Rapid Conceptual Design Testbed | Hypersonic Flight Vehicle Modeling and Control | Intelligent Flight Control | Aeroservoelasticity | Propulsion & Combustion | UAV Technologies



concept 0 logo
concept 0
< CONCEPT ONE / Eagle Scout >


  • Design of a Fuel Cell Powered UAV for Environmental Research
    (Uche C. Ofoma and Chivey C. Wu
    California State University, Los Angeles, Los Angeles, CA, 9003

    This paper describes the design of an unmanned aerial vehicle (UAV) intended for use as a remote sensing tool. Rationale behind the design goals are stated as well as the challenges of designing and fielding such a unique vehicle. Although fuel cells are not new, their integration with autonomous aircraft presents an interesting design problem. Analysis completed on a baseline configuration is covered and issues concerning fuel cell weight, size and cost are detailed. The paper presents an alternate approach to meeting the goal of developing a reliable fuel cell powered UAV for environmental research. This approach uses a smaller UAV as a test bed for major aircraft components. It is hoped that this design methodology will eventually provide ecologists with a robust and affordable method of conducting local scale, high resolution remote sensing and aerial photography.
    < PDF / Word>



concept 0 logo

Design and Composite Fabrication of a Wing for a Fuel Cell UAV

  • A UAV platform is desired by the Multidisciplinary Flight Dynamics and Control Laboratory (MFDCLab) as well as the Center for Environmental Analysis - Center for Research Excellence in Science and Technology (CEA-CREAST) to perform environmental sampling and to demonstrate a new technology in aircraft propulsion. In addition, the development of flight control lasws for a fuel cell powered aircraft that is capable of autonomous flight is of intrest to the MFDCLab. Pursuant to these goals, an overall aircraft design that emphasized stability and a high lift-to-drag ratio was employed. The Eppler 214 airfoil representeed a compromise between attaining high lift and minimum drag at low speed and low Reynolds number; roughly 30 to 35 mph and Re of 200,000. A high aspect ratio of 23, made the wing designlook like a gliderand imparted the maximum ability for the aircraft to protect the fuel cell from damage due to engine failure or crash. The Fuel Cell UAV has a maximum glide ratio of 22.

    Ease of construction and a high strength to weight ratio were factors in the choice of a foam core composite wing structure. The use of rare earth magnets for the wing segment connections allow for easy disassembly

Copyright © 2004 Multidisciplinary Flight Dynamics & Control Laboratory
Cal State University, Los Angeles

Home Events Research Publications Calendar Members Contact Us