| 摘要 |
Method of estimating the three components of the speed vector (TAS, AOA, SSA) of an aircraft relative to the surrounding air, in a reference frame tied to the aircraft, comprising: - a first step (1) consisting in estimating an estimated static pressure (PSe) on the basis of measurements of geographical altitude; - a second step (2) consisting in estimating a first intermediate variation of a linear combination of the three components of the speed vector of the aircraft relative to the surrounding air using explicitly the fact that the pressure measured by the static probe is falsified (by a known quantity) under the effect of the three components of this speed vector of the aircraft relative to the surrounding air; - a third step (3) consisting in estimating the three components of the speed vector of the aircraft relative to the air by likening the latter to the speed vector of the aircraft relative to an inertial reference frame and by using inertial measurements (accelerometers and gyrometers); and - a fourth step (4) and fifth step (5) consisting in fusing the estimation of the linear combination of the three components of the speed vector of the aircraft relative to the air obtained in the second step (2) and the estimation of the three components of the speed vector of the aircraft relative to the surrounding air obtained in the third step (3). |
