Characterization of Piezoelectric Macrofiber Composite Actuated Winglets

Abstract

Piezoelectric macro-fiber composite (MFC) structures have been used to develop oscillating winglets for active control of wing-tip vortices. A MFC structure was embedded inside a wing-section to oscillate the winglet at its free end. The goal is to weaken the potentially harmful tip vortices by introducing controlled instabilities through both spatial and temporal perturbations produced by an oscillating winglet. In the present study we have characterized MFC actuated winglets under different input excitation and pressure loading conditions. It consisted of bench-top experiments to characterize the structural resonance, with and without point pressure loading and wind tunnel tests involving distributed pressure loading. Surface pressure measurements were carried out at three spanwise locations to measure the effect of oscillating winglet on the pressure distributions on the wing surface. MFC actuated winglets show bimodal resonance behavior and the modes of oscillations are independent of magnitude of input excitation and the pressure loading.

Mathematical Modeling, Design Validation, and Simulation of Morphing Mechanism for Winglet Applications

“…As the effective angle of attack is reduced, so is the lift curve for the airfoil. The new slope of the lift curve for a finite airfoil can be defined in terms of the infinite lift slope as shown in Equation (1)(2)(3)(4)(5).…”

“…The velocity and acceleration equations are determined via differentiation of the above equations (2)(3)(4)(5) and (2)(3)(4)(5)(6). The actual solution of the system is conducted by relating the two parts, A and B, via the link C. The following equation represents this relationship:…”

Mathematical Modeling, Design Validation, and Simulation of Morphing Mechanism for Winglet Applications

“…As the effective angle of attack is reduced, so is the lift curve for the airfoil. The new slope of the lift curve for a finite airfoil can be defined in terms of the infinite lift slope as shown in Equation (1)(2)(3)(4)(5).…”

Design and Optimisation of Morphing Aircraft

“…The results indicated it was possible to find an optimal configuration although the comparisons were limited and more tests are required. MFC actuators to oscillate the winglet [99] Although conventional control surfaces were used in the study, it did not exclude the possibility of using a morphing camber, which is still an open question. Oscillations of the winglets could also be achieved by using piezoelectric materials.…”

“…Oscillations of the winglets could also be achieved by using piezoelectric materials. Experimental studies were performed by Guha et al [99,100]. As shown in Figure 1.19(b), MFC actuators were attached to the winglet model to oscillate the winglets.…”