METHOD AND SYSTEM FOR REGULATING POWER IN THE EVENT OF AT LEAST ONE AIRCRAFT ENGINE FAILURE

摘要

With a view to optimizing the resources needed to continue the flight upon the loss of at least one main engine, the invention seeks to unburden the propulsion system that has remained operative of all or some of the non-propulsive energy tappings through a continuously-operating additional generation of non-propulsive power. More specifically the method involves, using the power production unit GPP, constantly in operation during flight and taking over some (PGA) of the nominal total non-propulsive power (PTA) of the aircraft, to supply, almost instantaneously, increased non-propulsive powers (PSU, PMU, PIU) according to at least three respective emergency settings (RS, RM, RI) upon said engine failure. The GPP control and monitoring function assesses the time elapsed for each emergency setting (RS, RM, RI), and informs the data processing unit of this time with an alarm being emitted if the operating times (Xmax, Ymax, Zmax) allocated to each emergency setting (RS, RM, RI) are exceeded, and the emergency function adjusts the aircraft's non-propulsive power tappings between the main engines and the unit GPP either automatically or on the orders of the pilot.