SUMMARY
The problem of aircraft control is considered for certain class of situation, namely when aircraft enters GPS-denied zone with significant disturbances of different nature which may cause the constructive damage and the loss of control. The only source of information is from inertial navigation system that need to be aided by correlation extreme navigation system, for example. In the paper the control problem is solved by using particle filtering technique for correlation extreme navigation system which outputs form the control vector. Further the structural reconfiguration is done by redistributing control or changing the control law in order to create the necessary control forces and moments, maintain acceptable control quality and return for the desired track. The lack of reliable navigation information is compensated by correlation extreme navigation system working by terrain filed of the Earth to be included into control contour. The researches have been conducted by mathematical modeling of the developed algorithms in mathematical software package MATLAB using terrain field (the part of Carpathians territory). The results proved the high accuracy of navigation solution and stability of control estimated by error of closing loop.