STUDY OF THE TURBOJET ENGINES AS PROPULSION SYSTEMS FOR THE UNMANNED AERIAL VEHICLES

Abstract

The use of jet engines as propulsion systems for Unmanned Aerial Vehicles UAV's represents a actual challenge. For a large class of UAV's, providing more advantages with respect to the turboprop and turboshaft engines, as well as super-charged V12 piston engines, the small to medium size turbojet engines represent a more effective option. The research presented in this paper is focused on the thermo-dynamical analysis of a small sized turbojet. The single-spool turbojet engine model was used for the performance analysis; the one-dimensional engine cycle design was used to calculate the turbojet performances for a specified range of flight altitude and Mach number, as well as various engine operational regimes. From the numerical simulations have been expressed new parameter correlations, e.g. thrust - fuel flow, which will contribute to the deduction of a control law for the fuel flow. The objectives of the thermo-dynamical analysis have been fulfilled, with the calculated engine operating maps (i.e. variation of performances with altitude, flight Mach number and engine rotational speed), universal map of the engine; in addition, this analysis provides the values for significant engine parameters which are required by the engine's dynamic study.