METHOD TO CALCULATE SIDESLIP ANGLE AND CORRECT STATIC PRESSURE FOR SIDESLIP EFFECTS USING INERTIAL INFORMATION

摘要

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.