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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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References

1. Anon Eternal Airplane. The lift-off of unmanned solar-electric wings. Popular Science, April 1994, 100, pp 70–75.Google Scholar
2. Hall, D.W., Watson, D.A., Tuttle, R.P. and Hall, S.A. Mission analysis of solar powered aircraft, NASA CR-172583, July 1985.Google Scholar
3. Hall, D.W. and Hall, S.A. Structural sizing of a solar powered aircraft. NASA CR-172313, April 1984.Google Scholar
4. Youngblood, J.W., Talay, T.A. and Pegg, R.J. Design of long-endurance unmanned airplanes incorporating solar and fuel cell propulsion. AIAA paper 84-1430, June 1984.Google Scholar
5. Curtin, B. Solar-powered UAV development for NASA. International Technical Conf on uninhabited aerial vehicles. UAV 2000, Paris, France, June 2000. Paper 10·18.Google Scholar
6. Edin, P. ESA HALE General Study. ESTEC, Noordwijk, November 1996.Google Scholar
7. Romeo, G. Piattaforma Volante da Alta Quota, ad Energia Solare, per Applicazioni di Telecomunicazione e Telerilevamento (High altitude long endurance solar powered platform for telecommunication and Earth observation applications). ASI (Italian Space Agency), Research Contracts RS-95-63, ARS-96-136, 1995, 1996.Google Scholar
8. Romeo, G. Design proposal of high altitude very-long endurance solar powered platform for Earth observation and telecommunication applications, 48th Int Astronautical Congress, October 1997, Turin. Paper IAF-97-M.2.05.Google Scholar
9. Romeo, G. Design proposal and wing box manufacturing of a self launching solar powered sailplane. XXV OSTIV Congress, St Auban (France), July 1997. Technical Soaring, 21, (4), pp 106–115, October 1997.Google Scholar
10. Romeo, G. Manufacturing and testing of graphite-epoxy wing box and fuselage structures for a solar powered UAV-HAVE, 21st Congress of the International Council of the Aeronautical Sciences (ICAS), Melbourne, Australia, September 1998. Paper A98-31591.Google Scholar
11. Romeo, G. Design of high altitude very-long endurance solar powered platform for Earth observation and telecommunication Applications. AEROTECNICA MISSILI e SPAZIO, 77,N3-4, July-December 98. pp 88–99.Google Scholar
12. Romeo, G., Frulla, G. and Fattore, L. Heliplat: High altitude very-long endurance solar powered UAV for telecommunication applications. FEM analysis, manufacturing and testing of 21m long CFRP wing box. Applied vehicle technology panel symposium on unmanned vehicles (UV) for aerial, ground and naval military operations. Ankara (Turkey) October 2000. PaperN12.Google Scholar
13. Romeo, G. and Frulla, G. Analisi Strutturale di un’Ala in Materiale Composito per un Velivolo ad Energia Elettro-Solare (Analysis of an advanced composite wing structure for a solar powered airplane). XIII AIDAA Congress (Italian Association of Aeronautics and Astronautics), Roma, September 1995, II, pp 965–976. (in Italian).Google Scholar
14. Romeo, G. Numerical analysis, manufacturing and testing of advanced composite structures for a solar powered airplane. XV AIDAA Congress, Torino, November 1999, II, pp 1001–1012.Google Scholar
15. Strganac, T.W. Wind study for high altitude platform design. NASA RP-1044, 1979.Google Scholar
16. Prossdorf, S. and Tordella, D. On an extension of Prandtl’s lifting line theory to curved wings. Impact of Computing in Science and Engineering, 1991, 3, pp 191–212.Google Scholar
17. Frulla, G. Preliminary reliability design of a solar-powered high altitude very long endurance unmanned air vehicle. J Aerospace Eng Part G, 216,N G4, 2002, pp 189–196.Google Scholar
18. Drela, M. Xfoil An analysis and design system for low Reynolds number aerofoils Conference on Low Reynolds number aerofoil aerodynamics, University of Notre Dame, June 1989.Google Scholar
19. Althauss, D. and Wortmann, F.X. Stuttgarter Profilkatalog, Vieweg, I.F. (Ed), 1981.Google Scholar
20. Althauss, D. Niedrig-geschwindigkeits-profile. Friedr. Vieweg 1996.Google Scholar
21. Nathman, J. K. Vsaero version 6.2 User Manual, Analytical Methods Inc., Washington USA, 2001.Google Scholar
22. Romeo, G., Frulla, G. and Fattore, L. Analysis of representativeness of the scaled-size prototype HELINET Reports Number: HE-013-A1A-POL-RP-01-. Issued 12 July 2000, 10 pp.Google Scholar
23. Romeo, G., Frulla, G. and Fattore, L. Revised scaled-size prototype design, HELINET Reports Number: HE-087-A1A-POL-RP-04. Issued 18 December 2000. 20 pp.Google Scholar