Landing aid method and device for an aircraft

Patent metadata

Field	Value
Publication number	US-9776734-B2
Application number	US-201514750688-A
Country	US
Kind code	B2
Filing date	Jun 25, 2015
Priority date	Jul 4, 2014
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

A landing aid method and device for an aircraft including a unit for calculating automatically in a repetitive manner, during a final approach of the aircraft with a view to landing on a landing runway, using at least a ground speed of the aircraft, a height of the aircraft in relation to the ground, and a target vertical speed representing a vertical speed required on contact with the landing runway, a slope angle of a flight path allowing the aircraft to perform a flare, checking at least the target vertical speed on contact with the landing runway, and a unit for displaying automatically, on at least one screen of the flight deck of the aircraft, a first symbol illustrating the current slope angle of the aircraft and a second symbol illustrating the calculated slope angle.

First claim

The invention claimed is:

1. A landing aid method for an aircraft, comprising, in an automatic and repetitive manner, during a final approach of the aircraft with a view to landing on a landing runway:
a) receiving current values of a plurality of parameters, including a ground speed of the aircraft and a height of the aircraft in relation to ground;
b) calculating a slope angle of a flight path of the aircraft, using at least the current values of the ground speed of the aircraft and the height of the aircraft and at least a target vertical speed, the target vertical speed representing a vertical speed required on contact with the landing runway, wherein the flight path comprises a descent phase followed by a flare phase so that, if the aircraft follows the flight path, the aircraft will be descending at the target vertical speed on contact with the landing runway; and
c) displaying, on at least one screen of the flight deck of the aircraft, and while the aircraft is in the descent phase of the flight path, a first symbol at a fixed location on the at least one screen and a second symbol as moving across the at least one screen in a direction towards the first symbol at a rate based on a variation rate of the slope angle of the flight path so that the second symbol reaches the fixed location of the first symbol in the direction across the at least one screen at a time for the aircraft to transition from the descent phase of the flight plan to the flare phase of the flight plan; and
d) displaying, on the at least one screen of the flight deck of the aircraft, and while the aircraft is in the flare phase of the flight path, the first symbol illustrating a current slope angle of a current path of the aircraft by positioning the first symbol at a first distance in the direction across the at least one screen and the second symbol illustrating the slope angle of the flight path, calculated in step b), by positioning the second symbol at a second distance in the direction across the at least one screen.

2. The method as claimed in claim 1 , comprising a step of determining a slope value of the landing runway, and wherein step b) comprises calculating the slope angle of the flight path using the slope value of the landing runway.

3. The method as claimed in claim 2 , wherein determining the slope value of the landing runway takes into account at least one of the following slope values:
a slope value input by a member of the crew of the aircraft;
a slope value corresponding to that of the landing runway used for the landing, this slope value being extracted automatically from an on-board database; and
a slope value measured using at least one on-board measuring device.

4. The method as claimed in claim 2 , comprising an additional step of monitoring the slope value of the landing runway to detect an incorrect slope value.

5. The method as claimed in claim 4 , comprising an additional step of, in the event of detection of an incorrect slope value, automatically performing at least one of the following operations:
emitting an alarm signal in the flight deck of the aircraft;
correcting the incorrect slope value;
using a default slope value in step b);
deactivating at least the display of the second symbol; and
supplying the crew with information relating to the origin of a fault having resulted in the incorrect slope value and relating to actions to be taken.

6. The method as claimed in claim 1 , comprising generating a control parameter suitable for modifying shape of the flight path, this control parameter being used in step b) to calculate the slope angle.

7. The method as claimed in claim 1 , comprising receiving a target vertical acceleration representing a vertical acceleration required on contact with the landing runway, and wherein step b) comprises calculating the slope angle of the flight path also using this target vertical acceleration.

8. A landing aid device for an aircraft, the landing aid device comprising:
at least one data-receiving unit to receive automatically, during a final approach of the aircraft with a view to a landing on a landing runway, the current values of a plurality of parameters, including a ground speed of the aircraft and a height of the aircraft in relation to the ground, and also at least one target vertical speed representing a vertical speed required on contact with the landing runway;
a calculation unit configured to calculate automatically, at least using the current values of the ground speed of the aircraft and the height of the aircraft and the at least one target vertical speed, a slope angle of a flight path, wherein the flight path comprises a descent phase followed by a flare phase so that, if the aircraft follows the flight path, the aircraft will be descending at the at least one target vertical speed on contact with the landing runway; and
a display unit configured to display automatically, on at least one screen of the flight deck of the aircraft, and while the aircraft is in the descent phase of the flight path, a first symbol at a fixed location on the at least one screen and a second symbol as moving across the at least one screen in the direction towards the first symbol at a rate based on a variation rate of the slope angle of the flight path so that the second symbol reaches the fixed location of the first symbol in the direction across the at least one screen at a time for the aircraft to transition from the descent phase of the flight plan to the flare phase of the flight plan, and to display on the at least one screen of the flight deck of the aircraft, and while the aircraft is in the flare phase of the flight path, the first symbol illustrating a current slope angle of a current path of the aircraft by positioning the first symbol at a first distance in the direction across the at least one screen and the second symbol illustrating the slope angle of the flight path, calculated in step b), by positioning the second symbol at a second distance in the direction across the at least one screen.

9. The landing aid device as claimed in claim 8 , comprising at least a first additional unit configured to determine automatically a slope value of the landing runway, and wherein the calculation unit is configured to calculate the slope angle of the flight path using this slope value of the landing runway.

10. The landing aid device as claimed in claim 9 , comprising at least a second additional unit configured to monitor automatically the slope value of the landing runway to detect an incorrect slope value.

Assignees

• Airbus Operations Sas

Inventors

• Eberle Matthias

Classifications

• B64D45/08 Primary

  optical · CPC title

• G01C9/005

  specially adapted for use in aircraft · CPC title

• G01C23/00

  Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration · CPC title

• G01C21/20

  Instruments for performing navigational calculations (G01C21/24, G01C21/26 take precedence) · CPC title

• G05D1/0676 Primary

  specially adapted for landing · CPC title