High altitude long endurance unmanned aerial vehicle of a new generation - a design challenge for a low cost, reliable and high performance aircraft

• Autorzy: Goraj Z. , Frydrychewicz A. , Świtkiewicz R. , Hernik B. , Gadomski J. , Goetzendorf-Grabowski T. , Figat M. , Suchodolski S.
• Języki publikacji: EN

Abstrakty

EN

This paper describes a design process of HALE PW-114 sensor-craft, developed for high altitude (20 km) long endurance (40 h) surveillance missions. Designed as a blended wing (BW) configuration, to be made of metal and composite materials. Wing control surfaces provide longitudinal balance. Fin in the rear fuselage section together with wingtips provide directional stability. Airplane is equipped with retractable landing gear with controlled front leg that allows operations from conventional airfields. According to the initial requirements it is twin engine configuration, typical payload consists of electro-optical/infra-red FLIR, big SAR (synthetic aperture radar) and SATCOM antenna required for the longest range. Tailless architecture was based on both Horten and Northrop design experience. Global Hawk was considered as a reference point - it was assumed that BW design has to possess efficiency, relative payload and other characteristics at least the same or even better than that of Global Hawk. FLIR, SAR and SATCOM containers were optimised for best visibility. All payload systems are put into separate modular containers of easy access and quickly to exchange, so this architecture can be consider as a "modular". An optimisation process started immediately when the so-called "zero configuration", called PW-l11 was ready. It was designed in the canard configuration. A canard was abandoned in HALE PW-113. Instead, new, larger outer wing was designed with smaller taper ratio. New configuration analysis revealed satisfactory longitudinal stability. Calculations suggested better lateral qualities for negative dihedral. These modifications, leading to aerodynamic improvement, gave HALE PW-114 as a result. The design process was an interdisciplinary approach, and included a selection of thick laminar wing section, aerodynamic optimisation of swept wing, stability analysis, weight balance, structural and flutter analysis, many on-board redundant systems, reliability and maintability analysis, safety improvement, cost and performance optimisation. Presented paper focuses mainly on aerodynamics, wing design, longitudinal control and safety issues. This activity is supported by European Union within V FR, in the area Aeronautics and Space.

Słowa kluczowe

EN

aircraft; UAV; stability; structure; flutter; safety

• Wydawca: Polska Akademia Nauk, Wydział IV Nauk Technicznych
• Czasopismo: Bulletin of the Polish Academy of Sciences. Technical Sciences
• Rocznik: 2004
• Tom: Vol. 52, nr 3
• Strony: 173--194
• Opis fizyczny: Bibliogr. 35 poz., 45 rys., 15 tab.

Twórcy

autor

Goraj Z.

• Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology, 24 Nowowiejska St., 00–665 Warszawa, Poland

autor

Frydrychewicz A.

• Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology, 24 Nowowiejska St., 00–665 Warszawa, Poland

autor

Świtkiewicz R.

• Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology, 24 Nowowiejska St., 00–665 Warszawa, Poland

autor

Hernik B.

• Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology, 24 Nowowiejska St., 00–665 Warszawa, Poland

autor

Gadomski J.

• Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology, 24 Nowowiejska St., 00–665 Warszawa, Poland

autor

Goetzendorf-Grabowski T.

• Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology, 24 Nowowiejska St., 00–665 Warszawa, Poland

autor

Figat M.

• Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology, 24 Nowowiejska St., 00–665 Warszawa, Poland

autor

Suchodolski S.

• Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology, 24 Nowowiejska St., 00–665 Warszawa, Poland

