Experimental and theoretical study on rolling effectiveness of multiple control surfaces

It is well known that the effectiveness of a trailing-edge control surface can be substantially diminished due to the elastic twist of an airfoil or rolling wing. This aeroelastic phenomenon is known as control surface reversal when the lift or rolling rate vanishes at a sufficiently large ratio of flow dynamic pressure to airfoil or wing stiffness. However, a leading-edge control surface can be used to counteract control surface reversal, and, indeed, in principle, a leading-edge control surface can entirely cancel the tendency of the trailing-edge control surface to undergo reversal. Moreover, analysis shows that by using a simple adaptive control strategy, one can use a combination positive and negative control surface rotations to maximize lift and rolling effectiveness or minimize control surface rotations. In the present work, a theoretical-experimental study of the effectiveness of trailing- and leading-edge control surfaces has been made for a rolling wing-fuselage model. An experimental model and wind-tunnel test are used to assess the theoretical results. The theoretical model includes the inherently nonlinear dry friction damping moment between the spindle support and the experimental aeroelastic wing model for the rolling degree of freedom. A three-dimensional vortex lattice aerodynamic theory is employed. New insights into the behavior and design of an adaptive aeroelastic wing using trailing- and leading-edge control surfaces are provided.

Duke Scholars

Author Earl H. Dowell Thomas Lord Department of Mechanical Engineering and Materia ...