Flight control indicator determining the maximum slope for the flight control of an aircraft by terrain following
View Patent ↗The flight control indicator may include a set of information sources, a computation unit connected to said set of information sources, and a head-up display device. The computation unit determines, on the basis of information emanating from the set of information sources, at least one maximum total slope of the aircraft. The maximum total slope corresponds to the maximum thrust and is obtained on the basis of the measurement of the current performance of the aircraft, extrapolated to the condition of maximum slope and in anticipation of an engine fault. The head-up display device presents, on a display screen, at least one indicator which indicates the maximum total slope and which is presented superimposed on the environment existing in front of the aircraft.
1. A flight control indicator for an aircraft, said flight control indicator comprising:
a set of information sources;
a computation unit which is connected to said set of information sources; and
a display device which comprises a display screen and which is connected to said computation unit,
wherein
said computation unit determines, on the basis of information emanating from said set of information sources, at least one maximum total slope of the aircraft, which corresponds to the maximum thrust and is obtained on the basis of the measurement of the current performance of the aircraft, extrapolated to the condition of maximum slope and anticipating an engine fault; and
said display device is a head-up display device and presents, on the display screen, at least one indicator which indicates said maximum total slope and which is presented superimposed on the environment existing in front of the aircraft.
2. The flight control indicator as claimed in claim 1 , wherein said set of information sources provides the computation unit with at least some of the following information: the current kinetic state, the current atmospheric state, the current altitude and an aerodynamic polar of the aircraft.
3. The flight control indicator as claimed in claim 1 , wherein said computation unit determines said maximum total slope for the optimal climb speed.
4. The flight control indicator as claimed in claim 1 , wherein said computation unit determines said maximum total slope for the current speed.
5. An aircraft, which comprises a flight control indicator as specified under claim 1 .