Method and device for the filtering of alerts originating from a collision detection system of an aircraft
First Claim
1. A method for filtering alerts originating from a ground collision detection system, embedded aboard an aircraft, during a landing runway approach phase, said aircraft flying according to a speed vector (V), said landing runway comprising a runway threshold (G), the method comprising the following steps:
- determination of an angle of descent (α
) defined on a basis of approach procedures predefined for said landing runway by a filtering device,measurement of an altitude (H) of the aircraft with respect to the landing runway using an altimeter,determination of a factor (k) defined on a basis of said angle of descent (α
), of the measured altitude (H) of the aircraft with respect to the landing runway and of the distance x on the ground between the aircraft and the runway threshold (G) by the filtering device,determination of a first threshold (S1) by the filtering device on a basis of an angle of approach (FPA) of the aircraft, the angle of approach (FPA) of the aircraft being the angle between the speed vector (V) of the aircraft and a horizontal line, anddisabling of the ground alert of the ground collision detection system using the filtering device if the factor (k) is positive and is less than the first determined threshold (S1) and if the angle of approach (FPA) of the aircraft is less than a predetermined second threshold (FPAmax),whereby false alerts during a landing runway approach phase are avoided.
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Abstract
A method and a device for the filtering of alerts originating from a collision detection system of an aircraft makes it possible, by proposing a novel condition for alert disabling, to avoid an abnormal drop of an aircraft in the case of a CFIT (controlled flight into terrain) by authorizing the output of the alert when this novel condition is not complied with. This novel condition relies on a method for thresholding the angle of approach of the aircraft (FPA for flight path angle) as a function of the altitude of the aircraft with respect to the runway and of the angle of approach specified for each runway and which is recovered via the terrain database.
31 Citations
15 Claims
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1. A method for filtering alerts originating from a ground collision detection system, embedded aboard an aircraft, during a landing runway approach phase, said aircraft flying according to a speed vector (V), said landing runway comprising a runway threshold (G), the method comprising the following steps:
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determination of an angle of descent (α
) defined on a basis of approach procedures predefined for said landing runway by a filtering device,measurement of an altitude (H) of the aircraft with respect to the landing runway using an altimeter, determination of a factor (k) defined on a basis of said angle of descent (α
), of the measured altitude (H) of the aircraft with respect to the landing runway and of the distance x on the ground between the aircraft and the runway threshold (G) by the filtering device,determination of a first threshold (S1) by the filtering device on a basis of an angle of approach (FPA) of the aircraft, the angle of approach (FPA) of the aircraft being the angle between the speed vector (V) of the aircraft and a horizontal line, and disabling of the ground alert of the ground collision detection system using the filtering device if the factor (k) is positive and is less than the first determined threshold (S1) and if the angle of approach (FPA) of the aircraft is less than a predetermined second threshold (FPAmax), whereby false alerts during a landing runway approach phase are avoided. - View Dependent Claims (2, 3, 4, 5, 6)
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7. A device for filtering alerts originating from a ground collision detection system, embedded aboard an aircraft, during a landing runway approach phase, said aircraft flying according to a speed vector (V), said landing runway comprising a runway threshold (G), the device comprising:
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an altimeter for measuring an altitude (H) of the aircraft with respect to the landing runway, a computer configured to determine a factor k defined on a basis of said angle of descent (α
), of the measured altitude (H) of the aircraft with respect to the landing runway and of a distance (x) on the ground between the aircraft and the runway threshold (G),the computer further configured to determine a first threshold (S1) on a basis of an angle of approach (FPA) of the aircraft, the angle of approach (FPA) of the aircraft being the angle between the speed vector (V) of the aircraft and a horizontal line, and the computer further configured to disable the ground alert of the ground collision detection system if the factor k is positive and is less than the first determined threshold (S1) and if said angle of approach (FPA) of the aircraft is less than a predetermined second threshold (FPAmax). - View Dependent Claims (8, 9)
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10. A method of flying an aircraft during a landing runway approach phase, said landing runway comprising a runway threshold (G), the method comprising the following steps:
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flying said aircraft at a speed vector (V); using a filtering device for determining an angle of descent (a) defined on a basis of approach procedures predefined for said landing runway; using an altimeter for measuring an altitude (H) of the aircraft with respect to the landing runway; using said filtering device for determining a factor (k) defined on a basis of said angle of descent (α
), of the measured altitude (H) of the aircraft with respect to the landing runway and of the distance x on the ground between the aircraft and the runway threshold (G);using said filtering device for determining a first threshold (S1) on a basis of an angle of approach (FPA) of the aircraft, the angle of approach (FPA) of the aircraft being the angle between the speed vector (V) of the aircraft and a horizontal line; and disabling a ground alert of a ground collision detection system embedded aboard an aircraft using the filtering device if the factor (k) is positive and is less than the first determined threshold (S1) and if the angle of approach (FPA) of the aircraft is less than a predetermined second threshold (FPAmax). - View Dependent Claims (11, 12, 13, 14, 15)
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Specification