A New Architecture of Morphing Wing Based on Hyperelastic Materials and Metastructures With Tunable Stiffness
| العنوان: | A New Architecture of Morphing Wing Based on Hyperelastic Materials and Metastructures With Tunable Stiffness |
|---|---|
| المؤلفون: | Liping Xiao, Haifeng Zhao, Zhao Xu, Xiaoyu Li, Chengcheng Shen, Ke Wang, Lu Zhang |
| المصدر: | Frontiers in Mechanical Engineering, Vol 7 (2022) |
| بيانات النشر: | Frontiers Media SA, 2022. |
| سنة النشر: | 2022 |
| مصطلحات موضوعية: | morphing wing, hyperelastic materials, Mechanical Engineering, micro air vehicles (MAVs), metastructures with tunable stiffness, TJ1-1570, General Materials Science, Mechanical engineering and machinery, pneumatic networks, GeneralLiterature_MISCELLANEOUS, Industrial and Manufacturing Engineering, ComputingMethodologies_COMPUTERGRAPHICS, Computer Science Applications |
| الوصف: | Morphing wings with the ability of shape changing may enlarge the flight envelop of air vehicles. This is particularly important for small-scale aircrafts demanding maneuverability and adaptability in dynamic environments. However, to design a shape-changing mechanism suitable for small drones is very challenging due to extreme requirements raised by dimensional constraint, actuating limits, and weight restriction in Micro Air Vehicles (MAVs). A novel design method of morphing wings is proposed for small-scale aircrafts in this paper. The morphing wing is composed of a heterogeneous architecture, including three components: a longitudinal spar with pneumatic actuators, chordwise stiffening ribs with cable-driven metastructures, and a compliant skin. Through employing both pneumatic networks with hyperelastic behavior and modified pantographic metastructures with tunable stiffness, structural deformation along both spanwise and chordwise. Mechanical behaviors of this morphing wing were investigated thoroughly by theorical analysis, numerical verification, and experimental validation. Theorical predictions agree well with the results of 3D Finite Element Method (FEM). With optimal design determined through design of experiment (DOE) and FEM, prototyped morphing wings were fabricated accordingly. The aerodynamic performance was examined by a wind tunnel test with a Particle Image Velocimetry (PIV) instrument. Results demonstrate the efficiency and capacity of this morphing wing to adjust aerodynamic layout of aircraft in a low-speed airflow environment. This proposed design provides a promising solution applicable to small-scale aircrafts with morphing wings. |
| تدمد: | 2297-3079 |
| الوصول الحر: | https://explore.openaire.eu/search/publication?articleId=doi_dedup___::7379cb74a99f1d59ab89a0e3942ef391Test https://doi.org/10.3389/fmech.2021.814446Test |
| حقوق: | OPEN |
| رقم الانضمام: | edsair.doi.dedup.....7379cb74a99f1d59ab89a0e3942ef391 |
| قاعدة البيانات: | OpenAIRE |
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