A nonlinear missile guidance controller with pulse type input devices

Presents a nonlinear missile guidance controller with pulse type control inputs for the interception of a theater ballistic missile in the exoatmosphere region. A 3D terminal guidance law is designed to eliminate the "sliding velocity" such that the relative motion between the missile and the target is restricted along the LOS. To enhance the performance of the missile guidance, a quaternion-based attitude controller is proposed. Sliding mode control and nonlinear system analysis theory are employed to design a stable pulse type control system.