Patent ID: 6742742
Filing Date: 2004-06-01
Classification: B64C,B64D,F02C

Abstract:
A device for regulating the power of the engines of a rotary wing aircraft, in particular a helicopter which is furnished with at least two engines, said regulating device comprising main regulating systems associated respectively with said engines and intended to supply fuel to the associated engines respectively,which device furthermore comprises auxiliary regulating systems associated respectively with said engines, and means for determining the speeds of rotation of said engines, and in which each of said auxiliary regulating systems comprises:at least one triggering means for triggering said auxiliary regulating system, when the main regulating system of the associated engine has failed; a controllable supply means which is capable of supplying fuel to the associated engine; and a control means operable to automatically control said supply means so as to adjust the fuel flow rate in such a way as to slave the speed of rotation of the engine, whose main regulating system has failed, to the speed of rotation of the other engine of the aircraft.