Patent ID: 9604719
Date: 2017-03-28
CPC Classifications: B60T,B64C

Claim:
1. 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 directional 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 directional command orders, wherein the brake assembly 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 directional 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 the method also comprises: automatically determining braking orders for the brake assembly of the aircraft on the basis of said directional command orders comprises automatically verifying whether conditions for turning the aircraft are met in the event of activation of the emergency automatic asymmetrical braking; and if the conditions for turning the aircraft are met and for as long as the conditions are met: wherein the symmetrical braking value is generated in the form of a symmetrical pressure (Ps); wherein said symmetrical pressure (Ps) is combined with a commanded pressure (Pc), which is representative of said directional command orders, in order to form a high pressure (Ph) and a low pressure (Pb), of which one of the Ph or Pb is applied to the first braking device of the left landing gear and of which the other is applied to the second braking device of the right landing gear, as a function of the direction relative to said directional command orders; and wherein Ps and Pc are combined such that, if Pc is greater or equal to twice Ps, then Ph is set equal to Pc and Pb is set equal to zero; and if Pc is less than twice Ps, then Ph is set equal to the sum of Ps and half of Pc and Pb is set equal to the difference between Ps and half of Pc.