Research into Nose Wheel Steering Deviation Angle Calculation of a Civil Aircraft

This document, based on a civil aircraft, describes the basic principle of nose wheel steering deviation angle calculation. The taxiing deviation angle of aircraft in ground test can be balanced by adjusting the nose wheel angle, but the deviation angle cannot be read directly, it needs to be calculated according to the field data. In this paper, we research a method to calculate the deviation angle by try three different modelling: simplified point modelling, calculus modelling and trigonometric modelling. Finally, we find the third modelling is more practical, we can rectified the deviation angle by adjusting the nose wheel turning control system pre-set parameters according with the result. We also transform the mathematic modelling into a computer program, to improve the efficiency in practical use.