The open fan as a highly efficient propulsion concept is a promising approach to reduce climate-damaging emissions in aviation. However, the increased vibroacoustic emissions of the fan resulting from the open design lead to elevated cabin noise. Energy harvesting resonators can be used to leverage the piezoelectric effect and to attenuate structural vibrations caused by the acoustic loading simultaneously. To evaluate the potential of a specific configuration of energy harvesting resonators, an investigation of the dynamic interaction between the airframe and the resonators is necessary. Therefore, the eigenmodes and eigenfrequencies of a representative stiffened plate are determined experimentally using modal analysis via laser scanning vibrometry. A finite element model of the stiffened plate with the resonator idealized as a mass–spring element is implemented. The stiffness of this simplified resonator model is calibrated by correlating simulated with experimental results following a model updating approach. Finally, an optimization framework designed to determine the optimal quantity and placement of resonators using the experimentally validated model and representative loads is implemented to maximize both vibroacoustic attenuation and energy harvesting efficiency. The resulting framework serves as a generalized optimization tool capable of systematically optimizing the resonator configuration based on airframe geometry and specified vibroacoustic loading scenarios.

The integration of distributed electric propulsion into a wing significantly alters the dynamic behavior of the wing. Consequently, the loads on the wing structure in service, in particular upon transient gust and landing impact loads, change substantially compared with conventional aircrafts with main engines mounted on the inner wing. As this might significantly increase the stress levels and number of load cycles, this paper assesses the impact of wing-integrated distributed propulsion on the fatigue behavior of the wing structure. This assessment is conducted based on a retrofit scenario of a conventional 19-seater commuter aircraft of the CS-23 category retrofitted with distributed electric propulsion. The wing structure is idealized with beam elements. Static and dynamic response analyses followed by stress analyses are conducted for typical load cases occurring during operation of the aircraft. The fatigue analysis is carried out based on the safe life approach. This study concludes that the integration of distributed electric propulsion has a substantial impact on the fatigue behavior of the wing. A significant increase in fatigue damage for the electric configurations compared with the conventional configuration is observed, in particular in the outer wing area. The increased damage accumulation is a result of the higher stress amplitudes and the longer decay duration of the structural vibrations due to gusts. The results suggest that adjustments to the structural design and maintenance procedures of future electric aircrafts may be necessary.

In the preliminary design of aircraft structures, efficient modelling techniques are essential to balance accuracy and computational cost. Shear Panel Theory (SPT) offers a simple yet effective idealisation of thin-walled, stiffened structures such as wings. It captures more structural detail—like ribs, sweep and taper—than traditional beam idealisation and would otherwise require detailed finite element analysis. However, compared to a finite element model, the degrees of freedom of the structure as well as the meshing effort are significantly reduced, as SPT idealisation uses a structural element approach. This improves mass estimation and structural response calculation and makes SPT particularly well-suited for optimisation tasks in early design phases. This work presents a methodology to derive structural properties of wing segments based on NACA airfoils using SPT. This offers adjustment of the wing’s geometry for use in aeroelastic analysis and enables fast evaluation of structural behaviour and gradient computation, supporting integration into multidisciplinary design optimisation frameworks. The proposed methodology advances the use of idealised structural models in aircraft design by bridging the gap between high-fidelity analysis and system-level aeroelastic simulations, supporting faster and more informed early design iterations.

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