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.
