Procedure helps the approach and landing of an aircraft (11) using a deposicionamiento satellite system and MLS system under an axial approach calculated elsistema MLS a runway (1), a placing station comprising (4) and a station azimuth (5) defining the runway (1) a cartesian reference system direct Rc comprising, as axes, one ejelongitudinal of the runway (1), called first axis (x) , a transverse axis of the runway (1) quepasa by placing station (4), called second axis (y) and an axis perpendicular to the first and segundoejes, called third axis (z), an intersection point between the first axis (x) and the second axis (y) which defines the centrodel reference system Rc, called point of the track (6), the placing station (4) comprising an antenna site (7) and the station comprising deazimut (5) an antenna azimuth (8) , Each antenna comprising a center phase, the phase centers delas antennas location (7) and azimuth (8) located in a plane parallel to a plane (x, y) being a distance dzdel track point (6 ) according to the third axis (z), comprising the following steps: (41) creating a reference point Pref of the same coordinates as the phase center of the deazimut antenna (8) and / or antenna emplacement (7), (42) determining a Ρ distance between the reference point Pref and the aircraft (11) by deposicionamiento satellite system (43) determining an azimuth angle (θR) between a line through the phase center azimuth antenna (8) and the aircraft (11) and parallel to a plane (x, z) passing through the phase center of the antenna azimuth (8) plane, (44) determining a angle location (Ρ) between a line passing through the center of phase of the deazimut antenna (8) and the aircraft (11) and the plane parallel to plane (x And) passing through the phase centers of antenasde location (7) and bearing (8), (45) determining, from the distance Ρ between the reference point Pref and the aircraft (11), the angle deazimut and angle location, the position of the aircraft (11) relative to the reference point Pref, comprising determining the distance Ρ between the reference point Pref and the aircraft (11) the siguientesetapas: creating, in the system reference Rc, an intermediate point (a) of the same coordinates (λA, ΦA, hA) that lascoordenadas (λMLS, ΦMLS, HMLS) point of the track (6) along the first axis (x) and the second axis ( y) and demisma coordinate the reference point Pref following the third axis (z), determining a DMLS distance between the intermediate point (a) and the aircraft (11), determine an azimuth angle θref between the plane (x, z ) and a straight line passing through the reference point Pref and laaeronave, determining a distance d between the point of the track (6) and the reference point Pref following the second axis (y), calculate the distance between the point Ρ reference Pref and the aircraft (11) by the ratio ** ** Formula.
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