Modelling of Distributed-Propulsion Low-Speed HALE UAVs Burning Liquid Hydrogen

Paper #:
  • 2015-01-2467

Published:
  • 2015-09-15
DOI:
  • 10.4271/2015-01-2467
Citation:
Gallo, L., Tashie-Lewis, B., Laskaridis, P., Miller, P. et al., "Modelling of Distributed-Propulsion Low-Speed HALE UAVs Burning Liquid Hydrogen," SAE Technical Paper 2015-01-2467, 2015, doi:10.4271/2015-01-2467.
Pages:
8
Abstract:
The present work focuses on developing an integrated airframe, distributed propulsion, and power management methodology for liquid-hydrogen-fuelled HALE UAVs. Differently from previous studies, the aim is to assess how the synergies between the aforementioned sub-systems affect the integrated system power requirement, production, and distribution. A design space exploration study was carried out to assess the influence of distributing motor-driven fans on three different airframes, namely a tube-and-wing, a triple-fuselage, and a blended-wing-body.For the considered range of take-off masses from 5,000 to 15,000 kg, the 200 kW payload power requirement under examination was found to re-shape the endurance trends. In fact, the drop in specific fuel consumption due to the engine design point change alters the trends from nearly flat to a 25% maximum endurance increase when moving towards heavier take-off masses. For the selected distributed propulsion system, the BWB airframe was found to improve endurance by approximately 30% compared to the other designs, and no apparent benefit was found with the triple-fuselage airframe for the present application.
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