Method and device for determining anemometric parameters of an aircraft

1. A method of determining anemometric parameters of an aircraft (A), said method using at least one laser anemometer (A 1 to A 4 ) that is capable of measuring the wind speed along a laser axis (L 1 to L 4 ), in which four laser anemometers (A 1 to A 4 ) are mounted in pairs (CA, CB) on the aircraft (A), said pairs (CA, CB) being mounted symmetrically relative to a vertical plane (P 0 ) that corresponds to a plane passing through the longitudinal axis of the aircraft (A) and orthogonal to the general plane of the supporting surface ( 2 , 3 ) of said aircraft (A), and in which:

using each of said laser anemometers (A 1 to A 4 ), a wind measurement is taken, each of said measurements representing the projection (V 1 to V 4 ) of the wind speed vector on the corresponding laser axis (L 1 to L 4 );

for each pair (CA, CB) of laser anemometers, the two measurements (V 1 , V 2 ; V 3 , V 4 ) are projected onto an associated reference plane (PA, PB) and a speed vector (VA, VB) resulting from these two projections into this reference plane (PA, PB) is calculated, said reference plane (PA, PB) which is associated with a pair of laser anemometers (CA, CB) being a plane that is parallel to the plane (PA 0 , PB 0 ) tangential to the structure of the aircraft (A) at a reference point (RA, RB) that depends on the arrangement of the two laser anemometers of said pair (CA, CB) on the aircraft (A); and

using the two duly calculated speed vectors (VA, VB), and at least one reference table, the respective values of the angle of incidence and the angle of sideslip of the aircraft (A) are determined.

2. The method as claimed in claim 1 ,

in which, for a pair of laser anemometers, the corresponding laser axes (L 3 , L 4 ) emerge from one and the same point of the structure, and in which said reference point (RB) corresponds to this point of the structure.

3. The method as claimed in claim 1 ,

in which, for a pair of laser anemometers, the two corresponding laser axes (L 1 , L 2 ) emerge from two different points of the structure, and in which said reference point (RA) corresponds to the middle of these two points.

4. The method as claimed in claim 1 ,

in which the external temperature is determined, and in which the true speed of the aircraft (A) is calculated, using the duly determined external temperature and said two speed vectors.

5. A device for determining anemometric parameters of an aircraft, said device ( 1 ) comprising at least one laser anemometer (A 1 to A 4 ) that is capable of measuring the wind speed along a laser axis (L 1 to L 4 ), in which:

four laser anemometers (A 1 to A 4 ) that are arranged in pairs (CA, CB) on the aircraft (A), said pairs (CA, CB) being mounted symmetrically relative to a vertical plane (PA, PB) that corresponds to a plane passing through the longitudinal axis of the aircraft (A) and orthogonal to the general plane of the supporting surface ( 2 , 3 ) of said aircraft (A), each of said laser anemometers (A 1 to A 4 ) taking a measurement of the wind, which represents the projection (V 1 to V 4 ) of the wind speed vector on the corresponding laser axis (L 1 to L 4 ); and

first processing means ( 4 ) for projecting, for each pair (CA, CB) of laser anemometers, the two measurements (V 1 , V 2 ; V 3 , V 4 ) onto an associated reference plane (PA, PB) and for calculating a speed vector (VA, VB) resulting from these two projections into this reference plane (PA, PB), said reference plane (PA, PB) which is associated with a pair (CA, CB) of laser anemometers being a plane that is parallel to the plane (PA 0 , PB 0 ) tangential to the structure of the aircraft (A) at a reference point (RA, RB) that depends on the arrangement of the two laser anemometers of said pair (CA, CB) on the aircraft (A); and

second processing means ( 5 ) for using the two duly calculated speed vectors (VA, VB), and at least one reference table, to determine the respective values of the angle of incidence and of the angle of sideslip of the aircraft (A).

6. An aircraft,

comprises a device ( 1 ) as specified under claim 5 .