초록 ▼

Device and process for regulating the power of the engines of a rotary wing multi-engine aircraft. The regulating device (1) comprises, in addition to main regulating systems (2, 6) associated with the engines (M1,M2) of the aircraft, auxiliary regulating systems (12, 13) associated with said engine

Device and process for regulating the power of the engines of a rotary wing multi-engine aircraft. The regulating device (1) comprises, in addition to main regulating systems (2, 6) associated with the engines (M1,M2) of the aircraft, auxiliary regulating systems (12, 13) associated with said engines (M1,M2) and means (10, 11) for determining the speeds of rotation of the engines (M1,M2). Each auxiliary regulating system (12, 13) is capable of automatically adjusting the flow rate of fuel in such a way as to slave the speed of rotation of the associated engine, when its main regulating system has failed, to the speed of rotation of the other engine of the aircraft.

대표청구항 ▼

1. 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 en

1. 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. 2. The device as claimed in claim 1, wherein at least one of said supply means comprises an electric actuator and a fuel metering valve.3. The device as claimed in claim 2, wherein said fuel metering valve comprises an anti-shutdown stop.4. The device as claimed in claim 1, wherein at least one of said triggering means is manual.5. The device as claimed in claim 1, wherein at least one of said triggering means is automatic.6. The device as claimed in claim 1, wherein at least one of said auxiliary regulating systems furthermore comprises a display means operable to depict on a display screen the state of said auxiliary regulating system.7. A process for regulating the power of the engines of a rotary wing aircraft, in particular a helicopter which is furnished with at least two engines, each of which comprises a main regulating system, said process comprising, when one of said main regulating systems has failed, controlling automatically the flow rate of fuel which is fed to the engine, whose main regulating system has failed, by way of an auxiliary regulating system in such a way as to slave the speed of rotation NG1 of this engine to the speed of rotation NG2 of the other engine. 8. The process as claimed in claim 7, wherein the flow rate of fuel is controlled in such a way that the increase or the decrease in said flow rate is variable and varies as a function of the discrepancy between the speed of rotation NG1 and the speed of rotation NG2.9. The process as claimed in claim 7, wherein, to slave the speed of rotation NG1 to the speed of rotation NG2: the following expression E is determined: E=NG 1+K.dNG1/dt  in which: K is a predetermined parameter; anddNG1/dt is the derivative with respect to time of the speed of rotation NG1; this expression E is compared with thresholds which are defined on the basis of the speed of rotation NG2; and the slaving to be carried out is deduced on the basis of this comparison. 10. The process as claimed in claim 7, wherein the fuel flow rate is controlled as follows: in a case a), for which the following conditions hold simultaneously: NG2>60% and NG1>75%,&Dgr;=(|NG2−NG1|+0.9d|NG2−NG1|/dt)>1% d/dt being the derivative with respect to time, and(NG2−NG1)70% and NG1>75%,&Dgr;=(|NG2−NG1|+0.9d|NG2−NG1|/dt)>1%, and(NG2−NG1)>0, the fuel flow rate is increased; and otherwise, in a case c), the fuel flow rate is maintained at the value which it had upon the appearance of said failure. 11. The process as claimed in claim 10, wherein the fuel flow rate is controlled by controlling the speed of rotation of an electric actuator which is associated with a fuel metering valve, and wherein, for case a), in order to reduce the fuel flow rate, a speed of rotation of the electric actuator of substantially 9°/s is ordered if the discrepancy &Dgr; is greater than 3% and a speed of rotation of the electric actuator of substantially 3°/s is ordered if the discrepancy &Dgr; is less than or equal to 3%, and for case b) in order to increase the fuel flow rate, a speed of rotation of the electric actuator of substantially 3°/s is ordered.12. The process as claimed in claim 11, wherein said fuel metering valve is common to a main regulating system and an auxiliary regulating system which are associated.