| 摘要 |
In an engine control system for an aircraft diesel engine for a propeller aircraft for controlling the injection valves, charge pressure valves, common rail pressure valves and propeller control valves actuated by non-redundant actuators, comprising a plurality of sensors and a regulating device connected thereto and to the actuators, two engine control units - first and second - which are each connected to a first and a second power supply and are each connected to the sensors, are provided and are interconnected by way of a serial bus and can be connected selectively to the actuators by way of relays that are supplied with power together with the first engine control unit. The two engine control units each have a diagnostic function for calculating the respective health levels (A and B), which are determined by the defects detected, can be exchanged by way of the serial bus and are compared to one another. If the health level (A) of the first engine control unit is below the health level (B) of the second engine control unit, the power supply to the relay is interrupted, so that the second engine control unit is automatically connected to the actuators by way of the relays that have released, and consequently a redundant engine control system for an aircraft diesel engine is created. The core of the invention is the automatically switchable connection of the two engine control units communicating with one another via relays depending on the calculated health level.
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