METHOD AND DEVICE FOR AUTOMATIC PROTECTION OF AN AIRCRAFT AGAINST A RISK OF COLLISION WITH THE GROUND

• US 20160070263A1
• Filed: 09/03/2015
• Published: 03/10/2016
• Est. Priority Date: 09/08/2014
• Status: Active Grant

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Inventors: Fabre, Pierre
• Granted Patent: US 9,617,012 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 45/04 Landing aids; Safety measures to prevent collision with earth's surface
• CPC Class Codes: G01C 5/005 altimeters for aircraft G01C5/02, G01C5/06 take precedence
• CPC Class Codes: G05D 1/0676 specially adapted for landing

Abstract

A protection device including a unit for implementing a protection function that prevents the aircraft from flying under a given height with respect to the ground. The device includes a unit for determining the current values of parameters, and at least the current position of the aircraft and a current heading deviation of the aircraft with respect to a landing strip. A calculation unit is provided for calculating, during a landing on the landing strip, from data including said current values, a current longitudinal distance defined in the horizontal plane and necessary for bringing the aircraft into a position for deactivating the protection function. A checking unit is provided for checking whether a condition dependent on the current longitudinal distance is met, the protection function being automatically deactivated if the checking unit concludes that this condition is met.

Claims

1. A method of automatic protection of an aircraft against a risk of collision with the ground, comprising the steps:

implementing on the aircraft at least one protection function, said protection function preventing the aircraft from flying under a given height with respect to the ground, said protection function being capable of being activated and deactivated,

automatically and repetitively, during a landing on a landing strip (10), at least when the protection function is activated, performing the following successive steps;

determining a plurality of data including the current values of parameters related to the flight of the aircraft, namely at least the current position of the aircraft and a current heading deviation of the aircraft with respect to the landing strip, as well as at least one target point;

calculating, from some of these data, a current longitudinal distance, this current longitudinal distance being defined in the horizontal plane and being necessary and sufficient for bringing the aircraft into a position for deactivating the protection function; and

checking whether at least the following first condition is met;

XAC+D4·

sign(cos(Δ

χ

))XTGT

in which;

XAC illustrates a longitudinal coordinate of the current position of the aircraft, this longitudinal coordinate having a negative value and being defined along a longitudinal axis of the landing strip in the horizontal plane, with respect to a reference point;

sign represents the sign;

D4 is the current longitudinal distance,

Δ

χ

is the current heading deviation of the aircraft with respect to the landing strip; and

XTGT is a longitudinal coordinate of a target position dependent on said target point,

said method including an additional step comprising deactivating the protection function if at least said first condition is met.

2. The method as claimed in claim 1, wherein the step of checking also comprises checking whether the following second condition is met:

XACX2

in which X2 represents a maximum value of a target point,

the protection function being deactivated as soon as said first and second conditions are simultaneously met.

3. The method as claimed in claim 1, wherein the step of calculating includes the substeps comprising:

calculating a first distance D1 defined in the horizontal plane along the longitudinal axis of the landing strip and representing a minimum distance for which the protection function must be deactivated for an aligned flight;

calculating a second distance D2 defined in the horizontal plane along the longitudinal axis of the landing strip and representing a distance required for the aircraft for directing its flight path toward the target point, from its current position and the current heading deviation;

calculating a third distance D3 defined in the horizontal plane along the longitudinal axis of the landing strip and representing a distance required for the aircraft to be aligned in the axis of the landing strip with a close margin; and

calculating the current longitudinal distance D4 from these first, second and third distances, using the following expression, in which max represents the maximum value;

D4=max[0;

D1−

(D2+D3)].

4. The method as claimed in claim 3, wherein the substep of calculating the first distance comprises calculating the first distance D1 using the following expression:

D1=(k1·

Z0−

k2)·

k3

in which;

k1 is a predetermined margin;

k2 and k3 are predetermined parameters; and

Z0 is a lowest height at which the aircraft can fly if the protection function is engaged.

5. The method as claimed claim 3, wherein the substep of calculating the second distance comprises calculating the second distance D2 using the following expression:

D2=V²/(g·

tg(φ

0))·

|sin(Δ

χ

)−

sin(Δ

χ

1)|

in which;

V is the speed of the aircraft (AC);

g is the acceleration of gravity;

tg is the tangent and sin the sine;

φ

0 is a maximum bank angle of the aircraft;

Δ

χ

is the current heading deviation of the aircraft with respect to the landing strip; and

Δ

χ

1 is a heading deviation between the landing strip and a straight line passing through the current position of the aircraft and the target position.

