Automatic assistance method for landing an aircraft

Patent metadata

Field	Value
Publication number	US-10410529-B2
Application number	US-201615558992-A
Country	US
Kind code	B2
Filing date	Mar 16, 2016
Priority date	Mar 16, 2015
Publication date	Sep 10, 2019
Grant date	Sep 10, 2019

Abstract

The invention relates to an automatic assistance method for landing an aircraft on a landing runway, from a return point (A) to a completion point (PA) at which the aircraft comes into contact with the landing runway, implemented by a data-processing device on-board said aircraft and configured to be linked to an inertial unit, an altimeter and a deviation meter, said method comprising: —guidance, based on position and attitude data provided by the inertia unit and altitude data provided by the altimeter, of the aircraft along a predefined trajectory from the return point (A) to a predetermined holding point (C) approximately aligned with the axis of the landing runway, the guidance been performed over at least one part of said predefined trajectory on the basis of corrected position data calculated using position data of the aircraft provided by the inertia unit and measurements transmitted by the deviation meter, —guidance from the holding point (C) to the completion point (PA).

First claim

The invention claimed is:

1. An automatic assistance method for landing an aircraft on a landing runway from a return point to a culmination point at which the aircraft comes into contact with the landing runway,
said method being implemented by a data processing device on board said aircraft and configured to be connected to:
an inertial unit configured to estimate the position and the attitude of the aircraft,
an altimeter configured to measure the altitude of the aircraft,
a distance ruler configured to measure, with respect to a reference point, an azimuth of the aircraft with respect to a reference direction,

wherein said method comprises:
a return navigation assistance phase comprising guidance (E1, E2), based on position and attitude data provided by the inertial unit and altitude data provided by the altimeter of the aircraft along a predefined trajectory from the return point to a predetermined connection point approximately aligned with the axis of the landing runway, guidance being achieved over at least a portion of said predefined trajectory based on corrected position data calculated using position data of the aircraft provided by the inertial unit and measurements transmitted by the distance ruler, said return navigation assistance phase comprising:
a first step of guiding the aircraft along the predefined trajectory from the return point to a predetermined capture point, based on position and attitude data provided by the inertial unit and altitude data provided by the altimeter,
a second step of guiding the aircraft along the predefined trajectory from the capture point to the connection point (C) based on attitude data provided by the inertial unit, altitude data provided by the altimeter and corrected position data calculated using the aircraft position data provided by the inertial unit ( 5 ) and azimuth measurements transmitted by the distance ruler, said predefined trajectory imposing a turning movement on the aircraft between the capture point and the connection point,
a landing assistance phase comprising a guidance of the aircraft from the connection point to the culmination point.

2. The assistance method according to claim 1 , wherein the first step of guiding the return navigation assistance phase comprises the guidance of the aircraft along the predefined trajectory from the return point to the capture point based on attitude data provided by the inertial unit, altitude data provided by the altimeter and corrected position data calculated using the aircraft position data provided by the inertial unit and azimuth measurements transmitted by the distance ruler.

3. The assistance method according to claim 1 wherein the predefined trajectory between the return point and the capture point (B) is rectilinear.

4. The assistance method according to claim 2 wherein the predefined trajectory between the return point and the capture point is a zigzag.

5. The assistance method according to claim 1 , wherein, the data processing device being configured to also be connected to a camera on board the aircraft, the landing assistance phase comprises the estimation of a position of the culmination point in an image of the landing runway captured by the camera and the estimation of a position of the aircraft depending on said position of the culmination point estimated in the image and altitude data provided by the altimeter.

6. The assistance method according to any claim 1 , wherein, the data processing device further being configured to be connected to a transceiver on board said aircraft and designed to receive signals emitted by at least three transceivers positioned on the ground, the landing assistance phase comprises the estimation of corrected position data of the aircraft based on position data provided by the inertial unit, azimuth measurements transmitted by the distance ruler, distance data between the on-board transceiver and said at least three ground-based transceivers.

7. A non-transitory computer program product comprising code instructions which when executed by a processor perform an automatic assistance method for landing an aircraft on a landing runway from a return point to a culmination point at which the aircraft comes into contact with the landing runway,
said method being implemented by a data processing device including said processor on board said aircraft and configured to be connected to:
an inertial unit configured to estimate the position and the attitude of the aircraft,
an altimeter configured to measure the altitude of the aircraft,
a distance ruler configured to measure, with respect to a reference point, an azimuth of the aircraft with respect to a reference direction,
wherein said method comprises:
a return navigation assistance phase comprising guidance (E1, E2), based on position and attitude data provided by the inertial unit and altitude data provided by the altimeter of the aircraft along a predefined trajectory from the return point to a predetermined connection point approximately aligned with the axis of the landing runway, guidance being achieved over at least a portion of said predefined trajectory based on corrected position data calculated using position data of the aircraft provided by the inertial unit and measurements transmitted by the distance ruler, said return navigation assistance phase comprising:
a first step of guiding the aircraft along the predefined trajectory from the return point to a predetermined capture point, based on position and attitude data provided by the inertial unit and altitude data provided by the altimeter,
a second step of guiding the aircraft along the predefined trajectory from the capture point to the connection point (C) based on attitude data provided by the inertial unit, altitude data provided by the altimeter and corrected position data calculated using the aircraft position data provided by the inertial unit ( 5 ) and azimuth measurements transmitted by the distance ruler, said predefined trajectory imposing a turning movement on the aircraft between the capture point and the connection point,
a landing assistance phase comprising a guidance of the aircraft from the connection point to the culmination point.

8. A data processing device configured for implementing an automatic assistance method for landing an aircraft on a landing runway from a return point to a culmination point at which the aircraft comes into contact with the landing runway,
said aircraft including said data processing device,
said method being implemented by said data processing device and configured to be connected to:
an inertial unit configured to estimate the position and the attitude of the aircraft,
an altimeter configured to measure the altitude of the aircraft,
a distance ruler configured to measure, with respect to a reference point, an azimuth of the aircraft with respect to a reference direction,
wherein said method comprises:
a return navigation assistance phase comprising guidance (E1, E2), based on position and attitude data provided by the inertial unit and altitude data provided by the altimeter of the aircraft along a predefined trajectory from the return point to a predetermined connection point approximately aligned with the axis of the landing runway, guidance being achieved over at least a portion of said predefined trajectory based on corrected position data calculated using position data of the aircraft provided by the inertial unit and measurements transmitted by the distance ruler, said return navigation assistance phase comprising:
a first step of guiding the aircraft along the predefined trajectory from the return point to a predetermined capture point, based on position and attitude data provided by the inertial unit and altitude data pro

Assignees

• Safran Electronics & Defense

Inventors

• Chiodini Alain
• Pouillard Sylvain

Classifications

• G08G5/0086

  Physics · mapped topic

• G08G5/0021

  Physics · mapped topic

• G08G5/0078

  Physics · mapped topic

• G08G5/065

  Physics · mapped topic

• G05D1/0676 Primary

  specially adapted for landing · CPC title