A PN/SMC hybrid guidance law for missile with narrow field-of-view strapdown seeker

A hybrid guidance law based on both proportional navigation (PN) and sliding mode control (SMC) for missile with a strapdown narrow field-of-view (FOV) seeker is presented. The seeker FOV is an important limitation for guidance performance metrics when a strapdown seeker with a narrow FOV is used for tracking a target. A simplified strapdown guidance model is detailed. Then a hybrid guidance law included PN and SMC guidance laws is analyzed and formulated. Wherein, a first-order dynamic loop is used to represent the autopilot and remove the possible chattering phenomenon. The important guidance parameter of SMC guidance law is also analyzed. The trajectory simulation results validate the proposed hybrid guidance law.