Device for controlling an aircraft engine comprising two redundant control channels

A device for controlling an engine, the engine comprising a first control channel (V1) and a second control channel (V2), each control channel comprising a first sensor (CAV1, CAV2) and a second sensor (CBV2, CBV2), each first and second sensor being configured to supply a first measurement (A) and a second measurement (B) to the first control channel and to the second control channel respectively, each of the first and second channels comprising an active or passive state defining an active channel (V1) or a passive channel (V2), the active channel (V1) being intended to drive at least one actuator (ACT) of the engine whereas the passive channel (V2) is intended to take over on the active channel in the event of malfunction of the active channel, the device being such that each first and channel (V1, V2) comprises:

• a unit (UC1, UC2) for configured to consolidate measurements, the unit receiving as input the measurements coming from the first and second channels by way of at least one inter-channel communication link (LCOM) in such a way as to obtain a consolidation parameter,
• at least one unit (UT1, UT2) configured to process at least one command (CV1, CV2) of at least one actuator of the engine (ACT),
• the device being in a nominal operation in which the unit (UT1, UT2) of the first channel and of the second channel for computing each first and second channel (V1, V2) computes the command (CV1, CV2) as a function of the consolidation parameter and of the command computed at the previous computing time, the actuator being driven by the active channel,
• the device being in a failsafe operation, in the event of interruption of the communication link (LCOM), in which the unit (UT2) for computing the passive channel computes the command (CV2) as a function of the command (CV1) computed by the active channel (V1) at the previous computing time.