Flight vehicles are often designed to function around a primary operating point such as an efficient cruise or a high maneuverability mode. Performance and efficiency deteriorate rapidly as the airplane moves towards other portions of the flight envelope. One solution to this quandary is to radically change the shape of the aircraft. This yields both improved efficiency and a larger flight envelope. This global shape change is an example of aircraft morphing. Morphing aircraft structures offer the unique capability of multi-role deployment along with increased efficiency over fixed geometry aircraft. Various morphing aircraft designs are being investigated by engineers. One concept involves a span morphing wing. This type of design allows for at least two discreet modes of the aircraft. The clean configuration, in which the extensible portion of the wing is fully retracted, yields a high speed dash mode. Fully extending the wing provides the aircraft with a low speed mode tailored for fine tracking and loiter tasks. Considerable aerodynamic forces are present when trying to shift an airplane from one configuration to the next. These surface pressures cause undesired moments and forces on the control effectors that are morphing the structure. This paper focuses on the reduction of the forces acting on the morphing mechanism within the wing.


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    Titel :

    A design scheme aimed at minimizing actuator and structural loads of a span morphing aircraft


    Beteiligte:
    Boothe, Kenny (Autor:in)


    Erscheinungsdatum :

    2006


    Format / Umfang :

    10 Seiten, 16 Quellen



    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch





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