AIRCRAFT LANDING GEAR

• US 20140084108A1
• Filed: 03/22/2012
• Published: 03/27/2014
• Est. Priority Date: 04/13/2011
• Status: Abandoned Application

• Current Assignee: Messier-Dowty Limited (Safran SA)
• Original Assignee: Messier-Dowty Limited (Safran SA)
• Inventors: Goodburn, Simon
• Application Number:
  US14/111,405
• Publication Number:
  US 20140084108A1
• Time in Patent Office: Days
• US Class Current: 244/100.R
• CPC Class Codes: B64C 25/02 Undercarriages
• CPC Class Codes: B64C 25/34 wheeled type, e.g. multi-wheeled bogies
• CPC Class Codes: B64C 25/42 Arrangement or adaptation of brakes

Abstract

Aircraft landing gear including: a bogie beam coupled to a main strut; a first and second axles mounted on the bogie beam, each axle having a respective brake assembly and wheel assembly; and first and second stabilising arms mechanically coupling the first and second brake assemblies to respective first and second anchor points on the landing gear so as to react respective first and second brake torques generated as respective brake assembly applies a braking force to the respective wheel assembly. The first and second stabilising arms couple the respective first and second brake assemblies to the respective first and second anchor points such that the first and second brake torques result in both stabilising arms experiencing a tensile force or both stabilising arms experiencing a compressive force.

Claims

1. An aircraft landing gear including:

a bogie beam coupled to a main strut;

a first axle mounted on the bogie beam, the first axle carrying a first brake assembly and a first wheel assembly;

a second axle mounted on the bogie beam, the second axle carrying a second brake assembly and a second wheel assembly, the first and second axles being adjacent so as to form an axle pair;

a first stabilising arm arranged to mechanically couple the first brake assembly to a first anchor point on the landing gear so as to react a first brake torque generated as the first brake assembly applies a braking force to the first wheel assembly; and

a second stabilising arm arranged to mechanically couple the second brake assembly to a second anchor point on the landing gear so as to react a second brake torque generated as the second brake assembly applies a braking force to the second wheel assembly,

wherein the first and second stabilising arms couple the respective first and second brake assemblies to the respective first and second anchor points such that the first and second brake torques result in both stabilising arms experiencing a tensile force.

2. An aircraft landing gear according to claim 1, including a third axle mounted on the bogie beam, the third axle carrying a third brake assembly and a third wheel assembly, and a third stabilising arm arranged to mechanically couple the third brake assembly to a third anchor point on the landing gear so as to react a third brake torque generated as the third brake assembly transmits a braking force to the third wheel assembly, wherein the third stabling arm couples the third brake assembly to the third anchor point such that the third brake torque results in the third stabilising arm experiencing a tensile force.

3. An aircraft landing gear according to claim 2, wherein the third anchor point is provided on the second brake assembly and optionally is provided in the same region as a connection point between the second stabilising arm and the second brake assembly and optionally is provided coaxially with respect to connection point between the second stabilising arm and the second brake assembly and optionally is coupled to the second stabilising arm via a common connection point.

4. An aircraft landing gear according to claims 3, including a fourth axle mounted on the bogie beam, the fourth axle carrying a fourth brake assembly and a fourth wheel assembly and a fourth stabilising arm arranged to mechanically couple the fourth brake assembly to a fourth anchor point on the landing gear so as to react a fourth brake torque generated as the fourth brake assembly transmits a braking force to the fourth wheel assembly, wherein the fourth stabling arm couples the fourth brake assembly to the fourth anchor point such that the fourth brake torque results in the fourth stabilising arm experiencing a tensile force.

5. An aircraft landing gear according to claim 1, wherein one or more of the stabilising arms are attached to their respective brake assembly at a respective brake assembly connection point and wherein a respective plane is defined intersecting the respective anchor point and the axis of rotation of the wheel assembly, the brake assembly connection point being on the side of the plane in which the direction of rotation of the wheel assembly is away from the anchor point during forward motion of the aircraft during taxiing.

6. An aircraft landing gear according to claim 5, wherein a portion of the circumference of the respective wheel assembly on the side of the respective plane in which the direction of rotation of the respective wheel assembly is away from the respective anchor point during forward motion of the aircraft during taxiing defines an arc and wherein the respective anchor point is within a portion of the arc between ¼

π

radians and ¾

π

radians from the start of the arc.

7. An aircraft landing gear according to claim 5, wherein one or more of the anchor points are located on a direct path between the brake assembly connection points of the respective axle pair.

8. An aircraft landing gear according to claim 1, wherein two of the anchor points are coaxial.

9. An aircraft landing gear according to claim 8, wherein the two coaxial anchor points belong to the stabilising arms of a wheel pair.

10. An aircraft landing gear according to claim 1, wherein two of the stabilising arms are coupled to one another via a common anchor point.

11. An aircraft landing gear according to claim 1, wherein two of the stabilising arms are defined by a single member.

12. An aircraft landing gear according to claim 1, wherein the bogie beam is pivotally connected to the strut at a bogie pivot and the first and second anchor points are coaxial with, and optionally defined by, the bogie pivot.

14. An aircraft landing gear according to claim 12, wherein one wheel assembly has an axis of rotation that is generally coaxial with the bogie pivot axis.

15. An aircraft landing gear including:

a bogie beam coupled to a main strut of an aircraft;

a first axle mounted on the bogie beam, the first axle carrying first brake means and a first wheel assembly;

a second axle mounted on the bogie beam, the second axle carrying second brake means and a second wheel assembly, the first and second axles being adjacent so as to form an axle pair;

first stabilising means arranged to mechanically couple the first brake means to a first anchor point on the landing gear so as to react a first brake torque generated as the first brake means applies a braking force to the first wheel assembly; and

second stabilising means arranged to mechanically couple the second brake means to a second anchor point on the landing gear so as to react a second brake torque generated as the second brake means applies a braking force to the second wheel assembly,

wherein the first and second stabling means couple the respective first and second brake means to the respective first and second anchor points such that the first and second brake torques result in both stabilising means experiencing a tensile force.

16. (canceled)

17. (canceled)