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Aerospace 2018, 5(2), 34; https://doi.org/10.3390/aerospace5020034

Hybrid Propulsion Systems for Remotely Piloted Aircraft Systems

School of Engineering, RMIT University, Melbourne, VIC 3000, Australia
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Received: 31 December 2017 / Revised: 19 March 2018 / Accepted: 20 March 2018 / Published: 29 March 2018
(This article belongs to the Special Issue Aeroengine)
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Abstract

The development of more efficient propulsion systems for aerospace vehicles is essential to achieve key objectives. These objectives are to increase efficiency while reducing the amount of carbon-based emissions. Hybrid electric propulsion (HEP) is an ideal means to maintain the energy density of hydrocarbon-based fuels and utilize energy-efficient electric machines. A system that integrates different propulsion systems into a single system, with one being electric, is termed an HEP system. HEP systems have been studied previously and introduced into Land, Water, and Aerial Vehicles. This work presents research into the use of HEP systems in Remotely Piloted Aircraft Systems (RPAS). The systems discussed in this paper are Internal Combustion Engine (ICE)–Electric Hybrid systems, ICE–Photovoltaic (PV) Hybrid systems, and Fuel-Cell Hybrid systems. The improved performance characteristics in terms of fuel consumption and endurance are discussed. View Full-Text
Keywords: remotely piloted aircraft systems; unmanned aerial systems; hybrid electric propulsion; internal combustion engine; photovoltaic cell; fuel cell; electric motor remotely piloted aircraft systems; unmanned aerial systems; hybrid electric propulsion; internal combustion engine; photovoltaic cell; fuel cell; electric motor
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This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited (CC BY 4.0).
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Abdul Sathar Eqbal, M.; Fernando, N.; Marino, M.; Wild, G. Hybrid Propulsion Systems for Remotely Piloted Aircraft Systems. Aerospace 2018, 5, 34.

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