This paper presents the use of a new class of flight control actuators employing Post-Buckled Precompressed (PBP) piezoelectric elements in morphing wing Uninhabited Aerial Vehicles (UAVs). The new actuator relieson axial compression to amplify deflections and control forces simultaneously. Two designs employing morphingwing panels based on PBP actuators were conceived. One design employed PBP actuators in a membrane wingpanel over the aft 60% of the chord to impose roll control on a 720mm span subscale UAV. This design relied ona change in curvature of the actuators to control the camber of the airfoil. Axial compression of the actuatorswas ensured by means of rubber bands and increased end rotation levels with almost a factor of two up to ±13.6?peak-to-peak, with excellent correlation between theory and experiment. Wind tunnel tests quantitatively proved that wing morphing induced roll acceleration levels in excess of 1500 deg/s2. A second design employed PBPactuators in a wing panel with significant thickness, relying on a highly compliant Latex skin to allow for shapedeformation and at the same time induce an axial force on the actuators. Bench tests showed that due to theaxial compression provided by the skin end rotations were increased with more than a factor of two up to ±15.8?peak-to-peak up to a break frequency of 34Hz. Compared to conventional electromechanical servoactuaters, the PBP actuators showed a net reduction in flight control system weight, slop and power consumption for minimal part count. Both morphing wing concepts showed that PBP piezoelectric actuators have significant benefits over conventional actuators and can be successfully applied to induce aircraft control.