Summary
A method for the nonlinear analysis of dynamic systems and its application to an aircraft with a flexible wing is presented. In extension of existing averaging methods this procedure follows the linearizing eigenvalue analysis, but defines the eigenvalue and eigenvector as functions of the deflection a from the examined equilibrium. A test case to verify the robustness of the method and its application to the spiral mode and the short period mode of a rigid body aircraft with a wing of four flexible degrees-of-freedom is shown. The analysis of the unstable spiral mode shows the existence of additional stable equilibria in the vicinity of the examined equilibrium due to system nonlinearities.
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Siepenkötter, N., Kasberg, W., Alles, W. (2003). Approximated Nonlinear Stability Analysis of the Dynamics of Flexible Aircraft. In: Ballmann, J. (eds) Flow Modulation and Fluid—Structure Interaction at Airplane Wings. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 84. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-44866-2_12
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DOI: https://doi.org/10.1007/978-3-540-44866-2_12
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