UAV - MFDCLab

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

FUEL-CELL POWERED
UAV SERIES


CONCEPT ONE | CONCEPT TWO



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Documents

  • 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>

Presentations

 

 
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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

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