М. Кебир

In this article was developed a mathematical model of guidance process of an anti-ship missile (ASM), having a structure with two possible states which are defined by existence or absence of information about target. For creation of optimum guidance of ASM, it is necessary to go by the way of simplifications of initial differential equations system describing functioning of dynamic object, which allow decreasing its order. Further, to define the equations of the optimum linear filter and an optimum regulator than include them in initial system then include them in guidance law. The optimal filter work in two operation modes: the first is filtration regime when the information is available and the second is memory mode when the incoming information about target is interrupted.

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.