claim 10 wherein the aircraft comprises two translational inerter assemblies comprising a first translational inerter assembly attached to the first end of the flight control surface, and comprising a second translational inerter assembly attached to a second end of the flight control surface.

12. The aircraft of claim 11 wherein the first translational inerter assembly has a first inertia element with the plurality of exterior helical splines comprising right hand direction helical splines, and wherein the second translational inerter assembly has a second inertia element with the plurality of exterior helical splines comprising left hand direction helical splines.

13. The aircraft of claim 10 wherein the at least one translational inerter assembly further comprises a splined attachment element coupled to the torsion bar, and further wherein the torsion bar second end is fixedly attached to the support structure of the aircraft, via a first torsion bar bearing attached to the splined attachment element, the first torsion bar bearing constraining the torsion bar in six (6) degrees of freedom.

14. The aircraft of claim 10 wherein the translational inerter assembly further comprises a first bearing attaching the first end of the flight control surface to the support structure, and a second bearing attaching a second end of the flight control surface to the support structure, and further wherein the first bearing and the second bearing constrain the flight control surface in five (5) degrees of freedom and allow rotation about the hinge axis.

15. A method for damping movement of a flight control surface of an aircraft, the method comprising the steps of:
installing at least one translational inerter assembly at a first end of the flight control surface, the at least one translational inerter assembly comprising:
a press fit element fixedly disposed within the first end of the flight control surface and rotatably movable with the flight control surface;
an inertia element coupled to and installed in the press fit element, the inertia element having a plurality of exterior helical splines corresponding to a plurality of interior helical splines of the press fit element; and
a torsion bar having a torsion bar first end coupled to and installed in the inertia element, and having a torsion bar second end fixedly attached to a support structure of the aircraft, the torsion bar further having a plurality of exterior linear splines corresponding to a plurality of interior linear splines of the inertia element;

rotating the flight control surface using one or more actuators;
using the at least one translational inerter assembly to axially accelerate in a translational movement along a hinge axis of the flight control surface, the inertia element relative to the torsion bar, simultaneous with, and in proportion to, rotation of the flight control surface; and
damping movement of the flight control surface, using the at least one translational inerter assembly.

16. The method of claim 15 further comprising, after installing and prior to rot

Assignees

• Boeing Co

Inventors

• Fox Michael T
• Roach Jeffrey M
• Howell Eric A

Classifications

• F16F7/065 Primary

  where elements interengaging frictionally are in the shape of spiral bands · CPC title

• F16F15/1216

  Torsional springs, e.g. torsion bar or torsionally-loaded coil springs · CPC title

• F16F15/1208

  Bearing arrangements · CPC title

• F16F15/1204

  with a kinematic mechanism or gear system (F16F15/1202, F16F15/13157 take precedence) · CPC title

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title