Flight indicator that determines the maximum angle of climb for piloting an aircraft on a terrain-following flight

Abstract From the Canadian patent

The flight indicator (1) includes a set (2) of sources of information a calculation unit (3) connected to the said set (2) of sources of information and determining based on information issued from the said set (2) of sources of information at least the total maximum climb angle of the aircraft which corresponds to the maximum thrust and obtained based on the current performance measurement of the aircraft extrapolated to the maximum climb condition and anticipating engine failure and a heads-up display device (5) which presents at least the means which indicates the said maximum total climb angle and which is presented as an overlay of the existing environment in front of the aircraft on a …