A SMALL TURBOJET ENGINE MPM-20 WITH VARIABLE EXHAUST NOZZLE

Abstract

The aim of this thesis is to describe the jet engine MPM-20 with a variable nozzle exit, as a system with two degrees of freedom. The paper describes the development and current status of MPM-20 engine in the test engine. In the following analysis, in describing the effect of changing the nozzle exit section to run the engine with regard to the planned structural remodeling MPM20 engine. The core work is to address proposals for changes in the output control section. In the last part of this work is described showing the effect on the measurement speed due to changes in engine output variabile exhaust nozzle section.