Aircraft brake torque and clamp force reaction through landing gear structure

Patent metadata

Field	Value
Publication number	US-10145429-B1
Application number	US-201715699719-A
Country	US
Kind code	B1
Filing date	Sep 8, 2017
Priority date	Sep 8, 2017
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

An aircraft wheel braking arrangement may comprise a landing gear structure, a torque tube extending in an outboard direction from the landing gear structure, and an actuator housing disposed outboard from the torque tube. An actuator piston may extend in an inboard direction from the actuator housing for applying a force to a brake stack surrounding the torque tube. In various embodiments, a back plate is non-integral to the torque tube and may be disposed inboard of an end plate of the brake stack or the landing gear structure itself may act as the back plate. The back plate and/or the end plate may provide a direct thermal path from the brake stack to a landing gear structure.

First claim

What is claimed is:

1. An aircraft wheel braking arrangement, comprising:
a landing gear structure;
a torque tube extending in a first direction from the landing gear structure;
an actuator housing coupled to the torque tube, wherein the torque tube is disposed between the landing gear structure and the actuator housing; and
a brake stack disposed in the first direction from the landing gear structure and between the actuator housing and the landing gear structure.

2. The aircraft wheel braking arrangement of claim 1 , further comprising:
an axle disposed at least partially within the torque tube; and
a wheel disposed radially outward from the actuator housing.

3. The aircraft wheel braking arrangement of claim 2 , further comprising a bearing system disposed between the axle and the wheel.

4. The aircraft wheel braking arrangement of claim 1 , wherein the torque tube is in mechanical communication with the brake stack and is configured to transfer torque from the brake stack to the landing gear structure.

5. The aircraft wheel braking arrangement of claim 1 , wherein the torque tube is in thermal communication with the brake stack and is configured to transfer heat from the brake stack to the landing gear structure.

6. The aircraft wheel braking arrangement of claim 1 , wherein the brake stack is configured to transfer heat to the landing gear structure.

7. The aircraft wheel braking arrangement of claim 1 , wherein a first end of the torque tube engages the landing gear structure and a second end of the torque tube engages the actuator housing.

8. The aircraft wheel braking arrangement of claim 1 , wherein the landing gear structure comprises at least one of a landing gear bogie or a shock strut.

9. The aircraft wheel braking arrangement of claim 1 , further comprising:
an actuator extending in a second direction towards the brake stack from the actuator housing; and
a heat shield coupled to the actuator and disposed between the brake stack and the actuator housing.

10. The aircraft wheel braking arrangement of claim 1 , further comprising a back plate coupled between the landing gear structure and the brake stack.

11. An aircraft wheel braking arrangement, comprising:
a landing gear structure;
a brake stack disposed in a first direction from the landing gear structure;
an actuator housing disposed in the first direction from the brake stack; and
an actuator extending in a second direction from the actuator housing and configured to apply a force to the brake stack,
wherein the second direction is opposite from the first direction.

12. The aircraft wheel braking arrangement of claim 11 , further comprising a back plate coupled between the landing gear structure and the brake stack, wherein the back plate provides dampening of movement of the brake stack relative to the landing gear structure.

13. The aircraft wheel braking arrangement of claim 11 , further comprising a back plate coupled between the landing gear structure and the brake stack, wherein the back plate is floating between the brake stack and the landing gear structure.

14. The aircraft wheel braking arrangement of claim 11 , further comprising a back plate coupled between the landing gear structure and the brake stack, wherein the back plate provides a thermal path between the brake stack and the landing gear structure.

15. The aircraft wheel braking arrangement of claim 11 , further comprising a torque tube extending in the first direction from the landing gear structure and coupled to the brake stack.

16. The aircraft wheel braking arrangement of claim 15 , further comprising a back plate coupled between the landing gear structure and the brake stack, wherein the back plate is detached from the torque tube.

17. The aircraft wheel braking arrangement of claim 15 , further comprising:
an axle; and
a fastener coupled to the axle, wherein at least one of the torque tube and the actuator housing are compressed between the landing gear structure and the fastener.

18. The aircraft wheel braking arrangement of claim 11 , further comprising a heat shield coupled to the actuator and disposed between the brake stack and the actuator housing.

19. A method of assembling an aircraft wheel braking arrangement, comprising:
positioning a brake stack to surround a torque tube comprising a centerline axis, wherein the torque tube extends in a first axial direction from a landing gear structure; and
positioning an actuator housing relative to the brake stake such that the actuator housing is disposed in the first axial direction from the brake stack.

20. The method of claim 19 , further comprising positioning a back plate between the landing gear structure and an end plate of the brake stack.

Assignees

• Goodrich Corp

Inventors

• Whittle Scott

Classifications

• F16D65/0062 Primary

  integral with vehicle suspension, e.g. with the steering knuckle · CPC title

• F16D2055/0012

  integral with vehicle suspension · CPC title

• F16D55/36 Primary

  Brakes with a plurality of rotating discs all lying side by side · CPC title

• F16D65/78

  Features relating to cooling · CPC title

• F16D55/40

  actuated by a fluid-pressure device arranged in or one the brake · CPC title