A position error control method based on dynamic inversion for formation flight

A position error control method for formation flight based on dynamic inversion is provided according to the position error between the wing plane and its correct position in formation. An implementing program of position control system based on dynamic inversion for formation flight is suggested. In order to evaluate the validity of the method, many cases are simulated that the wing plane follows the leader plane when the leader plane speed up, climb up and turn. The computer simulation results indicate that the position error can be reduced in an allowable range of formation flight by this control method, so the formation configuration can be kept.