초록 ▼

A method and a device for estimating on an aircraft at least one wind characteristic. The device (1) comprises means (7) for determining a corrective term being representative of an apparent wind created upon a rotation of the aircraft and means (4) for determining the wind characteristic taking int

A method and a device for estimating on an aircraft at least one wind characteristic. The device (1) comprises means (7) for determining a corrective term being representative of an apparent wind created upon a rotation of the aircraft and means (4) for determining the wind characteristic taking into account such a corrective term.

대표청구항 ▼

1. A method for automatically estimating aboard an aircraft (AC) at least one wind characteristic existing outside said aircraft (AC), such a method wherein, upon said aircraft (AC) flying, the following automated operations are performed via a processor: a) a first piece of speed information is rec

1. A method for automatically estimating aboard an aircraft (AC) at least one wind characteristic existing outside said aircraft (AC), such a method wherein, upon said aircraft (AC) flying, the following automated operations are performed via a processor: a) a first piece of speed information is received relating to the speed of the aircraft (AC) in a terrestrial reference system, being expressed in a first point (G) of the aircraft (AC);b) a second piece of speed information ({right arrow over (Vair)}) is received relating to the speed of the aircraft (AC) in the air, being expressed in a second point (A) of the aircraft; andc) from at least said first and second speed information, said wind characteristic is determined in said terrestrial reference system, such a wind characteristic being determined taking into account a corrective term being representative of an apparent wind,wherein said corrective term TC is calculated using the following expression: TC={right arrow over (Ω)}^{right arrow over (GA)}wherein in step c), there is calculated, as a wind characteristic, a speed vector {right arrow over (Vv)} of said wind, using the following expression: {right arrow over (Vv)}={right arrow over (Vgs)}−{right arrow over (Vair)}+{right arrow over (Ω)}^{right arrow over (GA)}wherein:{right arrow over (Vgs)} represents said first piece of speed information;{right arrow over (Vair)} represents said second piece of speed information;^ represents the vector product;{right arrow over (Ω)} represents the rotation rate of the aircraft (AC) in an inertial reference system;G represents a reference point of the aircraft (AC), corresponding to said first point; andA represents the position on the aircraft (AC) of at least one anemometric probe, the measurements thereof being used for determining said second piece of speed information, such a position A corresponding to said second point. 2. A method for automatically generating aboard an aircraft (AC) at least one wind characteristic existing outside said aircraft (AC), wherein, upon said aircraft (AC) flying, the following automated operations are performed via a processor:a) a first piece of speed information is determined on the aircraft (AC);b) a second piece of speed information {right arrow over (Vair)} is determined on the aircraft (AC); andc) from at least said first and second speed information, said wind characteristic is determined in said terrestrial reference system, such a wind characteristic being determined taking into account a corrective term being representative of an apparent wind,wherein said corrective term TC is calculated using the following expression: TC={right arrow over (Ω)}^{right arrow over (GA)}where in step c), there is calculated, as a wind characteristic, a speed vector {right arrow over (Vv)} of said wind, using the following expression: {right arrow over (Vv)}={right arrow over (Vgs)}−{right arrow over (Vair)}+{right arrow over (Ω)}^{right arrow over (GA)}wherein:{right arrow over (Vgs)} represents said first piece of speed information;{right arrow over (Vair)} represents said second piece of speed information;^ represents the vector product;{right arrow over (Ω)} represents the rotation rate of the aircraft (AC) in an inertial reference system;G represents a reference point of the aircraft (AC), corresponding to said first point; andA represents the position on the aircraft (AC) of at least one anemometric probe, the measurements thereof being used for determining said second piece of speed information, such a position A corresponding to said second point. 3. A device for automatically estimating aboard an aircraft (AC) at least one wind characteristic existing outside said aircraft (AC), said device (1) being aboard the aircraft (AC) and comprising: a first receiver configured to receive a first piece of speed information relating to the speed of the aircraft (AC) in a terrestrial reference system, being expressed in a first point (G) of the aircraft (AC);a second receiver configured to receive a second piece of speed information ({right arrow over (Vair)}) relating to the speed of the aircraft (AC) in the air, being expressed in a second point (A) of the aircraft (AC);an auxiliary processor configured to calculate a corrective term being representative of an apparent wind; anda wind characteristic processor configured to determine, at least from said first and second speed information, said wind characteristic in the terrestrial reference system, said wind characteristic processor being formed so as to determine said wind characteristic taking into account said corrective term,wherein said auxiliary processor comprises elements for calculating said corrective term TC using the following expression: TC={right arrow over (Ω)}^{right arrow over (GA)}wherein said wind characteristic processor comprises elements for calculating, as a wind characteristic, a speed vector {right arrow over (Vv)} of said wind, using the following expression: {right arrow over (Vv)}={right arrow over (Vgs)}−{right arrow over (Vair)}+{right arrow over (Ω)}^{right arrow over (GA)}wherein:{right arrow over (Vgs)} represents said first piece of speed information;{right arrow over (Vair)} represents said second piece of speed information;^ represents the vector product;{right arrow over (Ω)} represents the rotation rate of the aircraft (AC) in an inertial reference system;G represents a reference point of the aircraft (AC), corresponding to said first point; andA represents the position on the aircraft (AC) of at least one anemometric probe, the measurements thereof being used for determining said second piece of speed information, such a position A corresponding to said second point. 4. A system for automatically generating aboard an aircraft (AC) at least one wind characteristic existing outside said aircraft (AC), wherein it is located aboard the aircraft (A) and comprises: means (13) for generating a first piece of speed information;means (11) for generating a second piece of speed information; anda device (1) according to claim 3, for estimating said wind characteristic based on said first and second speed information. 5. A system according to claim 4, it further comprising a display adapted to show to a crew member of the aircraft (AC) the wind characteristic having been estimated by said device (1). 6. An aircraft, comprising a device (1) according to claim 3. 7. An aircraft, comprising a system (10) according to claim 4. 8. A system for automatically generating aboard an aircraft (AC) at least one wind characteristic existing outside said aircraft (AC), wherein it is located aboard the aircraft (A) and comprises: a first plurality of sensors adapted to generate a first piece of speed information;a second plurality of sensors to generate a second piece of speed information; anda device (1) according to claim 3, for estimating said wind characteristic based on said first and second speed information. 9. The system of claim 8, wherein the first plurality of sensors comprises at least one anemometric sensor. 10. The system of claim 8, wherein the second plurality of sensors comprises at least on inertia sensor. 11. The system of claim 8, wherein the second plurality of sensors comprises a satellite positioning system.