| 摘要 |
<p>A method of the invention allows the determination of aircraft sideslip using an air data probe and an inertial reference unit. A lateral sideslip component beta L of the aircraft is calculated as a function of inertial flight information. An angular sideslip component beta A of the aircraft is also calculated as a function of inertial flight information. The lateral sideslip component beta L and the angular sideslip component beta A are combined to obtain a total sideslip angle beta TOTAL for the aircraft. The total sideslip angle beta TOTAL can be used to compensate static pressure, angle of attack and other aircraft parameters for sideslip effects. <IMAGE></p> |
