DEVELOPMENT CONCEPT
OF JET ENGINES FOR THE UNMANNED AERIAL VEHICLES
À.Ì. Shojaei, V.S. Chigrin
Based on published open sources, analyzed the problems
solved by unmanned aerial vehicles (UAVs) and applied
them to the types of gas turbine engines. Designing engine for the UAV can perform
«from scratch» in designing a special engine for a specific aircraft. However, a
more appropriate use of the gas generator is tested practice of modular development of gas
turbine engines, upgrading them to solve specific problems. For supersonic UAV with
a range of 500 km is reasonable to use a simplified and light turbojet, relatively
inexpensive, although with worse performance characteristics compared with turbofan
engines. The distinctive design features of these engines are a low number of compressor
stages, single-stage turbine, double-bearing, single-shaft rotor, the simplified
system starter, system lubrication and fuel. As objective function in designing
for turbojet engines with short lifetime for the UAV is advisable to use
at least economic cost to design, manufacture and operation of the engine at the
given parameters of thrust and specific fuel consumption. An example of the design
characteristics of the single-shaft turbojet calculation, developed for the UAV-based
gas generator series turbofan training aircraft.
Key words: Unmanned aerial vehicles (UAV), gas-turbine engines, turbojet, module Turbo-engine,
supersonic UAV.