An aircraft brake system comprising: - a first group of at least one electromechanical actuator able to apply a braking force to slow at least one wheel of the aircraft, - a second group of at least one electromechanical actuator able to apply a braking force to slow said at least one wheel of the aircraft, - a first control device configured to control the first group of at least one actuator by means of a first software module and a second software module , the second software module being configured to control the first group of at least one actuator at least in the event of a fault of the first software module, - a second control device configured to control the second group of at least one actuator by means of a third software module and a fourth software module , the fourth software module being configured to control the second group of at least one actuator at least in the event of a fault of the third software module, wherein the first control device and the second control device are dissimilar and have at least one structural difference, characterized in that the second software module differs from the first software module in that : - it includes a smaller number of inputs, and/or - it includes a smaller number of outputs, and/or - it includes a smaller number of functionalities, and/or wherein the fourth software module differs from the third software module in that : - it includes a smaller number of inputs, and/or - it includes a smaller number of outputs, and/or - it includes a smaller number of functionalities, and wherein the first software module and the second software module can further be executed in an isolated manner relative to one another, and/or wherein the third software module and the fourth software module can further be executed in an isolated manner relative to one another. - a first group of at least one electromechanical actuator able to apply a braking force to slow at least one wheel of the aircraft, - a second group of at least one electromechanical actuator able to apply a braking force to slow said at least one wheel of the aircraft, - a first control device configured to control the first group of at least one actuator by means of a first software module and a second software module , the second software module being configured to control the first group of at least one actuator at least in the event of a fault of the first software module, - a second control device configured to control the second group of at least one actuator by means of a third software module and a fourth software module , the fourth software module being configured to control the second group of at least one actuator at least in the event of a fault of the third software module, wherein the first control device and the second control device are dissimilar and have at least one structural difference, characterized in that the second software module differs from the first software module in that : - it includes a smaller number of inputs, and/or - it includes a smaller number of outputs, and/or - it includes a smaller number of functionalities, - it includes a smaller number of inputs, and/or - it includes a smaller number of outputs, and/or - it includes a smaller number of functionalities, and/or wherein the fourth software module differs from the third software module in that : - it includes a smaller number of inputs, and/or - it includes a smaller number of outputs, and/or - it includes a smaller number of functionalities, - it includes a smaller number of inputs, and/or - it includes a smaller number of outputs, and/or - it includes a smaller number of functionalities, and wherein the first software module and the second software module can further be executed in an isolated manner relative to one another, and/or wherein the third software module and the fourth software module can further be executed in an isolated manner relative to one another. <EOS>