초록 ▼

The present invention relates to a method of decoupling the mode of automatic following of the lateral profile and the mode of automatic following of the vertical profile of an automatic guidance system of an aircraft (A) flying on a reference trajectory (T). The mode of automatic following of the v

The present invention relates to a method of decoupling the mode of automatic following of the lateral profile and the mode of automatic following of the vertical profile of an automatic guidance system of an aircraft (A) flying on a reference trajectory (T). The mode of automatic following of the vertical profile is not disengaged immediately on disengaging the mode of automatic following of the lateral profile. After disengaging the mode of automatic following of the lateral profile, the mode of automatic following of the vertical profile is disengaged automatically only if at least one criterion of lateral separation between the current or short-term position of the aircraft and the lateral profile corresponding to the reference trajectory is satisfied, having regard to the position error.

대표청구항 ▼

1. A method of controlling automatic following of a lateral profile and automatic following of a vertical profile of an automatic guidance system of an aircraft flying on a reference trajectory, comprising the steps of: disengaging automatic following of the lateral profile, while automatic followin

1. A method of controlling automatic following of a lateral profile and automatic following of a vertical profile of an automatic guidance system of an aircraft flying on a reference trajectory, comprising the steps of: disengaging automatic following of the lateral profile, while automatic following of the vertical profile remains engaged;estimating a projected lateral deviation distance of the aircraft from the lateral profile corresponding to the reference; andautomatically disengaging automatic following of the vertical profile if the projected lateral deviation distance plus an associated lateral position error is greater than a predetermined threshold;wherein estimating the projected lateral deviation distance comprises:when the aircraft is not in a turn, estimating the projected lateral deviation distance by a function comprising propagating a current position of the aircraft by a predetermined time period along a current heading of the aircraft;when the aircraft is in a turn that causes the aircraft to converge towards the reference trajectory, estimating the projected lateral deviation distance based on a maximum lateral deviation of the aircraft from the reference trajectory while in the turn; andwhen the aircraft is in a turn that causes the aircraft to diverge from the reference trajectory, estimating the-projected lateral deviation distance by a function comprising propagation of the turn over the predetermined time period from the current position of the aircraft. 2. The method as claimed in claim 1, wherein the step of calculating the lateral deviation distance further comprises the step of: estimating the position of the aircraft after the predetermined time period if, on starting from the current position, the aircraft maintains its speed or angle of roll substantially constant during the predetermined time period. 3. The method as claimed in claim 2, wherein the step of disengaging automatically the automatic following of the vertical profile occurs if: the aircraft is at a distance from the lateral profile corresponding to the reference trajectory that is greater than the predetermined threshold; orthe aircraft strays from the lateral profile corresponding to the reference trajectory so that after the predetermined time period the aircraft will be at a distance from the lateral profile corresponding to the reference trajectory that is greater than the predetermined threshold. 4. The method as claimed in claim 1, wherein the step of calculating the lateral deviation distance further comprises the step of: estimating a distance between the position of the aircraft after the predetermined time period and a point of the lateral profile, corresponding to the reference trajectory, situated at a same altitude. 5. A method of controlling automatic following of a lateral profile and automatic following of a vertical profile of an automatic guidance system of an aircraft flying on a reference trajectory, wherein the automatic following of the vertical profile is engaged automatically if: the mode of automatic following of the lateral profile is armed; anda criterion of lateral proximity between the aircraft and the lateral profile corresponding to the reference trajectory is satisfied, the criterion comprising at least one of the following:when the aircraft is converging towards the reference trajectory and a current deviation of a lateral position of the aircraft from the lateral profile, plus an associated lateral position error, is less than a predetermined threshold;when the aircraft is diverging from the reference trajectory: when the aircraft is not in a turn, a first projected lateral deviation distance computed according to a function comprising a current position of the aircraft propagated by the predetermined time period along a current heading of the aircraft, plus an associated lateral position error, is less than the predetermined threshold; andwhen the aircraft is in a turn that causes the aircraft to converge towards the reference trajectory, a second projected lateral deviation distance computed according to a function comprising a maximum lateral deviation of the aircraft from the reference trajectory while in the turn, plus an associated lateral position error, is less than the predetermined threshold. 6. The method as claimed in claim 5, wherein a distance by which the aircraft is liable to approach the lateral profile corresponding to the reference trajectory is calculated by a method comprising the step of: estimating the position of the aircraft after the predetermined time period if, on starting from the current position, the aircraft maintains its speed or angle of roll constant during the predetermined time period. 7. The method as claimed in claim 5, wherein a distance by which the aircraft is liable to approach the lateral profile corresponding to the reference trajectory is calculated by a method comprising the step of: estimating a distance between the position of the aircraft after the predetermined time period and the point of the lateral profile, corresponding to the reference trajectory, situated at the same altitude.