6. The method as claimed in claim 3, wherein the substep of calculating the third distance comprises calculating the third distance D3 using the following expression:

D3=max[0;

V²/(g·

tg(φ

0))·

(sin(|Δ

χ

1|)−

sin(Δ

χ

0))]

in which;

V is the speed of the aircraft;

g is the acceleration of gravity;

tg is the tangent and sin the sine;

φ

0 is a maximum bank angle of the aircraft;

Δ

χ

1 is a heading deviation between the landing strip and a straight line passing through the current position of the aircraft and the target position; and

Δ

χ

0 is a maximum heading deviation with respect to the landing strip for being able to perform a safe landing.

7. The method as claimed in claim 5, wherein the heading deviation Δ

χ

1 between the landing strip and the straight line passing through the current position of the aircraft and the target position, is calculated using the following expressions;

Δ

χ

1=arc tg(YAC/(XTGT−

XAC)) if (XTGT−

XAC)0;

Δ

χ

1=180+arc tg(YAC/(XTGT−

XAC)) if (XTGT−

XAC)0 and YAC0;

Δ

χ

1=−

180+arc tg(YAC/(XTGT−

XAC)) if (XTGT−

XAC)0 and YAC0

in which;

arc tg is the arc tangent; and

YAC illustrates a lateral coordinate of the current position of the aircraft in the horizontal plane.

8. The method as claimed in claim 1, further comprising an additional step comprising calculating the longitudinal coordinate XTGT of the target position so that:

this longitudinal coordinate XTGT of the target position is initially equal to the longitudinal coordinate X1 of the target point, as long as the longitudinal coordinate X1 of the target point remains greater than the sum of the longitudinal coordinate XAC of the current position of the aircraft and a predetermined minimum distance X min;

then, the longitudinal coordinate XTGT of the target position is equal to the sum of the longitudinal coordinate XAC of the current position of the aircraft and the minimum distance X min, as long as this longitudinal coordinate XTGT remains less than a predetermined maximum longitudinal coordinate X2.

9. A device for automatic protection of an aircraft against a risk of collision with the ground, said device comprising:

at least one main unit configured for implementing on the aircraft at least one protection function that prevents the aircraft from flying under a given height with respect to the ground, said main unit including an activation/deactivation element capable of activating and deactivating said protection function,

a data generation unit configured for determining the current values of parameters related to the flight of the aircraft, namely at least the current position of the aircraft and a current heading deviation of the aircraft with respect to a landing strip;

a calculation unit configured for calculating, during a landing on the landing strip, from data including said current values and at least one target point, a current longitudinal distance defined in the horizontal plane and necessary for bringing the aircraft into a position for deactivating the protection function; and

a checking unit configured for checking whether at least the following first condition is met;

XAC+D4·

sign(cos(Δ

χ

))XTGT

in which;

XAC illustrates a longitudinal coordinate of the current position of the aircraft, this longitudinal coordinate having a negative value and being defined along the longitudinal axis of the landing strip in the horizontal plane, with respect to a reference point;

sign represents the sign;

D4 is the current longitudinal distance;

Δ

χ

is the current heading deviation with respect to the landing strip; and

XTGT is a longitudinal coordinate of a target position dependent on said target point,

the activation/deactivation element being configured for deactivating said protection function if the checking unit concludes that at least said first condition is met.

10. An aircraft comprising a device for automatic protection of an aircraft against a risk of collision with the ground, said device comprising:

at least one main unit configured for implementing on the aircraft at least one protection function that prevents the aircraft from flying under a given height with respect to the ground, said main unit including an activation/deactivation element capable of activating and deactivating said protection function,

a data generation unit configured for determining the current values of parameters related to the flight of the aircraft, namely at least the current position of the aircraft and a current heading deviation of the aircraft with respect to a landing strip;

a calculation unit configured for calculating, during a landing on the landing strip, from data including said current values and at least one target point, a current longitudinal distance defined in the horizontal plane and necessary for bringing the aircraft into a position for deactivating the protection function; and

a checking unit configured for checking whether at least the following first condition is met;

XAC+D4·

sign(cos(Δ

χ

))XTGT

in which;

XAC illustrates a longitudinal coordinate of the current position of the aircraft, this longitudinal coordinate having a negative value and being defined along the longitudinal axis of the landing strip in the horizontal plane, with respect to a reference point;

sign represents the sign;

D4 is the current longitudinal distance;

Δ

χ

is the current heading deviation with respect to the landing strip; and

XTGT is a longitudinal coordinate of a target position dependent on said target point,

the activation/deactivation element being configured for deactivating said protection function if the checking unit concludes that at least said first condition is met.