UAV Aeroelastic Control Using Redundant Micro-Actuators

The investigation of trailing edge micro-actuators for aeroelastic control of uninhabited air vehicles (UAVs) has ranged from examining the fundamental aerodynamic effects to demonstrating flutter suppression of a flexible wing. The applicability of aerodynamic prediction methods including CFD and panel methods has been studied. Several generations of actuator concepts have been developed and characterized. Wind tunnel experiments have been completed on a rigid wing to determine the aerodynamic performance of the various actuator concepts including the effects of deflection pattern and rate. Unsteady wind tunnel investigations with Particle Image Velocimetry have been completed to gain insight into the flow physics. An elastically scaled flexible wind tunnel model was fabricated, instrumented, and equipped with several actuators. Active flutter suppression of the flexible model was accomplished using the micro-actuators. This report summarizes the completed research program and highlights potential areas for further investigation.