Patent ID: 6568260
Filing Date: 2003-05-27
Classification: G01M,G01P

Abstract:
A measuring system for determining air data for an aircraft, having a measuring device for determining values for measured variables, and an evaluation unit associated with said measuring device, for determining the air data from the measured variables, wherein:the measuring device comprises a force measuring device, which is arranged between front and rear portions of a fuselage of the aircraft in a transverse measuring section extending at least partly around a circumference of the aircraft, and acquires measured variables that are indicative of a load gradient exerted within the aircraft fuselage, which load gradient is a function of a flow vector of an air flow impinging on the aircraft, and of the inertia forces, both of which act on the front fuselage portion of the air craft in relation to the rear fuselage portion; the measuring device further includes at least one acceleration transducer arranged in the aircraft, for determining inertia forces acting on a front fuselage portion of the aircraft; the evaluation unit includes a storage unit with stored calibration curves and a comparison unit which compares at least one calibration curve with a measurement curve determined from the measured variables acquired, so as to select that calibration curve which is most similar to the measurement curve, for determining said air data.