Design, kinematic and fluid-structure interaction analysis of a morphing wing

Yang, Hui; Jiang, Songcheng; Wang, Yan; Xiao, Hong

doi:10.1016/j.ast.2023.108721

Cited by 4 publications

(1 citation statement)

References 30 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…This equation is often used in conjunction with finite element analysis (FEA) to model the wing structure and predict its behavior. One study that applied this approach was conducted by Wang et al (2018), who used FEA to analyze the static structural behavior of a wing with morphing winglets. They found that the morphing winglets reduced the bending moment and deformation of the wing, leading to a reduction in stress and improved structural performance.…”

Section: Wing Structural and Vibrational Analysismentioning

confidence: 99%

Vibrational Analysis of a Wing with Morphing/Variable Winglets

Gilani¹

2023

Preprint

View full text Add to dashboard Cite

This work presents a numerical and analytical vibrational and structural analysis of a wing model with morphing winglets. The methodology for this analysis is developed by the undergraduate thesis students in collaboration with the faculty at Toronto Metropolitan University (formerly known as Ryerson University) and performs a static structural and modal analysis for the developed wing with morphing winglet model. This report summarizes the modal and static structural analysis conducted on the model. The CAD model for the study was developed on Solidworks while the two analyses were conducted on Ansys. The wing model was developed with four winglet configurations with varying cant angles. Various winglet configurations were designed with variable cant to study the effect of morphing winglet on the structure’s modal analysis. During the structural test, it was observed that the model undergoes a deflection of 0.001 in under the prescribed loading conditions. The modal analysis was completed for the four configurations using similar boundary conditions as for the static structural analysis. The average frequency for the first mode shape for all the configurations were recorded to be 29 Hz. The results for the modal analysis conducted on Ansys were then verified using an analytical methodology. The equations for this method were developed by modelling the wing as a slender and straight wing with rigid root and no sweep back angles. The procedure for this accounted for the maximum speed of the wind tunnel at Toronto Metropolitan University. The frequency solution obtained from the analytical methodology was then compared to the frequency obtained from the modal analysis completed on Ansys. The frequency at flutter was calculated to be 30 Hz. This validates the assumptions and expectations made prior to both methods of analysis. The next step for this study would be to build the 3D model of the wing with morphing winglets and conduct a ground vibration testing and wind tunnel testing. The observations made during this study, specifically, the natural frequencies, damping, and mode shapes, can be further compared and validated through conducting the ground vibration testing and wind tunnel testing of these models. By comparing the results, it is possible to validate the numerical models and simulation techniques used for the modal analysis and improve the design of the wing with winglets.

show abstract

Section: Wing Structural and Vibrational Analysismentioning

confidence: 99%