Abstract: A friction damped turbine blade is disclosed. The turbine blade is formed of segments configured so as to form an assemblage corresponding to the airfoil shaped body. Each of the segments is in slidable contact with an adjacent segment. During turbine operation, the segments rub against one another due to the stresses placed on the blade, imparting frictional damping to the turbine blade.

Abstract: A configurable aerial vehicle aerosurface is disclosed, The configurable aerial vehicle aerosurface includes first and second airfoil surfaces in sliding engagement. A plurality of apertures pass transversely through the airfoil surfaces and are disposed in such a relationship so as to define a first position wherein the apertures are in substantial alignment and a second position wherein the apertures are in substantial non-alignment. In this way, the configurable aerial vehicle aerosurface of the present invention can be configured from a first, low drag transport position, to a second, aerodynamic position to provide missile lift and control.