IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0622877
(2009-11-20)
|
등록번호 |
US7999926
(2011-08-03)
|
우선권정보 |
FR-2008-8 06587(2008-11-24) |
발명자
/ 주소 |
- Perrie, Jean-Damien
- Preaux, Guillaume
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
5 |
초록
▼
A method and device for determining anemometric parameters of an aircraft. The device (1) comprises four laser anemometers (A1, A2, A3, A4) that are mounted in pairs (CA, CB) symmetrically on the aircraft and means (4, 5) for determining the angle of sideslip and the angle of incidence of the aircra
A method and device for determining anemometric parameters of an aircraft. The device (1) comprises four laser anemometers (A1, A2, A3, A4) that are mounted in pairs (CA, CB) symmetrically on the aircraft and means (4, 5) for determining the angle of sideslip and the angle of incidence of the aircraft, using measurements taken by these laser anemometers (A1, A2, A3, A4).
대표청구항
▼
The invention claimed is: 1. A method of determining anemometric parameters of an aircraft (A), said method using at least one laser anemometer (A1 to A4) that is capable of measuring the wind speed along a laser axis (L1 to L4), in which four laser anemometers (A1 to A4) are mounted in pairs (CA, C
The invention claimed is: 1. A method of determining anemometric parameters of an aircraft (A), said method using at least one laser anemometer (A1 to A4) that is capable of measuring the wind speed along a laser axis (L1 to L4), in which four laser anemometers (A1 to A4) are mounted in pairs (CA, CB) on the aircraft (A), said pairs (CA, CB) being mounted symmetrically relative to a vertical plane (P0) 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 (A1 to A4), a wind measurement is taken, each of said measurements representing the projection (V1 to V4) of the wind speed vector on the corresponding laser axis (L1 to L4);for each pair (CA, CB) of laser anemometers, the two measurements (V1, V2; V3, V4) 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 (PA0, PB0) 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); andusing 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.
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