The paper presents algorithms of automatic control of an intelligent anti-tank guided missile (ATGM) with possibility of attacking the target from the upper ceiling and with possibility of the missile flight through indicated points in space. The polynomial functions are used to designate the program trajectories. Numerical analysis of the operation of chosen algorithms is performed. The results are presented in a graphical form. As it results from the conducted tests, the proposed algorithms of automatic control of ATGM with the use of polynomial functions work properly during attack on the target from the upper ceiling, for both mobile and immobile targets.

The paper concerns the issue of optimum control of the strongly non-linear dynamic system, i.e. Anti-Tank Guided Missile (ATGM). The linear-quadratic regulator (LQR) was used to provide control capabilities. In order to use the classic LQR, the dynamics of the object must be presented in the form of a linear-stationary model. This is not possible in the case of the considered missile, mostly due to mass changing in time (intensive consumption of fuel) and varying aerodynamic conditions depending on the Mach number Ma. Thus, we are dealing with a non-stationary system. Moreover, state variables are frequently involved in complex functions, which do not allow one to separate coefficients related to state variables very easily. In order to linearize such a complex system, the paper uses Jacobian, as the matrix of state, calculated at each time instant. The automatic pilot of the ATGM, using the LQR method, determines the signals controlling the angles of flight control surfaces and the thrust vector using continuously calculated Jacobians. The paper presents the algorithm for the ATGM control.

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The paper presents algorithms of automatic control of an intelligent anti-tank guided missile with the possibility of attacking a target from the upper ceiling (top attack). Polynomial functions have been used to determine program trajectories. The numerical analysis of chosen algorithms has been performed. The results of work are presented in a graphical form. It appears from the conducted research that the proposed algorithms of automatic control of the anti-tank guided missile work correctly during attack from the upper ceiling, both movable and fixed.

This work presents an analysis of guiding an anti-tank missile (ATGM) onto a ground-based target. The concept presented here is the feasibility of bypassing obstacles in the path of an ATGM when the obstacle coordinates are known prior to firing the ATGM weapon. The ATGM contemplated here uses a homing algorithm to calculate the stages of the ATGM flight path with the use of polynomial curves (including third-degree polynomial curves). The start and end coordinates of the polynomial curves are determined by the position of the obstacle(s) along the flight path. A method is presented for calculating the factors of subsequent flight path stages, along with a method of equating the ATGM kinematics and dynamics. A comparison is made between the operating efficiency of various configurations of a traditional proportional integral derivative (PID) controller, and at various gain factor values of the PID controller stages. The applied mathematical model of the ATGM are used in a series of numerical simulations for different take-off and in-flight conditions of the projectile. The simulation results are presented in a graphical form.