IMPROVEMENT OF THE ANTI-AIRCRAFT MISSILE SYSTEMS GUIDANCE ELECTRIC DRIVES STATE OBSERVER

The work substantiates the necessity of improving the adaptive state observer of the modern anti-aircraft missile systems guidance electric drives in order to ensure the efficiency of the electric drives when the executive motor is operating in the zone of speeds higher than the nominal one and to increase the overall speed of the guidance system. The structure of the well-known adaptive state observer of combat vehicles electric drives, developed on the basis of Luenberger observers, is considered. A study of the direct current motor D-135 parameters uncertainty influence on the operation of the specified state observer as part of the 9K35 anti-aircraft missile system guidance system was carried out by means of simulation in the Matlab/Simulink software environment. The results of the study showed that the guidance electric drive with the state observer of the known structure has good robustness indicators in relation to the deviations of the values of the active resistance of the armature winding and the armature inertia moment from the nominal values, the error of estimating the executive motor rotation velocity did not exceed 4%. At the same time, when the motor magnetic flux is weakened, which characterizes the transition of the electric drive to the zone of speeds higher than nominal one, the results of the study revealed the complete inoperability of the state observer proposed structure. To solve the identified problem, the synthesis and improvement of the known state observer structure was carried out by the modal method, taking into account the magnetization curve of the executive motor. Previously, the magnetization curve was linearized and presented in the form of a linear dependence of the EMF and moment coefficient on the excitation current of the executive motor. A numerical study of the operation of the improved state observer as part of the guidance system of the 9K35 anti-aircraft missile system was carried out using Matlab/Simulink. The simulation results proved the full functionality of the improved observer structure when the guidance electric drive is operating in both rotation velocity zones. Keywords: Luenberger observer, executive motor, guidance electric drive, anti-aircraft missile system.