Method of Guidance for Aircraft Trajectory Correction
First Claim
1. A guidance method of an aircraft for correcting a trajectory deviation due to the presence of wind, comprising a step of computing a roll command of the aircraft during a phase of alignment of the trajectory of the aircraft according to an imposed direction of alignment passing through a determined point, on the basis:
- of a current angular divergence between a straight line passing through the said determined point and the aircraft on the one hand and the said direction of alignment on the other hand, andof a current estimated ground speed of the aircraft with respect to a frame of reference tied to the ground,said current estimated ground speed being computed on the basis of a current air speed of the aircraft with respect to the surrounding air and of a stored wind speed,said stored wind speed being obtained on the basis of at least one wind speed computed on the basis;
of a first value of a first speed equal to the speed of the said aircraft with respect to a frame of reference tied to the ground originating from a satellite navigation system, andof a second value of a second speed equal to the said air speed with respect to the surrounding air,said first value and second value being taken into account simultaneously at at least one instant earlier than or equal to the instant at which the aircraft starts the said alignment phase.
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Accused Products
Abstract
Guidance for an aircraft correcting a trajectory deviation due to wind computes a roll command during trajectory alignment according to imposed alignment passing through a determined point, via a current angular divergence between a line through the point and aircraft and direction of alignment and of a current estimated ground speed of the aircraft with respect to a frame of reference. The current estimated ground speed is computed via a current air speed and stored wind speed. The stored wind speed is obtained via at least one wind speed computed via a first value of a first speed equal to the speed of the said aircraft with respect to a frame of reference originating from a satellite navigation system and a second value of a second speed equal to the air speed. The first and second value are simultaneously accounted earlier than or at the instant at the alignment phase.
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Citations
13 Claims
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1. A guidance method of an aircraft for correcting a trajectory deviation due to the presence of wind, comprising a step of computing a roll command of the aircraft during a phase of alignment of the trajectory of the aircraft according to an imposed direction of alignment passing through a determined point, on the basis:
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of a current angular divergence between a straight line passing through the said determined point and the aircraft on the one hand and the said direction of alignment on the other hand, and of a current estimated ground speed of the aircraft with respect to a frame of reference tied to the ground, said current estimated ground speed being computed on the basis of a current air speed of the aircraft with respect to the surrounding air and of a stored wind speed, said stored wind speed being obtained on the basis of at least one wind speed computed on the basis; of a first value of a first speed equal to the speed of the said aircraft with respect to a frame of reference tied to the ground originating from a satellite navigation system, and of a second value of a second speed equal to the said air speed with respect to the surrounding air, said first value and second value being taken into account simultaneously at at least one instant earlier than or equal to the instant at which the aircraft starts the said alignment phase. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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13. A system for the guidance of an aircraft able to correct a trajectory deviation due to the presence of wind comprising:
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a computation module for computing a roll command for the aircraft during a phase of alignment of the trajectory of the aircraft according to an imposed direction of alignment passing through a determined point, on the basis; of a current angular divergence between a straight line passing through the said determined point and the aircraft on the one hand and the said direction of alignment on the other hand, and of a current estimated ground speed of the aircraft with respect to a frame of reference tied to the ground, a computation module for computing the said current estimated ground speed of the aircraft on the basis of a current air speed of the aircraft with respect to the surrounding air and of a stored wind speed, a computation module for computing the said stored wind speed on the basis; of a first value of a first speed equal to the speed with respect to a frame of reference tied to the ground of the said aircraft originating from a satellite navigation system, and of a second value of a second speed equal to the said air speed with respect to the surrounding air, the said first value and second value being taken into account simultaneously at at least one instant earlier than or equal to the instant at which the aircraft starts the said alignment phase.
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Specification