Method and device for preventing an anti-collision system on board an airplane from emitting alarms, during an altitude capture maneuver

• US 8,477,048 B2
• Filed: 01/28/2011
• Issued: 07/02/2013
• Est. Priority Date: 02/02/2010
• Status: Active Grant

• Current Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Original Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Inventors: Botargues, Paule, Sapin, Olivier, Bompart, Vincent, Dal Santo, Xavier
• Primary Examiner(s): Wu, Daniel
• Assistant Examiner(s): LITTLEJOHN JR, MANCIL H
• Application Number:
  US13/016,154
• Publication Number:
  US 20110187561A1
• Time in Patent Office: 886 Days
• Field of Search: 340/970, 340/961, 340/976, 340/977, 340/468, 340/463, 340/471, 340/469, 701/4, 701/5, 701/18, 701/123, 701/121, 701/301, 701/23, 701/24, 701/408, 342/29, 342/30, 342/36, 342/455
• US Class Current: 340/961
• CPC Class Codes: G01S 13/933 of aircraft or spacecraft
• CPC Class Codes: G08G 5/04 Anti-collision systems
• CPC Class Codes: G08G 5/045 Navigation or guidance aids, e.g. determination of anti-collision manoeuvers radar or analogous systems specially adapted for anti-collision between aircraft G01S13/933

Abstract

According to the invention, the device (1) comprises means (3) for detecting, during an altitude capture maneuver, the emission of a first type alarm by the anti-collision system (2) and means (4) for controlling the vertical speed of said airplane (AC), after the emission of such an alarm, until the triggering of the capture phase.

Claims

1. A method for preventing at least some alarms from being emitted by an anti-collision system (2) on board an airplane (AC) during an altitude change maneuver comprising an approach phase followed by a phase for capturing a set level (Zc), said anti-collision system (2) being able to detect at least one intrusive aircraft (AI) being located in the air environment of said airplane (AC), to calculate a theoretical collision time between said airplane (AC) and said intrusive aircraft (AI) and to emit first type alarms (TA) and second type alarms, when such a theoretical collision time is lower respectively than a first predetermined triggering threshold and a second predetermined triggering threshold,

characterized in that, when said airplane (AC) is flying to said set level (Zc) with a vertical speed (Vz), the absolute value of which is at least equal to a first predetermined vertical speed threshold (Vz1), the following steps are carried out for preventing a second type alarm from being emitted:

the emission of a first type alarm (TA) is first detected;

in the case where said first type detected alarm (TA) occurs when the height (h) separating said airplane (AC) from said set level (Zc) is at the most equal to a predefined height threshold (ho), the vertical speed (Vz) of said airplane (AC) is reduced so that the absolute value thereof is equal to said first vertical speed threshold (Vz1), so as to maintain the theoretical collision time associated with a second type alarm above the second triggering threshold; and

in the case where said first type detected alarm (TA) occurs when the height (h) separating said airplane (AC) from said set level (Zc) is strictly higher than said height threshold (ho);

i) as long as the height (h) separating said airplane (AC) from said set level (Zc) remains strictly higher than said height threshold (ho), the vertical speed (Vz) of said airplane (AC) is reduced so that the absolute value thereof is equal to a second predetermined vertical speed threshold (Vz2); and

ii) then, when the height (h) separating said airplane (AC) of said set level (Zc) is at the most equal to said height threshold (ho), the vertical speed (Vz) of said airplane (AC) is limited so that the absolute value thereof is equal to said first vertical speed threshold (Vz1), until said capture phase is initiated, so as to maintain the theoretical collision time associated with a second type alarm above the second triggering threshold.

2. The method according to claim 1,

characterized in that said second vertical speed threshold (Vz2) depends on the height (h) separating the airplane (AC) from said set level (Zc) to be reached and on the vertical speed (Vz) of said airplane (AC), at the time of the emission of said first type alarm (TA).

