Journal of Theoretical
and Applied Mechanics

38, 1, pp. 157-165, Warsaw 2000

Identification of the aircraft control basing on the linear and angular accelerations recorded

Jarosław Pyrz, Jerzy Maryniak
A method for identification of the aircraft control based on the recorded linear and angular accelerations is presented in the paper. The aircraft accelerations have been calculated by means of numerical simulation of a flight for specified deflections of the control surfaces. These values have been also applied to reconstruction of the manual control. The computations were made for the I-22 IRYDA M93 aircraft.
Keywords: flight dynamics; flight control; flight simulation