scholarly journals Aeroelastic tailoring using crenellated skins-modelling and experiment

2017 ◽  
Vol 4 (2) ◽  
pp. 93-124
Author(s):  
Guillaume Francois ◽  
Jonathan E. Cooper ◽  
Paul M. Weaver
Keyword(s):  
Aeroelastic Tailoring

Effect of Aeroelastic Tailoring of Composite Wing Skin Laminates on Controllability of Aircraft

2021 ◽  
Author(s):  
Varakini Sanmugadas ◽  
Rikin Gupta ◽  
Wei Zhao ◽  
Rakesh K. Kapania ◽  
David K. Schmidt
Keyword(s):  
Aeroelastic Tailoring ◽  
Wing Skin ◽  
Composite Wing

Aeroelastic tailoring of composite aircraft wings

2017 ◽  
Author(s):  
Mihai Mihaila-Andres ◽  
Ciprian Larco ◽  
Paul-Virgil Rosu ◽  
Constantin Rotaru
Keyword(s):  
Aeroelastic Tailoring ◽  
Aircraft Wings

Aeroelastic tailoring using fiber orientation and topology optimization

2012 ◽  
Vol 46 (5) ◽  
pp. 663-677 ◽  
Author(s):  
D. M. De Leon ◽  
C. E. de Souza ◽  
J. S. O. Fonseca ◽  
R. G. A. da Silva
Keyword(s):  
Topology Optimization ◽  
Fiber Orientation ◽  
Aeroelastic Tailoring ◽  
And Topology

Aeroelastic Tailoring of Helicopter Blades

2013 ◽  
Author(s):  
Donatien Cornette ◽  
Benjamin Kerdreux ◽  
Yves Gourinat ◽  
Guilhem Michon
Keyword(s):  
Dynamic Behaviour ◽  
Vertical Shear ◽  
Dynamic Loads ◽  
Modal Approach ◽  
Aeroelastic Tailoring ◽  
Helicopter Blades ◽  
Shear Modification ◽  
Elastic Couplings ◽  
The Impact ◽  
Aerodynamic Lift

The dynamic loads transmitted from the rotor to the airframe are responsible for vibrations, discomfort and alternate stress of components. A new and promising way to minimize vibration is to reduce dynamic loads at their source by performing an aeroelastic optimization of the rotor. This optimization is done thanks to couplings between the flapwise-bending motion and the torsion motion. The impact of elastic couplings (composite anisotropy) on the blade dynamic behaviour and on dynamic loads are evaluated in this paper. Firstly, analytical results, based on a purely linear modal approach, are given to understand the influence of those couplings in terms of frequency placement, aerodynamic lift load and vertical shear modification. Then, those elastic couplings are introduced on a simplified but representative blade (homogeneous beam with constant chord) and results are presented.

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