Numerical and experimental validation of a full scale servo-actuated morphing aileron model

Aircraft industry is by now deeply involved in technological breakthroughs bringing innovative frameworks, in which the morphing systems constitute the most promising scenario. These systems are taking a remarkable role among the unconventional solutions for the improvement of performance in the operating conditions. The application of morphing devices involves a combination among structural and aerodynamic analyses, actuation requirements, weight assessment and flight control performance. The research project CRIAQ-MDO505, Canadian-European cooperation project on smart technologies, has investigated morphing structures potential through the design and the manufacturing of a variable camber aileron tailored to CS-25 category aircraft applications. This paper is especially focused on the most considerable results able to validate the conceptual design: functionality, ground vibration and wind tunnel tests outcomes have been discussed. The ailerons typically constitute crucial elements for the aerodynamic forces equilibrium of the wing. Therefore, compared to the traditional architectures, the need of studying the dynamic performance and the following aeroelastic impact is, in the specific case of servo-actuated variable-shaped systems, higher. Relying upon the experimental evidence within the present research, the issue appeared concerns the critical importance of considering the dynamic modelling of the actuators in the design phase of a smart device. The higher number of actuators and mechanisms involved makes de facto the morphing structure much more complex. In this context, the action of the actuators has been modelled within the numerical model of the aileron: the comparison between the modal characteristics of numerical predictions and testing activities has shown a high level of correlation. Moreover, the compliance of the device with the design morphing shapes has been proved by wind tunnel test. The outcomes are expected to be key insights for future designers to better comprehend the dynamic response of a morphing aileron, primary knowledge for flutter and failure analyses.