Fluid-Structure Interaction Simulation for the Design of Bio-Inspired Micro Air Vehicle Wings

2012 ◽  
Author(s):  
Thomas Combes ◽  
Arif Malik ◽  
Gotz Bramesfeld
Keyword(s):  
Fluid Structure Interaction ◽  
Micro Air Vehicle ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Air Vehicle ◽  
Interaction Simulation

Efficient Fluid-Structure Interaction Method for Conceptual Design of Flexible, Fixed-Wing Micro-Air-Vehicle Wings

AIAA Journal ◽  
2015 ◽  
Vol 53 (6) ◽  
pp. 1442-1454 ◽  
Author(s):  
Thomas P. Combes ◽  
Arif S. Malik ◽  
Götz Bramesfeld ◽  
Mark W. McQuilling
Keyword(s):  
Conceptual Design ◽  
Fluid Structure Interaction ◽  
Micro Air Vehicle ◽  
Interaction Method ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Air Vehicle

scholarly journals Fluid–structure interaction simulation on flight performance of a dragonfly wing under different pterostigma weights

2021 ◽  
Vol 37 ◽  
pp. 216-229
Author(s):  
Yung Jeh Chu ◽  
Poo Balan Ganesan ◽  
Mohamad Azlin Ali
Keyword(s):  
Optimization Design ◽  
Fluid Structure Interaction ◽  
Spatial Location ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Dragonfly Wing ◽  
Interaction Simulation ◽  
Wing Performance ◽  
Drag Ratio ◽  
Lift To Drag Ratio

Abstract The dragonfly wings provide insights for designing an efficient biomimetic micro air vehicle (BMAV). In this regard, this study focuses on investigating the effect of the pterostigma weight loading and its spatial location on the forewings of dragonfly by using the fluid–structure interaction simulation. This study also investigates the effect of change in the wing elasticity and density on the wing performance. The forewing, which mimics the real dragonfly wing, is flat with a 47.5 mm span and a 0.4 mm thickness. The wing was set to cruise at 3 m/s with a constant flapping motion at a frequency of 25 Hz. This study shows that a small increase of pterostigma loading (11% of wing weight) at the tip of the wing significantly improves the lift to drag ratio, CL/CD, which has 129.16% increment in comparison with no loading. The lift to drag ratio depends on the pterostigma location, pterostigma loading, elastic modulus and density. The results of this study can be used as a reference in future BMAV wing optimization design.

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