Patent ID: 8170727
Filing Date: 2012-05-01
Classification: G05D,G08G,Y02T

Abstract:
1. A method for calculating an approach trajectory of an aircraft to a runway of an airport, the aircraft being controlled in terms of trajectory flight path angle and speed, in terms of trajectory flight path angle and thrust or in terms of thrust and speed, the aircraft being able to fly at reduced engine thrust, the descent/approach trajectory terminating in an impact point on the runway and comprising a high-altitude descent segment constructed on the basis of an idle thrust and speed setpoint, an intermediate geometric segment constructed on the basis of speed and slope setpoints appending altitude constraints, to which the aircraft is controlled in terms of trajectory flight path angle and thrust and then in terms of trajectory flight path angle and speed, said method comprising the following steps: calculating a final approach segment at reduced idle engine thrust and a landing segment with adequate thrust for preparing a possible go-around, to which the aircraft is controlled in terms of thrust and speed, wherein the landing segment has a slope of trajectory less than a slope of trajectory of the final approach segment and the landing segment performed with engine thrust greater than the reduced engine thrust; calculating a maximum impact point, the runway comprising an extreme limit point, the extreme limit point being defined as the most distant impact point on the runway in the direction of landing in service below which the aircraft lands, brakes and disengages the runway without risk, the maximum impact point being situated on the runway upstream of the extreme limit point at a safety distance; and calculating a point of switchover to reduced engine thrust, the aircraft flying under meteorological conditions defined by a maximum wind and a minimum wind, the point of switchover to reduced engine thrust being defined by the intersection between: a descent trajectory at reduced engine thrust with the maximum wind and according to the approach speed suited to the maximum wind, having the minimum impact point as point of impact with the runway, and a descent trajectory at reduced engine thrust with the minimum wind and according to the approach speed suited to the minimum wind, having the maximum impact point as point of impact with the runway.