Improvement of quadrocopter command performance system

Abstract

It is considered the problem of quadrocopter flight control. A system with four degrees of freedom is used as a model of the control object. Phase states of this system are acceleration along the vertical axis and Euler angles angular rate. Copter's cxecutive system is improved by the addition of a filter. The step response of the system with filter is presented. Quality performance management system with simple PI regulator and with designed dynamic filter is demonstrated.