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Heliplat®: high altitude very-long endurance solar powered UAV for telecommunication and Earth observation applications

Published online by Cambridge University Press:  03 February 2016

G. Romeo  and
G. Frulla
G. Romeo
Affiliation:
Department of Aerospace Engineering, Politecnico di Torino (Turin Polytechnic University), Turin, Italy
G. Frulla
Affiliation:
Department of Aerospace Engineering, Politecnico di Torino (Turin Polytechnic University), Turin, Italy
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Abstract

Research is at present being carried out at the Turin Polytechnic University with the aim of designing an HAVE/UAV (high altitude very-long endurance/unmanned air vehicle). The vehicle should climb to 17-20km by mainly taking advantage of direct Sun radiation and thereafter maintain a level flight; during the night, a fuel cells energy storage system would be used. A computer program has been developed to carry out a parametric study for the platform design. The solar radiation change over one year, the altitude, masses and efficiencies of the solar and fuel cells, and the aerodynamic performances have all been taken into account. The parametric studies have shown how fuel cells and solar cells efficiency and mass have the most influence on the platform dimensions. A wide use of high modulus CFRP has been made in designing the structure in order to minimise the airframe weight. A first configuration of HELIPLAT® (HELIos PLATform) was worked out, following a preliminary parametric study. The platform is a monoplane with eight brushless electric motors, a twin-boom tail type with an oversized horizontal stabiliser and two rudders. The co-ordinates at the root and along the wing span as well as the wing planform were optimised to achieve the best efficiency. Several profiles and wing plans have been analysed using the CFD software Xfoil and Vsaero. Several wind-tunnel tests were carried out to compare the analytically predicted performances. A preliminary design of a scale-sized technological demonstrator was completed with the aim of manufacturing a proof-of-concept structure. A FEM analysis was carried by using the Msc/Patran/Nastran code to predict the static and dynamic behaviour of the UAV structure.

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1084 , June 2004 , pp. 277 - 293
Copyright
Copyright © Royal Aeronautical Society 2004 

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