FIELD: engines.
SUBSTANCE: group of inventions relates to power control method and system in case of aircraft engine failure. For power control in case of at least one aircraft engine failure increasing of main engine type power plant (GPP) operation limits in accordance with three emergency modes, arranged in series in order of power level reduction. At that, in special hazard mode providing power increase for attempt to start failed engine, in maximum hazard mode providing all or part of non-thrust power, in medium hazard mode providing minimum fraction of non-thrust power until end of flight. In case of exceeding of maximum action periods allocated for each emergency mode, emergency actuation function distributes non-thrust power take-off between engines and GPP automatically or in accordance with pilot’s command. Power control system contains flight control center with data processing unit, servicing module, engines and GPP control and monitoring (FADEC) modules, connected in certain way with bidirectional data transmission channels.
EFFECT: providing for power control in case of at least one aircraft engine failure.
10 cl, 5 dwg
