23 May 1997 Smart wing wind tunnel model design
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To verify the predicted benefits of the smart wing concept, two 16% scale wind tunnel models, one conventional and the other incorporating smart wing design features, were designed, fabricated and tested. Meticulous design of the two models was essential to: (1) ensure the required factor of safety of four for operation in the NASA Langley TDT wind tunnel, (2) efficiently integrate the smart actuation systems, (3) quantify the performance improvements, and (4) facilitate eventual scale-up to operational aircraft. Significant challenges were encountered in designing the attachment of the shape memory alloy control surfaces to the wing box, integration of the SMA torque tube in the wing structure, and development of control mechanisms to protect the model and the tunnel in the event of failure of the smart systems. In this paper, detailed design of the two models are presented. First, dynamic scaling of the models based on the geometry and structural details of the full- scale aircraft is presented. Next, results of the stress, divergence and flutter analyses are summarized. Finally some of the challenges of integrating the smart actuators with the model are highlighted.
© (1997) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
Christopher A. Martin, Christopher A. Martin, Larry Jasmin, Larry Jasmin, John S. Flanagan, John S. Flanagan, Kari Appa, Kari Appa, Jayanth N. Kudva, Jayanth N. Kudva, } "Smart wing wind tunnel model design", Proc. SPIE 3044, Smart Structures and Materials 1997: Industrial and Commercial Applications of Smart Structures Technologies, (23 May 1997); doi: 10.1117/12.274675; https://doi.org/10.1117/12.274675

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