SINS and Aiming-Line Error Model for a Small Tactical Missile

In order to study the error characteristics of a small tactical missile with strapdown inertial navigation system(SINS), the mathematical platform drift model, the acceleration error model and the aiming-line error model are set up and analyzed, using the coordinate transformation and similar transformation principle, based on the mathematical model of initial alignments. The models are verified and validated through digital simulation experiments, and allowable sensors precision is shown.