Replacing articulated flight control surfaces with adaptive controls reduces surface discontinuities, and enhances low observability. Actuation of the aerodynamic surfaces is achieved by an electric field applied to PZT actuators embedded in the top and bottom skins, creating differential strain and shear (torsion) in the host substrate. The torsion of the torquebox was modeled in the presence of a full complement of air-loads by extending the Bredt-Batho theorem. This was accomplished through modifying Libove's method, using a thin-walled, linearly elastic, fully anisotropic, trapezoid cross-section beam. The linear tip twist angles due to a uniform cross-sectional moment were verified using the isotropic Bredt-Batho theorem, and published anisotropic results by applying isotropic, then anisotropic laminate elastic properties. The isotropic solutions were within 3.1%; the anisotropic results were within 6.9-10.9% of the published angles. The PZT actuation of the host structure was achieved by substituting PZT- composite laminate elastic properties into the derived solution and inducing strain and shear of the PZT lamina by composite laminate elastic properties into the derived solution and inducing strain and shear of the PZT laminae, the angular twist as a function of the host lamina orientation angle and applied voltage was recorded. The amount of twist ranged between 0.03 and 0.40 degrees, and 0.12-1.04 degrees for the AFC and G-1195 PZT laminae respectively.