A METHOD FOR CONTROLLING THE WING DRIVING COMMAND IN A GUIDED MISSILE USING A TAIL WING

摘要

PURPOSE: A driving command control method of a guided missile using tail wing is provided to effectively restrict the driving command of a roll wing even if the driving command of a roll wing is generated due to the unstability of a roll control loop. CONSTITUTION: A driving command control method of a guided missile using tail wing comprises the following steps. In order that the guided missile is controlled in a space, a wing driving command value for each channel is generated in the controller designed according to the channel. The channel comprises first, second and third channels. The first channel is related to the stabilization control of the guided missile. The second and third channels are related to the position control or the acceleration control of the guided missile. The absolute value of the wing driving command value calculated in the first channel controller and the wing driving command threshold of the first channel are compared. The wing driving command value is divided through a distribution logic according to the tail.