Bibliografia

• [1] Website: www.uavnet.com.
• [2] D. Fulghum and R. Wall, “Israel’s future includes armed, long-range UAVs”, Aviation Week and Space Technology, 83–84 (2002).
• [3] D. Fransaer and G. Lissens, “PEGASUS, the future of remote sensing”, UAVNET Meeting in Eilat, Oct. 2002, www.uavnet.com.
• [4] Sh. Tsach, “Advanced technologies for civil applications UAV’s”, Rochester UAVNET Meeting, July 2002, www.uavnet.com.
• [5] A. Yaniv, “Review of IAI advanced design HALE UAV activities”, UAVNET Eilat Meeting, Oct. 2002, www.uavnet.com.
• [6] G. Goodman (Jr.), “Manned-unmanned synergy-US army UAV-related efforts gain momentum”, Armed Forces Journal International, 56–61 (July 2002).
• [7] D. Fulghum and R. Wall, “Israel pursues high tech despite war costs”, Aviation Week and Space Technology, 78–80 (June 24, 2002).
• [8] M. Allouche, “Civil UAV safety issues – airworthiness and operational certification aspects”, UAVNET, Stockholm, Oct. 2001, www.uavnet.com.
• [9] A. Morag, “UNITE UAV National Industry Team”, Eilat UAVNET Meeting, Oct. 2002, www.uavnet.com.
• [10] CAPECON Project No GRD1–2001–40162 (Civil UAV Applications and Economic Effectivity of Potential Configuration Solutions), Technical documents 2002–2004. V FR of European Union.
• [11] A. Morag, “Aurora flight sciences corporate overview”, Eilat UAVNET Meeting, Oct. 2002, www.uavnet.com.
• [12] J. Vitali, S. Tsach and H. Avni, “Development Approach of the HERON Medium Altitude Long Endurance UAV”, 20th ICAS Proc., Vol. I, 380–390 (Sept. 1996).
• [13] Z. Goraj, Ph. Ransom and P. Wagstaff, “Dynamics and design aspects of future UAV’s”, Aviation VII (3), 20–36 (2003).
• [14] Z. Goraj and A. Frydrychewicz, “Design challenges associated to development of a new generation UAV”, Proceedings of the First International Conference on Unmanned Arial Vehicles, Kielce University of Technology, Kielce, 19 May 2004, 161–168 (2004), (in Polish).
• [15] Z. Goraj, A. Frydrychewicz, C. de’Tallec and J. Hermetz, “HALE UAV platform optimised for a specialized 20-km altitude patrol mission”, Proc. of 24th ICAS Congress, Yokohama 2004, Paper 1.6.3.
• [16] Z. Goraj, Ph. Ransom and P. Wagstaff, “From specification and design layout to control law development for unmanned aerial vehicles – lessons learned from past experience”, Proceedings of V European Workshop on Aircraft Design Education, Link¨oping, Sweden, 17–21 (June 2–4, 2002).
• [17] Z. Goraj, A. Frydrychewicz and J. Winiecki, “Design concept of a high altitude long endurance unmanned aerial vehicle”, Aircraft Design – An International Journal 2(1), 19–44.
• [18] Z. Goraj, “Dynamics of a high altitude long endurance UAV”, ICAS Congress 2000, England, Harrogate, paper 362, 10 (2000).
• [19] Z. Goraj and T. Ueda, “Ultra light wing structure for high altitude long endurance UAV”, ICAS Congress 2000, England, Harrogate, paper 476, 10 (2000).
• [20] Z. Goraj, “Design and flight dynamics of a HALE UAV – HARVE-2”, Workshop for the Advancement of Unmanned Air Vehicles (UAVs) for Civilian Commercial Applications, Paper no. 9, Israel Aircraft Industries, Israel, 15 (7–8 November 2000).
• [21] Z. Goraj, “Civilian unmanned aerial vehicles – overview of European effort and challenges for the future”, Aviation Journal, Vilnius 2003, Aviation VII(2), 1–18 (2003).
• [22] Z. Goraj, “Dynamic characteristics of different UAV configurations”, UAVNET Capua Meeting, Feb. 2002, www.uavnet.com.
• [23] B. Holder, Unmanned Air Vehicles – An Illustrated Study of UAVs, Copyright @ 2001 by Bill Holder.
• [24] Jane’s Unmanned Aerial Vehicles and Targets, ed. Kenneth Munson, Couldson, Surrey CR5 2YH, UK 2001.
• [25] www.airframe-technology.com/projects/global/index.
• [26] www.airframe-technology.com/projects/predator/index.
• [27] S. Tsach, A. Yaniv, H. Avni and D. Penn, “High altitude long endurance (HALE) UAV for Intelligence Missions”, 20th ICAS Proceedings, I, 368–379 (Sept. 1996).
• [28] W. P. Rodden and E. H. Johnson, MSC/Nastran v.68. Aeroelastic Analysis, Los Angeles, 1994.
• [29] D. H. Hodges and G. A. Pierce, Introduction to Structural Dynamics and Aeroelasticity, Cambridge University Press, Cambridge, 2002.
• [30] “Airframe and equipment engineering report”, No. 45, Simplified Flutter Prevention Criteria for Personal Type Aircraft, Rev. 23889.
• [31] “U.S. Department of transportation. Federal aviation administration”, Federal Aviation Regulations, Part 23, Amendments 1.42.
• [32] “U.S. Department of transportation. Federal aviation administration”, Advisory Circular 23.629(1A), (1985).
• [33] F. Kießling, On Simplified Analytical Flutter Clearance Procedures for Light Aircraft, DLR-Forschungsbericht, G¨ottingen 89–56 (1989).
• [34] W. Stender and F. Kießling, Aeroelastic Flutter Prevention in Gliders and Small Aircraft, DLR-Mitteilung, G¨ottingen 91–03, (1991).
• [35] Z. Goraj and S. Suchodolski, “Unmanned aerial vehicles of increased safety level”, Proc. of VI Conference on “Investigation Methods and Flight Tests of Aircraft”, 161–168 (June 2004), (in Polish).