Development of aircraft engines is aimed on increase of reliability, efficiency and ecology of operation. The presently still used hydro-mechanic control systems are being replaced by electronic ones characterized by high speed, precision of control and ability to optimize all operating regimes of an engine. One of the aims of research in the Laboratory of intelligent control systems of aircraft engines lies in new possibilities of expansion of working envelope of turbojet engines by implementation of variable exhaust geometry and new approaches in its control strategies and construction solutions. Such expansion can be beneficial for small turbojet engines and increase their possibilities of real-world applications. New control methodologies and approaches can be further expanded to normal sized engines. All these problems are described in the presented article.
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