Method and device for lateral control of a taxiing aircraft
AssigneeAirbus Operations GmbH
InventorsMatthieu MAYOLLE, Caroline ACANFORA, Louis-Emmanuel ROMANA, Julien FONTAN
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Abstract
The device includes, but is not limited to a calculating unite for automatically applying, if conditions for turning of the aircraft are met, a symmetrical braking value at a brake assembly, then in the course of the turn automatically distributing this symmetrical braking value in differential braking between braking device of the left main landing gear and braking device of the right main landing gear of the aircraft, as a function of current directional command orders, in such a way as to maintain a constant overall braking level, at least for directional command orders below a predetermined threshold.
Claims19
A method of lateral control of an aircraft, said aircraft equipped with an orientable nose wheel provided with an orientation system, wherein, in event of a breakdown of the orientation system, said method implementing an emergency automatic asymmetrical braking, comprising:
- receiving command orders relating to a command of an orientation of said nose wheel;
- automatically determining braking orders for a brake assembly of the aircraft on a basis of said command orders, which comprises a first braking device for at least one left main landing gear and a second braking device for at least one right main landing gear and which is capable of generating a lateral movement of the aircraft about a vertical axis with an asymmetrical action,
- wherein said braking orders are determined to generate a lateral movement on the aircraft which is substantially identical to the lateral movement which would have been generated by an application of said command orders to said nose wheel when they are applied to the brake assembly;
- and
- automatically applying said braking orders to said brake assembly,
- wherein it also comprises sub-steps of the step b) consisting of:
- automatically determining braking orders for the brake assembly of the aircraft on the basis of said command orders comprises automatically verifying whether conditions for turning of the aircraft are met in the event of activation of the emergency automatic asymmetrical braking;
- and
- if the conditions for turning of the aircraft are met and as long as the conditions are met:
- automatically applying a symmetrical braking value at said brake assembly;
- and
- then in the course of the turn automatically distributing the symmetrical braking value in differential braking between the first braking device of the left main landing gear and the second braking device of the right main landing gear as a function of current directional command orders, in such a way as to maintain a constant overall braking level, at least for directional command orders below a predetermined threshold.
The device for lateral control of an aircraft, said aircraft equipped with an orientable nose wheel provided with an orientation system, wherein said device includes, at least in order to implement emergency automatic asymmetrical braking in the event of breakdown of the nose wheel orientation system:
- a receiving device that is configured to receive command orders relating to a command of the orientation of said nose wheel;
- a determining device that is configured to automatically determine, on a basis of said command orders, braking orders for a brake assembly of the aircraft, which comprises a first braking device for at least one left main landing gear and second braking device for at least one right main landing gear and which is capable of generating a lateral movement of the aircraft about a vertical axis with an asymmetrical action, said braking orders determined in such a way as to generate on the aircraft, when they are applied to the brake assembly, a lateral movement which is substantially identical to the lateral movement which would have been generated by an application of said command orders to said nose wheel;
- and
- a device that is configured to automatically apply said braking orders to said brake assembly,
- wherein said brake assembly further comprising:
- a verification device that is configured to automatically verify, in the event of activation of the emergency automatic asymmetrical braking, whether conditions for turning of the aircraft are met;
- and
- a second device that is configured to automatically apply, if the conditions for turning of the aircraft are met and so long as the conditions are met, a symmetrical braking value, at said brake assembly, then in the course of the turn automatically distributing this symmetrical braking value in differential braking between the first braking device of the left main landing gear and the second braking of the right main landing gear, as a function of current directional command orders, in such a way as to maintain a constant overall braking level, at least for directional command orders below a predetermined threshold.
(canceled)
Dependencies are inferred from the claim text.