Exoatmospheric DACS Type Missile Controller Based on Sliding Mode Control Considering the Seeker’s Field-of-View Limit

Abstract

A sliding mode based controller for the divert and attitude control system (DACS) type exoatmospheric missile is designed considering the narrow field-of-view of the strapdown seeker. First, six-degrees-of-freedom equations of the DACS type exoatmospheric missile are derived. Considering the characteristics of the exoatmospheric missile that the translational motion is decoupled from the rotational motion, the controller with two-loop structure is designed to achieve two objectives: to generate the accelerations corresponding to the guidance command and to maintain the lock-on condition. An outer-loop controller generates the command inputs of the pitch and yaw angular rates to decrease the look angle, and an inner-loop controller generates the DACS inputs corresponding to the outer-loop inputs and guidance acceleration commands. To demonstrate the performance of the proposed controller, numerical simulation for the exoatmospheric target interception scenario is performed using three-dimensional pure proportional navigation guidance law.