Method and Device for the Filtering of Alerts Originating from a Collision Detection System of an Aircraft
First Claim
1. A method for the filtering of alerts originating from a terrain collision detection system embedded aboard an aircraft in a landing runway approach phase, said aircraft flying according to a speed vector (V), said landing runway comprising a runway threshold (G), comprising the following steps:
- determination of an angle of descent (α
) defined on the basis of approach procedures predefined for said landing runway,determination of a factor (k) defined on the basis of said angle of descent (α
), of the 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),determination of a first threshold (S1) on the basis of the 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 terrain alert, 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).
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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.
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Citations
9 Claims
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1. A method for the filtering of alerts originating from a terrain collision detection system embedded aboard an aircraft in a landing runway approach phase, said aircraft flying according to a speed vector (V), said landing runway comprising a runway threshold (G), comprising the following steps:
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determination of an angle of descent (α
) defined on the basis of approach procedures predefined for said landing runway,determination of a factor (k) defined on the basis of said angle of descent (α
), of the 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),determination of a first threshold (S1) on the basis of the 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 terrain alert, 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 (2, 3, 4, 5, 6)
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7. A device for the filtering of alerts originating from a terrain collision detection system embedded aboard an aircraft in a landing runway approach phase, said aircraft flying according to a speed vector (V), said landing runway comprising a runway threshold (G), comprising:
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means for determining an angle of descent a defined on the basis of approach procedures predefined for the said landing runway, means for determining a factor k defined on the basis of said angle of descent (α
), of the 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)means for determining a first threshold (S1) on the 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 means for disabling the terrain alert, 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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Specification