ДВИГАТЕЛЬНЫЕ УСТАНОВКИ БЕСПИЛОТНОГО ЛЕТАТЕЛЬНОГО АППАРАТА НА ГРАНУЛИРОВАННОМ ТВЕРДОМ ТОПЛИВЕ

Abstract

The paper considers the use of a granulated solid fuel engine as a propulsion system for an unmanned aerial vehicle, which will be able to solve different kinds of problems in extreme conditions (extreme temperatures and low oxygen content). Vari-ous schemes of propulsion system using granulated solid fuel have been developed and proposed: gas turbine and rocket-turbine engines (screw and jet type). The optimality criteria for the granular solid fuel are determined. The fuel components of the engine have been selected. The compositions of granular fuel based on ammonium perchlorate and polybutadiene with terminal hydroxyl substances have been studied. In accordance with the optimality criteria, a composition using HTPB 37 % was selected for calcula-tions. The fuel parameters correspond to the optimality criteria (combustion temperature 1270 K, gas constant 457 kJ/(kgK), the density which is taking into account the porosity 930 kg/m3, k-phase 3 %. The calculation of the scheme of a gas turbine engine is made. The operating ranges of the parameters of the propulsion system are determined, such as: the ratio of air consumption to fuel (from 12.5 to 27.5), temperatures in the afterburning zone (1600–1100 K), specific power (3500–4300 kW / (kg / s)), efficiency (25–28 %), specific fuel consumption (0.83–1.06 kg/(kWh)). A gas turbine engine powered by granulated fuel is inferior to a modern piston engine in terms of specific fuel consumption (0.83 versus 0.58). However, a gas turbine engine on granulated fuel is signifi-cantly superior to a piston engine in terms of fuel consumption by 16% and efficiency by 1.8 times. An unmanned aerial vehicle powered by granulated solid fuel operates in extreme conditions with sufficiently high efficiency parameters.