Abstract
in this study the effect of uncertainties on the flutter and instability speeds of the control actuation system of a missile is analyzed. The control surface is modeled as a typical section wing with uncertainties in damping and stiffness coefficients. The analyses are carried out for incompressible flow with some uncertainties in aerodynamic coefficients. The actuator dynamics of the aeroservoelastic system is modeled as a second order system with a frequency varying uncertainty.
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