| Advances in aerodynamic flight controls can increase performance and lower the cost of guided weapons. Research at The University of Texas at Arlington has focused on using active materials to produce a lightweight, low-cost, missile fin that can be used on subsonic and supersonic weapons. This dissertation describes the design, construction, and testing of one such aerodynamic control device, consisting of a circular arc spoiler integrated with a piezoelectric bimorph actuator. As part of this dissertation, an examination of state-of-the-art active materials technology was conducted to select an actuator material compatible with guided weapon operating conditions. An examination of state-of-the-art aerodynamic "active structures" research was also conducted to identify aerodynamic control schemes suitable for integration with guided weapon control fins. The aerodynamic controls schemes examined include: the all-moving wing, wing twist, discrete flaps, continuous flaps, jet spoilers, and mechanical spoilers. After determining the advantages and disadvantages of each control device the combination of a mechanical spoiler and piezoelectric bimorph was selected for further research. A missile fin model using an integrated piezoelectric circular-arc spoiler was designed, built, and tested in a subsonic wind tunnel at speeds up to 210 ft/s (64 m/s). Aerodynamic quantities presented include CL, CL/CD, and C M as functions of spoiler displacement. Actuator related quantities presented include displacement vs. input voltage, force vs. input voltage, and spoiler bandwidth. |
