AIRCRAFT ENGINE CONTROL DEVICE CONTAINING TWO REDUNDANT CONTROL CHANNELS Russian patent published in 2024 - IPC G05B9/03 

FIELD: turbojet engine.

SUBSTANCE: device contains a first control channel (V1) and a second control channel (V2), each control channel contains a first sensor (CAV1, CAV2) and a second sensor (CBV1, CBV2), each of which is configured to provide a first measurement (A) and a second measurement (B) into each channel, with each channel having an active or passive state, defining an active channel (V1) or a passive channel (V2). The active channel (V1) is designed to control one drive (ACT) of the engine, while the passive channel (V2) is intended to replace the active channel in the event of a malfunction of the latter. In the event of an emergency operation when the specified communication line (LCOM) is broken, the specified computing unit (UT2) of the passive channel calculates the command (CV2) depending on the command (CV1) calculated by the active channel (V1) at the previous moment of calculation.

EFFECT: increasing the robustness and reliability of the system with respect to inter-channel communication losses in order to be able to reliably localize anomalies and ensure isolation of only the faulty channel.

11 cl, 5 dwg