To quantify the benefits of smart materials and structures adaptive wing technology. Northrop Grumman Corp. built and tested two 16% scale wind tunnel models of a fighter/attach aircraft under the DARPA/AFRL/NASA Smart Materials and Structures Development-Smart Wing Phase 1. Performance gains quantified included increased pitching moment, increased rolling moment and improved pressure distribution. The benefits were obtained for hingeless, contoured trailing edge control surfaces with embedded shape memory alloy wires and spanwise wing twist effected by SMA torque tube mechanism, compared to convention hinged control surfaces. This paper presents an overview of the results from the second wind tunnel test performed at the NASA Langley Research Center's 16 ft Transonic Dynamic Tunnel in June 1998. Successful results obtained were: (1) 5 degrees of spanwise twist and 8-12% increase in rolling moment utilizing a single SMA torque tube, (2) 12 degrees of deflection, and 10% increase in rolling moment due to hingeless, contoured aileron, and (3) demonstration of optical techniques for measuring spanwise twist and deflected shape.


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    Titel :

    DARPA/ARFL/NASA Smart Wing second wind tunnel test results


    Beteiligte:
    Scherer, L.B. (Autor:in) / Martin, C.A. (Autor:in) / West, M. (Autor:in) / Florance, J.P. (Autor:in) / Wieseman, C.D. (Autor:in) / Burner, A.W. (Autor:in) / Fleming, G.A. (Autor:in)


    Erscheinungsdatum :

    1999


    Format / Umfang :

    11 Seiten, 8 Quellen




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




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