F. Afonso, J. Vale, É. Oliveira and F. Lau, F. Moreira, J. Marra, A. Meinicke, M. Pedras, O. Mello, J. Richards, W. Brussow, S. Warwick, A. Suleman

DOI Number: N/A

Conference number: IFASD-2017-004

One of the main concerns in the design of high aspect ratio wings is the constant change in the aerodynamic and inertial properties during flight which consequently affects its performance. To account for the structural flexibility in the preliminary design stage and adequately explore the design space, an aeroelastic framework that considers the fluid-structure interaction is employed. There are some aeroelastic frameworks specially developed to study this type of wings, although the experimental data required to evaluate and validate these frameworks is scarce, particularly in what concerns flight tests. In this work, the experimental data from the ground vibration tests, static tests and flight tests carried out for a highly flexible unmanned flight test demonstrators are used to evaluate and validate both the ASWING and an in-house nonlinear aeroelastic frameworks.

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In Categories: 1.Events, Highly Flexible Aircraft Structures, IFASD 2017
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