Design of the variable exhaust nozzle control system for a small turbojet engine MPM-20

In order to achieve higher efficiency and to explore new progressive approaches in control of turbo-jet engines with more than one degree of freedom, the experimental turbojet engine MPM-20 has to be expanded with flexible geometry exhaust nozzle. The article is aimed at design of a mechanism, which would control the variable geometry exhaust nozzle of the engine allowing its practical application. Selection and precise analysis of the appropriate actuator for the needs of digital control of exhaust nozzle and design of the appropriate modifications for its practical use in laboratory conditions are presented. The presented design is usable for similar class of such engines in laboratory conditions.