The missile angular rate stabilization in the vertical plane by determining the optimal autopilot coefficients using the “Matlab” software

In this article, was proposed, a variant to choose the values of two parameters of the autopilot stabilization loop (i1, i2), for some fixed combat use conditions of the ASM, in order to improve the stabilization of the flight. A model of the pitch angle stabilization loop of the proposed missile is presented. Then we proceed to find its aerodynamic characteristics. Based on the optimization methods of the several variables functions and using the signal constraint block of the Simulink library, selection and optimization of the missile autopilot parameters ratios were made. Using the calculated optimal coefficients of the missile autopilot allow obtaining transient process of pitch angle with performed parameters missile flight stabilization.