Design of Hybrid Propulsion Systems for Unmanned Aerial Vehicles

Abstract

The aim of aircraft engines development is the propulsion which is characterized by high power-to-mass ratio. Therefore, the alternative solutions that provide the required power by the low weight propulsion are sought after. The main advantage of these solutions is improvement of environmental and economic properties. This paper presents the overview of solutions and studies conducted for the unmanned aerial vehicles propulsion. For the purposes of studies a test bench was prepared. Its enables the comparison of the propulsion operating parameters taking into account changes in the values of thrust and propulsion power. The summary includes a proposal to improve the environmental indicators of propulsion systems for unmanned aerial vehicles.

A Virtual Test Bench of a Parallel Hybrid Propulsion System for UAVs

“…Similar advantages are expected in the aeronautics field, where the application are still few and mostly limited to UAVs. In recent years a number of studies on the subject have been published, including several theoretical studies [2][3][4][5][6][7], definition of test benches [8][9][10] and aircraft prototypes [11,12]. So far, the majority of the available literature is focused on the design and the performance analysis of one of two alternative architectures: the serial hybrid configuration and the parallel one.…”

Overview of solutions and analysis of the ability to evaluate the performance parameters of unmanned aerial vehicles propulsion systems

“…The use of hybrid (ICE-electric) drive in Unmanned Aerial Platforms brings together the advantages of the internal combustion engine (high energy value of aviation fuel) and electric motor (high energy conversion efficiency) [13][14][15][16]. Due to the differences between the vehicle's drive cycle and the aircraft flight profile, it is not possible to directly translate the advantages of the hybrid system from road to air transport.…”

Experimental Study of the Swirling Oxidizer Flow in HTPB/N2O Hybrid Rocket Motor

“…These characteristics are obtained by a combination of liquid propulsion system and solid propulsion system features. By this alternative, it is possible to perform a vast range of missions from low orbit missions like sounding rocket [1,2] and target drones [3] to space missions such as transportation vehicles [4,5], thrusters [6], and upper-stage motors [7]. In this type of propulsion system, usually, the solid fuel is a cylinder with port(s) in it, placed between injector(s) and nozzle (shown in Figure 1).…”