Patent ID: 7952492

Claim:
A landing assistance method for an aircraft in approach phase located at a current height h and descending toward a runway following, with a current approach speed V, a current approach trajectory forming with said runway a current approach angle γ, said current approach speed V and said current approach angle γ ideally needing to be close, respectively, to a constant reference approach speed Vr and a constant reference approach angle γ associated with said runway, wherein: a range of approach speed values is predetermined, either side of said reference approach speed Vr, that will allow for a complete stoppage of said aircraft on said runway in the case where the current approach angle γ is at least approximately equal to said reference approach angle γr, said range of approach angles being delimited by a lower limit value Vinf and by an upper limit value Vsup; a range of approach angle values is predetermined, either side of said reference approach angle γr, that will allow for a complete stoppage of said aircraft on said runway in the case where the current approach speed V is at least approximately equal to the reference approach speed Vr, said range of approach angle values being delimited by a lower limit value γinf and by an upper limit value γsup; there are calculated: a lower total energy threshold Einf, corresponding to the situation for which the current approach speed V and the current approach angle γ are respectively equal to said lower limit value Vinf and said lower limit value γinf, an upper total energy threshold Esup, corresponding to the situation for which the current approach speed V and the current approach angle γ are respectively equal to said upper limit value Vsup and said upper limit value γsup, and the current total energy E of said aircraft; and said current total energy E is compared with said lower Einf and upper Esup total energy thresholds to obtain an indication as to the theoretical possibility for said aircraft to stop on said runway.