Aircraft braking system architecture comprising: - a brake intended to brake a wheel of the aircraft and comprising friction members and a first electromechanical actuator (1; 101; 201) and a second electromechanical actuator (2; 102; 202) respectively comprising a first electric motor and a second electric motor and adapted to apply a braking force to the friction members; - a principal control channel (6; 106; 206) and an alternative control channel (7; 107; 207) comprising electrical components that are at least partly different and respectively adapted to produce a principal braking control function and an alternative braking control function that are at least partly different so that the principal control channel and the alternative control channel respectively generate principal control signals (Scp) and alternative control signals (Sca), the principal braking control function employing servocontrol of the braking force based on direct measurement of the braking force or based on monitoring a depression of pistons of the first electromechanical actuator and of the second electromechanical actuator and the alternative braking control function employing a simplified servocontrol function that is intended only to ensure that the braking force is bounded between a low level enabling minimum braking performance and a high level guaranteeing absence of locking up of the wheel; - a first power module (15; 115; 215) and a second power module (16; 116; 216) comprising electrical components that are at least partly different and adapted to generate on the basis of the principal control signals or the alternative control signals respectively at least one first electrical power supply current for supplying power to the first electric motor and at least one second electrical power supply current for supplying power to the second electric motor; - a surveillance unit (8; 108; 208) adapted to ensure that in normal operation the principal control signals are used to generate the first electrical power supply current and the second electrical power supply current and in the event of a fault impacting the principal control channel the alternative control signals are used to generate the first electrical power supply current and the second electrical power supply current. - a brake intended to brake a wheel of the aircraft and comprising friction members and a first electromechanical actuator (1; 101; 201) and a second electromechanical actuator (2; 102; 202) respectively comprising a first electric motor and a second electric motor and adapted to apply a braking force to the friction members; - a principal control channel (6; 106; 206) and an alternative control channel (7; 107; 207) comprising electrical components that are at least partly different and respectively adapted to produce a principal braking control function and an alternative braking control function that are at least partly different so that the principal control channel and the alternative control channel respectively generate principal control signals (Scp) and alternative control signals (Sca), the principal braking control function employing servocontrol of the braking force based on direct measurement of the braking force or based on monitoring a depression of pistons of the first electromechanical actuator and of the second electromechanical actuator and the alternative braking control function employing a simplified servocontrol function that is intended only to ensure that the braking force is bounded between a low level enabling minimum braking performance and a high level guaranteeing absence of locking up of the wheel; - a first power module (15; 115; 215) and a second power module (16; 116; 216) comprising electrical components that are at least partly different and adapted to generate on the basis of the principal control signals or the alternative control signals respectively at least one first electrical power supply current for supplying power to the first electric motor and at least one second electrical power supply current for supplying power to the second electric motor; - a surveillance unit (8; 108; 208) adapted to ensure that in normal operation the principal control signals are used to generate the first electrical power supply current and the second electrical power supply current and in the event of a fault impacting the principal control channel the alternative control signals are used to generate the first electrical power supply current and the second electrical power supply current.