FLIGHT TEST VALIDATION OF SIDESLIP ESTIMATION USING INERTIAL ACCELERATIONS

This paper demonstrates the feasibility of using INS derived accelerations to estimate the sideslip angle of aircraft. This is validation of earlier work [1], a paper proposing an avionics system architecture that, by sensing both the Ny and Nz acceleration components of the aircraft, can analytically derive both the angle-of-attack, a, and the sideslip angle, p, in the presence of gusts and turbulence. Results from U-2S aircraft flight test are used to show that the system will work for sideslip calculation.