High-speed-deployed, drum-brake, inertia disk for rack and pinion rotational inerter

Patent metadata

Field	Value
Publication number	US-10723441-B2
Application number	US-201815952407-A
Country	US
Kind code	B2
Filing date	Apr 13, 2018
Priority date	Apr 13, 2018
Publication date	Jul 28, 2020
Grant date	Jul 28, 2020

Abstract

A dual rack and pinion rotational inerter, configured to dampen the flutter of a flight control member of an aircraft, includes an inertial wheel and a brake member disposed on an inertial wheel. The brake member moves between a retracted position and a deployed position based on a rotational velocity of the inertial wheel. The brake member moves to the retracted position when the rotational velocity of the inertial wheel is slower than a predetermined threshold velocity to allow the rotation of the inertial wheel. When the rotational velocity of the inertial wheel is at least as fast as the predetermined threshold velocity, however, the brake member deploys to yieldingly resist the rotation of the inertial wheel. In either position, the inertial wheel causes the inerter to dampen the flutter.

First claim

What is claimed is:

1. An inertial wheel assembly for a dual rack and pinion rotational inerter configured to control movement of a flight control member on an aircraft, the inertial wheel assembly comprising:
a housing; and
an inertial wheel disposed within the housing and operatively connected to an axle of the dual rack and pinion rotational inerter, wherein the inertial wheel is configured to dampen flutter of the flight control member and comprises:
a trigger member configured to pivot between a first position and a second position based on a rotational velocity of the inertial wheel; and
a brake member operatively coupled to the trigger member and configured to move between a retracted position in which the brake member is spaced away from the housing when the trigger member is in the first position, and a deployed position in which the brake member contacts the housing when the trigger member is in the second position.

2. The inertial wheel assembly of claim 1 wherein the trigger member is configured to:
pivot to, and persist in, the first position when the rotational velocity of the inertial wheel is slower than a predetermined velocity threshold; and
pivot to, and persist in, the second position when the rotational velocity of the inertial wheel is at least as fast as the predetermined velocity threshold.

3. The inertial wheel assembly of claim 2 wherein the inertial wheel further comprises a biasing member operatively coupling the brake member to the trigger member and configured to:
bias the brake member into the retracted position when the trigger member pivots to the first position; and
bias the brake member into the deployed position when the trigger member pivots to the second position.

4. The inertial wheel assembly of claim 3 wherein the inertial wheel further comprises a stop member configured to:
engage the brake member when the trigger member is in the first position and the brake member is in the retracted position; and
engage the biasing member when the trigger member is in the second position and the brake member is in the deployed position.

5. The inertial wheel assembly of claim 1 wherein the inertial wheel further comprises a balancing mass configured to balance rotation of the inertial wheel about a center of gravity of the inertial wheel.

6. The inertial wheel assembly of claim 1 further comprising a brake lining disposed on an interior surface of the housing, and wherein the brake member is spaced away from the brake lining when the brake member is in the retracted position, and contacts the brake lining when the brake member is in the deployed position.

7. The inertial wheel assembly of claim 1 wherein the brake member yieldingly resists rotation of the axle when the brake member is in the deployed position.

8. The inertial wheel assembly of claim 1 wherein the trigger member moves the brake member to the deployed position responsive to a flight control actuator disconnecting from the flight control member with the dual rack and pinion rotational inerter remaining connected to the flight control member.

9. The inertial wheel assembly of claim 1 wherein the inertial wheel assembly comprises first and second inertial wheel assemblies with the first inertial wheel assembly being disposed adjacent a first side of the dual rack and pinion rotational inerter, and the second inertial wheel assembly being disposed adjacent a second side of the dual rack and pinion rotational inerter opposite the first side.

10. An aircraft comprising:
a dual rack and pinion rotational inerter coupled between a support structure of the aircraft and a flight control member comprising a flight control surface; and
an inertial wheel assembly operatively coupled to a side of the rack and pinion rotational inerter and comprising:
an inertial wheel disposed within a housing and operatively connected to an axle of the dual rack and pinion rotational inerter, wherein the inertial wheel is configured to dampen flutter of the flight control member;
a trigger member disposed on the inertial wheel and configured to pivot between a first position and a second position based on a rotational velocity of the inertial wheel; and
a brake member operatively coupled to the trigger member and configured to move between a retracted position away from the housing when the trigger member is in the first position, and a deployed position contacting the housing when the trigger member is in the second position.

11. The aircraft of claim 10 wherein the trigger member is configured to:
pivot to, and persist in, the first position when the rotational velocity of the inertial wheel is slower than a predetermined velocity threshold; and
pivot to, and persist in, the second position when the rotational velocity of the inertial wheel is at least as fast as the predetermined velocity threshold.

12. The aircraft of claim 11 wherein the inertial wheel assembly further comprises a biasing member operatively coupling the brake member to the trigger member and configured to:
bias the brake member into the retracted position when the trigger member pivots to the first position; and
bias the brake member into the deployed position when the trigger member pivots to the second position.

13. The aircraft of claim 10 further comprising a brake lining disposed on an interior surface of the housing, and wherein the brake member is spaced away from the brake lining in the retracted position, and contacts the brake lining in the deployed position.

14. The inertial wheel assembly of claim 10 wherein the brake member yieldingly resists rotation of the inertial wheel when the brake member is in the deployed position.

15. A method of controlling movement of a flight control member on an aircraft comprising a dual rack and pinion rotational inerter and an inertial wheel assembly, the inertial wheel assembly comprising an inertial wheel disposed within a housing, a brake member disposed on the inertial wheel, and a trigger member disposed on the inertial wheel and operatively connected to the brake member, the method comprising:
responsive to a rotational velocity of the inertial wheel being slower than a predetermined velocity threshold, retracting the brake member away from the housing to allow the inertial wheel to rotate; and
responsive to the rotational velocity of the inertial wheel being at least as fast as the predetermined velocity threshold, deploying the brake member into contact with the housing to yieldingly resist rotation of the inertial wheel.

16. The method of claim 15 further comprising:
pivoting the trigger member to, and persisting the trigger member in, a first position when the rotational velocity of the inertial wheel is slower than the predetermined velocity threshold; and
pivoting the trigger member to, and persisting the trigger member in, a second position when the rotational velocity of the inertial wheel is at least as fast as the predetermined velocity threshold.

17. The method of claim 16 wherein retracting the brake member away from the housing comprises biasing the brake member into a retracted position when the trigger member is pivoted to the first position.

18. The method of claim 16 wherein deploying the brake member into contact with the housing comprises biasing the brake member into a deployed position when the trigger member is pivoted to the second position.

19. The method of claim 16 :
wherein retracting the brake member away from the housing comprises retracting the brake member away from a brake lini

Assignees

• Boeing Co

Inventors

• Fox Michael Thomas
• Howell Eric Anton
• Roach Jeffrey M

Classifications

• Y02T50/40

  Weight reduction · CPC title

• F16F7/1005 Primary

  characterised by active control of the mass · CPC title

• F16F7/1022

  the linear oscillation movement being converted into a rotational movement of the inertia member, e.g. using a pivoted mass · CPC title

• B64C13/28

  mechanical · CPC title

• F16D2129/046

  Flywheels · CPC title