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Modeling techniques and design principles of a low-aspect-ratio active aeroservoelastic wing

The design of a new aeroservoelastic wing configuration is detailed. The design uses a torque plate mounted within an aerodynamic shell. As the plate is actively twisted, the shell, which is connected to the plate at the tip, undergoes a pitch deflection. An active torque plate for a low aspect ratio subsonic wing section is analyzed and designed with laminated plate theory. Several actuator elements were considered for the plate, including: conventionally attached lead zirconate titanate (PZT), polyvinylidene fluoride (PVDF), piezoelectric fiber composites and directionally attached piezoelectric (DAP) elements. The analytical studies demonstrate that the highest twist deflections are obtained by DAP elements bonded to a beryllium substrate which produces twist deflections and restrained moments that are 67% greater than the next closest actuator material. An aeroservoelastic wing using the DAP torque plate was constructed to demonstrate the concept. The wing used an active plate made from DAP elements bonded to an AISI 1010 steel substrate. The torque plate was mounted within a graphite-epoxy wing with a modified NACA 0012 profile, measuring 2.6' in chord with a 3.66' span. The wing was tested to 160 ft/s and exhibited a stable increase in pitch deflection (in addition to the +/- 3.5 degree(s) static deflection) with theory and experiment in close agreement.