Aircraft Braking System

• US 20080283660A1
• Filed: 11/10/2006
• Published: 11/20/2008
• Est. Priority Date: 11/11/2005
• Status: Active Grant

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus UK Limited (Airbus SE)
• Inventors: Thompson, Robert Ian
• Granted Patent: US 8,376,273 B2
• Time in Patent Office: Days
• US Class Current: 244/75.1
• CPC Class Codes: B60T 8/00 Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force by changing number of effective brake cylinders in power brake systems B60T17/10
• CPC Class Codes: B64C 25/48 differentially operated for steering purposes

Abstract

A method of braked pivot turning an aircraft, the aircraft comprising a fuselage and a landing gear assembly located to one side thereof. The landing gear comprises a bogie with wheels mounted thereon, at least one wheel being located on a first side of the bogie and at least one wheel being located on a second side of the bogie. The method includes the steps of applying thrust (7″) for moving or turning the aircraft, and via the braking of at least one wheel, applying a greater braking force to the first side of the bogie than to the second side. The first side is located closer to the centre of turning of the aircraft than the second side. The method thereby generates relatively low torque loads in the landing gear leg, reducing fatigue damage. A brake control system is also provided for selectively braking wheels during a turn.

Claims

1. A method of braked pivot turning an aircraft on the ground, the aircraft comprising a fuselage and a landing gear assembly located to one side thereof, the landing gear assembly comprising a bogie with a plurality of wheels mounted thereon, at least one wheel being located on a first side of the bogie and at least one wheel being located on a second side of the bogie,

the method including the steps of:

(i) applying thrust suitable for moving the aircraft, and

(ii) via the braking of at least one wheel, applying a greater braking force to the first side of the bogie than to the second side, the first side being located closer to the centre of turning of the aircraft than the second side.

2. A method according to claim 1 wherein the thrust is a differential thrust suitable for turning the aircraft.

3. A method according to claim 1 wherein at least one more wheel is braked on the first side of the bogie than on the second side.

4. A method according to claim 1 wherein the aircraft is travelling at less than 20 knots.

5. A method according to claim 1, the aircraft further comprising a nose wheel, wherein the method further includes the step of turning the nose wheel at an angle of greater than 45 degrees to the centre-line of the aircraft fuselage.

6. A method according to claim 1 further comprising the steps of:

(i) receiving a first signal relating to an aircraft parameter, and

(ii) applying the braking force in dependence on the signal.

7. A method according to claim 6 further comprising the steps of:

(i) comparing the value of the aircraft parameter to an aircraft parameter reference threshold, and

(ii) applying the braking force if the value of the parameter is outside the reference threshold.

8. A method according to claim 1, wherein the aircraft is heavier than 50 tonnes dry weight.

12. An aircraft for use in the method of claim 1 wherein the aircraft is so arranged that a greater braking force can be applied to the first side of the bogie of the landing gear assembly than to the second side.

9. A brake control system for selectively braking wheels on a landing gear assembly during an aircraft braked pivot turn, the aircraft comprising a fuselage and the landing gear assembly being located to one side thereof, the landing gear assembly comprising a bogie with a plurality of wheels mounted thereon, at least one wheel being located on a first side of the bogie and at least one wheel being located on a second side of the bogie, wherein the brake control system is arranged to effect, via the braking of at least one wheel, a greater braking force on the first side of a bogie than on the second side, the first side being located closer to the centre of turning of the aircraft than the second side.

10. A brake control system according to claim 9 further comprising a brake input receiver for receiving a signal relating to the application of brakes to the wheels of the aircraft landing gear, wherein the brake control system is arranged to effect the braking force in dependence on the signal received by the brake input receiver.

11. A brake control system according to claim 9, further comprising a first receiver for receiving a signal relating to an aircraft parameter, and a database for storing an aircraft parameter reference threshold,

wherein, the brake control system is arranged to compare the value of the aircraft parameter to the aircraft parameter reference threshold, and the brake control system is arranged to effect the braking of at least one wheel in dependence on the comparison of the aircraft parameter to the aircraft parameter reference threshold.

13. An aircraft wherein the aircraft is so arranged that a greater braking force can be applied to the first side of the bogie of the landing gear assembly than to the second side, wherein the aircraft comprises a brake control system according to claim 9.

14. A method of braked pivot turning an aircraft on the ground, the aircraft comprising a fuselage, two landing gear assemblies, the landing gear assemblies being located either side of the fuselage and each comprising a bogie with a plurality of wheels mounted thereon, at least one wheel being located on an inner side of the bogie and at least one wheel being located on an outer side of the bogie,

the method including the steps of:

(i) applying thrust suitable for moving the aircraft, and

(ii) braking at least one wheel on the landing gear assembly that is located the closer to the centre of turning of the aircraft,

wherein,

via the braking of at least one wheel, a greater braking force is applied to the outer side of the bogie of said landing gear assembly than to the inner side.