“…In this work, only the lateral/ directional motion control is considered. A state equation representing the dynamic motion of an aircraft is expressed as follows [57][58][59][60] where x = { , , , } , is the sideslip, a velocity in direction, is the yaw rate, rate of change of rotation about the -axis, is the roll rate, rate of change of rotation about the -axis, is the bank angle, rotation about the -axis, A is the kinetic energy matrix, B is Coriolis matrix, u = { } is the control vector, is the aileron deflection, and is the rudder deflection.…”