Aircraft comprising measuring sensor, AND METHOD FOR DETERMINING THE PARAMETERS OF SUCH AIRCRAFT FLIGHT

摘要

1. An aircraft, comprising a fuselage (4) and the first measuring sensor (6A), comprising means (10A) for measuring the local angle of attack, means (8A) measuring the static pressure and, possibly, measuring means (12A) of total pressure, wherein that the fuselage (4) comprises at least a first zone (14) where the pressure ratio (edges) of the aircraft is a function of the local angle of attack (α, α, α), which is uniform at any value of the lateral drift (β) and the angle attack (α) of the aircraft, and in that the first measuring sensor (6A) is located in said first zone (14) .2. An aircraft according to Claim. 1, characterized in that it comprises a second measuring sensor (6B) comprising auxiliary measuring means (10B) of the local angle of attack, the auxiliary measuring means (8B) static pressure and possibly auxiliary measuring means (12B) of the total pressure .3. An aircraft according to claim. 2, characterized in that the second measuring sensor (6B) located on the fuselage in the second zone (16), symmetrical with the first zone (14) relative to the vertical plane of symmetry (P) of the aircraft (2) .4. An aircraft according to any one of the preceding claims, characterized in that the measuring means (8A, 8B) static pressure and measuring means (12A, 12B) of total pressure measurement sensor or each measuring sensor (6A, 6B) are fixed relative to the fuselage (4) of the aircraft apparatus (2) .5. An aircraft according to claim 1, characterized in that at least one measuring sensor (6A, 6B) has a pressure coefficient (Kps, Kps), corresponding to the ratio:. Where Kps - pressure ratio of said flowmeter sensor, and the edges - aircraft pressure coefficient apparata.6. FPIC