3. The method according to claim 2,

characterized in that said second vertical speed threshold (Vz2) is determined by the linear interpolation of a predetermined set of values of vertical speed, each one of said values being associated to a couple of values comprising a height value separating said airplane (AC) from said set level (Zc) and a vertical speed value of said airplane (AC), at the time of the emission of a first type alarm (TA).

4. The method according to claim 1,

characterized in that, after a first type alarm (TA) has been emitted and detected when the height (h) separating said airplane (AC) from said set level (Zc) is strictly higher than said height threshold (ho) and the absolute value of the vertical speed (Vz) of said airplane (AC) is equal to said second speed threshold (Vz2), in the case where a new first type alarm (TA′

) is emitted for a height (h) of said airplane with respect to said set level (Zc) always strictly higher than said height threshold (ho), said vertical speed (Vz) of said airplane (AC) is again reduced so that the absolute value thereof is equal to a third speed threshold (Vz3).

5. The method according to claim 4,

characterized in that said third vertical speed threshold (Vz3) depends on the height (h) separating said airplane (AC) from said set level (Zc) and on the vertical speed (Vz) of said airplane (AC), at the time of the emission of the new first type alarm (TA′

).

6. The method according to claim 1,

characterized in that the speed values of said predetermined set are such that the reduction of the vertical speed (Vz) of said airplane (AC), in step i), results in a limited increase of the time necessary to said airplane (AC) to cause the height (h) separating it from said set level (Zc) to be at the most equal to said height threshold (ho), as from the emission of said first type alarm (TA).

7. The method according to claim 1,

characterized in that said capture phase is initiated when the height (h) separating said airplane (AC) from said set level (Zc) to be reached is at the most equal to a predetermined capture height (hc), defined by the following equation:

9. An airplane comprising the device (1) specified in claim 5.

8. A device for preventing at least some alarms from being emitted by an anti-collision system (2) on board an airplane (AC) during an altitude change maneuver comprising an approach phase followed by a phase for capturing a set level (Zc), said anti-collision system (2) being able to detect at least one intrusive aircraft (AI) being located in the air environment of said airplane (AC), to calculate a theoretical collision time between said airplane (AC) and said intrusive aircraft (AI) and to emit first type alarms (TA) and second type alarms, when such a theoretical collision time is lower respectively than a first predetermined triggering threshold and a second predetermined triggering threshold,

characterized in that said airplane (AC) flying to said set level (Zc) with a vertical speed (Vz), the absolute value of which is at least equal to a first predetermined threshold of vertical speed (Vz1), said device (1) comprises:

means (3) for detecting the emission of a first type alarm (TA) by the anti-collision system (2);

means (4) for controlling the vertical speed (Vz) of said airplane (AC) such as;

in the case where said first type detected alarm (TA) occurs when the height (h) separating said airplane (AC) from said set level (Zc) is at the most equal to a predefined height threshold (ho), the vertical speed (Vz) of said airplane (AC) is reduced so that the absolute value thereof is equal to said first vertical speed threshold (Vz1), so as to maintain said theoretical collision time associated with a second type alarm above the second triggering threshold; and

in the case where said first type detected alarm (TA) occurs when the height (h) separating said airplane (AC) from said set level (Zc) is strictly higher than said height threshold (ho);

as long as the height (h) separating said airplane (AC) from said set level (Zc) remains strictly higher than said height threshold (ho), the controlling means (4) reduce the vertical speed (Vz) of said airplane (AC) so that the absolute value thereof is equal to a second predetermined vertical speed threshold (Vz2); and

when the height (h) separating said airplane (AC) from said set level (Zc) is at the most equal to said height threshold (h), said controlling means (4) limit the vertical speed (Vz) of said airplane (AC) so that the absolute value thereof is equal to said first vertical speed threshold (Vz1), until said capture phase is initiated, so as to maintain said calculated collision time associated with a second type alarm above the second triggering threshold.