Method of detecting proximity to the ground of a side arrangement on an aircraft, and an aircraft

Patent metadata

Field	Value
Publication number	US-11480429-B2
Application number	US-201916704391-A
Country	US
Kind code	B2
Filing date	Dec 5, 2019
Priority date	Dec 19, 2018
Publication date	Oct 25, 2022
Grant date	Oct 25, 2022

Abstract

A method of assisting in piloting an aircraft having a fuselage, the aircraft having a first side arrangement and a second side arrangement, which arrangements are disposed laterally on either side of the fuselage, and each of them participates in the movement of the aircraft. During an assistance phase, the method includes the following steps: measuring a value of a first ground clearance of the first side arrangement and a value of a second ground clearance of the second side arrangement; and displaying on a screen at least one symbol that varies as a function of the variation in the value of the first ground clearance and/or of the variation in the value of the second ground clearance.

First claim

What is claimed is:

1. A method of assisting in piloting an aircraft having a fuselage that extends longitudinally from a nose towards a rear end, the aircraft having a first side arrangement and a second side arrangement, which first side arrangement and second side arrangement are disposed laterally on respective sides of the fuselage, and participate in the lift and/or propulsion of the aircraft;
wherein, during an assistance phase, the method includes the following steps:
measuring, with a first sensor, a value of a first ground clearance of the first side arrangement, the first ground clearance being a first distance separating the first side arrangement and the ground, and measuring, with a second sensor, a value of a second ground clearance of the second side arrangement, the second ground clearance being a second distance separating the second side arrangement and the ground; and
displaying on a screen at least one symbol that varies as a function of the variation in the value of the first ground clearance and/or of the variation in the value of the second ground clearance.

2. The method according to claim 1 ,
wherein, for measuring the value of the first ground clearance and the value of the second ground clearance, the method includes the following steps:
acquiring at least one first measurement signal with the first sensor, which first measurement signal carries a first piece of information that is an image of the value of the first ground clearance, and acquiring at least one second measurement signal with the second sensor, which second measurement signal carries a second piece of information that is an image of the value of the second ground clearance; and
determining the value of the first ground clearance by processing the first measurement signal(s), and determining the value of the second ground clearance by processing the second measurement signal(s).

3. The method according to claim 1 ,
wherein, for measuring the value of the first ground clearance and the value of the second ground clearance, the method includes the following steps:
acquiring a plurality of first measurement signals with a plurality of first sensors of the first ground clearance, and acquiring a plurality of second measurement signals with a plurality of second sensors of the second ground clearance;
conditioning the plurality of first measurement signals and the second measurement signals;
consolidating the plurality of first measurement signals and the plurality of second measurement signals following the conditioning via a voting method for obtaining respectively the value of the first ground clearance and the value of the second ground clearance.

4. The method according to claim 1 ,
wherein the aircraft is provided with a plurality of first sensors containing at least two first sensors that are dissimilar and/or disposed in mutually different zones of the first side arrangement, the aircraft being provided with a plurality of second sensors containing at least two second sensors that are dissimilar and/or disposed in mutually different zones of the second side arrangement.

5. The method according to claim 1 ,
wherein the displaying of the symbol(s) is dependent on detection of at least one of following two events:
detection that a retractable undercarriage of the aircraft is deployed;
detection that the value of the first ground clearance is less than a threshold height or that the second ground clearance is less than the threshold height.

6. The method according to claim 1 ,
wherein the method includes a step of determining a roll set value to be complied with, the at least one symbol comprising a central symbol that moves along a reference segment, and the positioning of the central symbol along the reference segment being a function of the roll set value.

7. The method according to claim 6 ,
wherein the central symbol comprises a first portion and a second portion that represent respectively the first ground clearance and the second ground clearance, a background of the first portion and a background of the second portion varying as a function respectively of the value of the first ground clearance and of the value of the second ground clearance.

8. The method according to claim 1 ,
wherein the at least one symbol comprises a first symbol and a second symbol, the first symbol extending in a direction from a horizon segment representing the horizon of an artificial horizon to a first end over a first length that is a function of the value of the first ground clearance, and the second symbol extending in the direction from the horizon segment to a second end over a second length that is a function of the value of the second ground clearance.

9. The method according to claim 8 ,
wherein the first symbol has a background that varies as a function of the value of the first ground clearance and the second symbol has a background that varies as a function of the value of the second ground clearance.

10. The method according to claim 8 ,
wherein the method includes a step of displaying a ground segment connecting the first end to the second end.

11. The method according to claim 1 ,
wherein, with the aircraft being provided with at least one undercarriage that can be compressed so that it is either in a compressed state or in a non-compressed state, the method includes the following steps:
determining that the at least one undercarriage is in the compressed state or in the non-compressed state; and
assigning to the at least one symbol an appearance that varies while the undercarriage(s) is/are going from the compressed state to the non-compressed state and vice versa.

12. An aircraft having a fuselage that extends longitudinally from a nose towards a rear end, the aircraft having a first side arrangement and a second side arrangement, which first side arrangement and second side arrangement are disposed laterally on respective sides of the fuselage, and each of them participates in the lift and/or propulsion of the aircraft;
wherein the aircraft is provided with at least one first sensor emitting a first signal relating to the value of a first ground clearance of the first side arrangement, the first ground clearance being a first distance separating the first side arrangement and the ground, the aircraft being provided with at least one second sensor emitting a second signal relating to the value of a second ground clearance of the second side arrangement, the second ground clearance being a second distance separating the second side arrangement and the ground, the aircraft being provided with a screen and with a computer, the computer being connected to each first sensor and to each second sensor, and to the screen, and the computer being configured to transmit a control signal to the screen to display at least one symbol that varies as a function of the variation in the value of the first ground clearance and/or of the variation in the value of the second ground clearance.

13. The aircraft according to claim 12 ,
wherein the aircraft is provided with at least two of the at least first sensors of the at least one first sensor that are dissimilar and/or disposed in mutually different zones of the first side arrangement, the aircraft being provided with at least two of the at least second sensors of the at least one second sensor that are dissimilar and/or disposed in mutually different zones of the second side arrangement.

14. The aircraft according to claim 12 ,
wherein at least one first sensor or at least one second sensor comprises a lidar sensor or a radio altimeter.

15. The aircraft according

Assignees

• Airbus Helicopters

Inventors

• Abdelli Kamel

Classifications

• G01S15/86

  Combinations of sonar systems with lidar systems; Combinations of sonar systems with systems not using wave reflection · CPC title

• B64D45/04

  Landing aids; Safety measures to prevent collision with earth's surface · CPC title

• G01C5/005 Primary

  altimeters for aircraft (G01C5/02, G01C5/06 take precedence) · CPC title

• G01S17/933

  of aircraft or spacecraft · CPC title

• G01S15/93

  for anti-collision purposes · CPC title