Asymptotic analysis of aircraft wing model in subsonic airflow (Q2717412)

The asymptotic and spectral analysis of an aircraft wing model has been developed in order to control the flutter phenomena using the so-called self-straining actuators. The model is governed by two coupled integro-differential equations and by a two-parameter family of boundary conditions. The unknown functions (bending and torsion angle) depend on time and one spatial variable. The differential parts of the above equations form a coupled linear hyperbolic system, the integral parts are of convolution type. The author shows that the Laplace-transformed solutions of these equations can be represented in terms of a generalized resolvent operator.NEWLINENEWLINEFor the entire collection see [Zbl 0959.00036].