Granted Patent B2

US 12,380,807 · App. 17/774,781 · Granted Aug 5, 2025

Inventors: Rodolphe Cottron (Mérignac, FR); Jean-Philippe Lebrat (Mérignac, FR); Yoan Veyrac (Mérignac, FR)

Assignee: THALES

G08G5/54B64D45/08G01S13/89G01S13/933G08G5/21

Abstract

Claims (29)

1. A method for assisting a landing of an aircraft on a landing runway, the landing runway having a longitudinal axis equidistant from a longitudinal edges of the landing runway, called a runway axis, the landing runway comprising a set of characteristic elements, the characteristic elements being distributed over the landing runway in at least two longitudinal rows and at least one transverse row, the longitudinal rows being substantially parallel to the runway axis, with two of the longitudinal rows each being arranged along a distinct longitudinal edge of the landing runway, with the or each transverse row being substantially perpendicular to the runway axis, a last transverse row in a direction of landing the aircraft on the landing runway being called a runway threshold, the method being implemented by a landing assistance device comprising a radar and a calculator, the radar having a longitudinal detection axis, called the radar axis, the method comprising:

detecting, by the radar characteristic elements of the landing runway, each detection being associated to coordinates,

determining an angular offset between the radar axis and the runway axis as a function of the coordinates of the characteristic elements detected, and

determining, as a function of the angular offset determined and the coordinates of the characteristic elements detected:

a distance of an orthogonal projection onto the runway axis of a horizontal projection of the radar, called an axial offset, the horizontal projection of the radar being the orthogonal projection of a position of the radar in a horizontal plane of the landing runway, and

the distance of the orthogonal projection onto a line passing through the runway threshold of the horizontal projection of the radar, called the distance to the runway threshold,

wherein the method further comprises a step of determining a horizontal velocity of the aircraft in relation to the runway axis expressed in two components as a function of values over time of the determined angular offset and a Cartesian coordinates of the detections corrected for said angular offset,

wherein the step of determining the horizontal velocity of the aircraft comprises:

determining a first point cloud representing an actual positions of the detections at a first instant, corrected by the value of the angular offset determined,

determining a second point cloud representing the actual positions of the detections at a second instant, corrected by the value of the angular offset determined, with the second instant being later than the first instant

for test values of the components of a horizontal speed of the aircraft, determining third point clouds representing theoretical positions of the detections at the second instant as a function of the first point cloud, and

calculating the distance between the first point cloud and each third point cloud, with the components of the horizontal velocity being obtained as a function of a minimum distance calculated and a time difference between the first instant and the second instant.

2. The method according to claim 1 , wherein a step of determining the angular offset comprises:

converting the coordinates of each detection into Cartesian coordinates,

for each angular offset value comprised in a predetermined value interval, determining a Cartesian coordinate along a x-axis, for each detection, corrected by the value of said angular offset,

for each angular offset value comprised in the predetermined value interval, determining a number of detections corresponding to each Cartesian coordinate corrected along the x-axis, the angular offset value associated with a greatest number of detections being the angular offset between the radar axis and the runway axis.

3. The method according to claim 1 , wherein a distance determination step comprises:

calculating a Cartesian coordinates of each detection, corrected for the angular offset determined in the determination step, known as optimal Cartesian coordinates,

determining a histogram of the positions along a x-axis of each detection as a function of the optimal Cartesian coordinates of each detection, the histogram having at least two peaks, and

determining the axial offset as a function of the Cartesian coordinates along the x-axis of the at least two peaks of the histogram.

4. The method according to claim 1 , wherein a distance determination step comprises:

calculating a Cartesian coordinates of each detection, corrected for the angular offset determined in the determination step, known as optimal Cartesian coordinates,

determining a histogram of the positions along a y-axis of each detection as a function of the optimal Cartesian coordinates of each detection, the histogram having at least one peak, and

determining the distance to the runway threshold as a function of the Cartesian coordinates on the y-axis of a one or more peaks in the histogram.

5. The method according to claim 1 , wherein the method comprises a step of determining a value of at least one trajectory value as a function of the determined axial offset and the determined distance to the runway threshold,

the at least one trajectory value being selected from: an angular lateral deviation of the aircraft, an angular vertical deviation of the aircraft, a metric lateral deviation of the aircraft and a metric vertical deviation of the aircraft.

6. The method according to claim 1 , wherein the method comprises a first step of determining a horizontal velocity of the aircraft in relation to a runway centerline expressed in two components as a function of a variation over time of the distance to the runway threshold and the variation over time of the axial offset.

7. A device for assisting the landing of an aircraft on a landing runway, the landing runway having a longitudinal axis equidistant from the longitudinal edges of the landing runway, called the runway axis, the landing runway comprising a set of characteristic elements the characteristic elements being distributed on the landing runway in at least two longitudinal rows and at least one transverse row, the longitudinal rows being substantially parallel to the runway axis, two of the longitudinal rows each being arranged along a distinct longitudinal edge of the landing runway, the or each transverse row being substantially perpendicular to the runway axis, with the last transverse row in the direction of landing the aircraft on the landing runway being called the runway threshold, the landing assistance device comprising a radar and a calculator, the radar having a longitudinal detection axis, called the radar axis, the landing assistance device being configured to implement a method according to claim 1 .

8. An aircraft comprising a landing assistance device according to claim 7 .

Assignments (1)

Priority Claims (1)

Continuity (1)

References Cited (22)