Flight control indicator for aircraft

Claim 2

A flight control indicator for twin-engine aircraft, in particular a rotary-wing aircraft, comprising two turboengines for driving at least one rotor, intended to provide the power margin available on the engines of the aircraft as a function of the flight conditions, comprising: sensors (2, 3, 4) able to deliver information relating to various parameters for monitoring the engines, namely the gas generator regime (Ng), the free turbine inlet gas ejection temperature (T4), and the engine torque (Cm), means (5) for processing the information arising from said sensors, and display means (6) which present, on display screen (7), the processed information relating to the parameter, from among said monitoring parameters, whose current value is closest to the limit value for said parameter, wherein said display means (6) presents a single dial (8) furnished with two needles (9 1 , 9 2 ), each of them corresponding to a respective engine, and positioned in such a way that, when the engines are operating normally, the two needles are merged, and each needle (9 1 , 9 2 ) presenting the smallest margin between the gas generator regime (Ng), the free turbine inlet gas ejection temperature (T4), and the engine torque (Cm), said display means having two distinct graduations making it possible to differentiate, in flight, an idling engine from an engine which is faulty or has almost shut down.

Claim 3

The indicator as claimed in claim 1, wherein, for each engine, one mode, from among the various possible modes of operation of the engines, is automatically selected and displayed on said dial (8) as a function of the state of the engine.

Claim 4

The indicator as claimed in claim 2, wherein, for each mode of operation of the engines, the corresponding limitations, functions of the state of the engines and of their environments, in particular power limitations, are presented on said dial (8).

Claim 5

The indicator as claimed in claim 2, wherein, in startup mode, only the two limits of T4 at startup are presented.

Claim 6

The indicator as claimed in claim 1, comprising the displaying, on said display means (6), of the true numerical values of various parameters.

Claim 7

The indicator as claimed in claim 1, comprising mobile graduations.

Claim 8

A flight control indicator for twin-engine aircraft, in particular a rotary-wing aircraft, comprising two turboengines for driving at least one rotor, intended to provide the power margin available on the engines of the aircraft as a function of the flight conditions, comprising: sensors (2, 3, 4) able to deliver information relating to various parameters for monitoring the engines, namely the gas generator regime (Ng), the free turbine inlet gas ejection temperature (T4), and the engine torque (Cm), means (5) for processing the information arising from said sensors, and display means (6) which present, on a display screen (7), the processed information relating to the parameter, from among said monitoring parameters, whose current value is closest to the limit value for said parameter, wherein said display means (6) present a single dial (8) furnished with two needles (9 1 , 9 2 ), each of them corresponding to a respective engine, and positioned in such a way that, when the engines are operating normally, the two needles are merged, and each needle (9 1 , 9 2 ) presenting the smallest margin between the gas generator regime (Ng), the free turbine inlet gas ejection temperature (T4), and the engine torque (Cm), and wherein, for each engine, one mode, from among the various possible modes of operation of the engines, is automatically selected and displayed on said dial (8) as a function of the state of the engines, only the two limits of T4 at startup being presented in startup mode.

Claim 9

A flight control indicator for twin-engine aircraft, in particular a rotary-wing aircraft, comprising two turboengines for driving at least one rotor, intended to provide the power margin available on the engines of the aircraft as a function of the flight conditions, comprising: sensors (2, 3, 4) able to deliver information relating to various parameters for monitoring the engines, namely the gas generator regime (Ng), the free turbine inlet gas ejection temperature (T4), and the engine torque (Cm), means (5) for processing the information arising from said sensors, and display means (6) which present, on a display screen (7), the processed information relating to the parameter, from among said monitoring parameters, whose current value is closest to the limit value for said parameter, wherein said display means (6) present a single dial (8) furnished with two needles (9 1 , 9 2 ), each of them corresponding to a respective engine, and positioned in such a way that, when the engines are operating normally, the two needles are merged, and each needle (9 1 , 9 2 ) presenting the smallest margin between the gas generator regime (Ng), the free turbine inlet gas ejection temperature (T4), and the engine torque (Cm), and wherein, for each engine, one mode, from among the various possible modes of operation of the engines, is automatically selected and displayed on said dial (8) as a function of the state of the engines, only the two limits of T4 at startup being presented in startup mode.

Claim 10

The indicator as claimed in claim 7, wherein, for each mode of operation of the engines, the corresponding limitations, functions of the state of the engines and of their environments, in particular power limitations, are presented on said dial (8).

Claim 11

The indicator as claimed in claim 7, comprising the displaying, on said display means (6), of the true numerical values of various parameters.

Claim 12

The indicator as claimed in claim 7, comprising two distinct graduations making it possible to differentiate, in flight, an idling engine from an engine which is faulty or has almost shut down.

Claim 13

The indicator as claimed in claim 7, comprising mobile graduations.