Abstract
The paper deals with mathematical modeling of a small turbojet iSTC-21v with variable exhaust nozzle. We evaluate and measure the appropriate parameters that describe the engine modes during changes of the exhaust nozzle diameter. The article describes methods of experimental identification (the method of successive integration and the approximation of characteristic response) applied on a system with two inputs and two outputs. For the purpose of mathematical modeling, as well as for models evaluation, real data obtained from a small turbojet engine measurement are used.
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