Abstract. An indirect method of aircraft aerodynamic angles measuring with accelerometers and pressure sensors is presented. The peculiarity of the method is the application of measured flight parameters and structural characteristics of the aircraft to formulate equations for derivation of current values of attack and slip angles. Aircraft aerodynamic characteristics and calibration motor characteristics are used as design data. Equation of forces is formulated in the related coordinate system with subsequent projec-tion on the speed coordinate system. Solution to the nonlinear equation for attack angle is obtained using the chord method for calculation of approximate root to the equation with high precision sufficient for practical application. Slide angle is found from a linear equation solution. Simulation of three flight phases is performed and the iteration procedures of equation root evaluation are illustrated for takeoff climb, glideslope descent, and horizontal turn with the roll of 30 degrees.

Keywords: attack angle, sideslip angle, measuring, accelerometer, pressure sensor, modeling

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