Optimum stacking sequence design of composite materials Part I: Constant stiffness design

2009 ◽  
Vol 90 (1) ◽  
pp. 1-11 ◽  
Author(s):  
Hossein Ghiasi ◽  
Damiano Pasini ◽  
Larry Lessard
Keyword(s):  
Composite Materials ◽  
Stacking Sequence ◽  
Sequence Design ◽  
Constant Stiffness ◽  
Stiffness Design

scholarly journals Optimum stacking sequence design of composite materials Part II: Variable stiffness design

2010 ◽  
Vol 93 (1) ◽  
pp. 1-13 ◽  
Author(s):  
Hossein Ghiasi ◽  
Kazem Fayazbakhsh ◽  
Damiano Pasini ◽  
Larry Lessard
Keyword(s):  
Composite Materials ◽  
Variable Stiffness ◽  
Stacking Sequence ◽  
Sequence Design ◽  
Stiffness Design

scholarly journals Simulation and Test of Discrete Mobile Surfaces for a RC-Aircraft

Aerospace ◽  
2019 ◽  
Vol 6 (11) ◽  
pp. 122
Author(s):  
Francesco Nicassio ◽  
Gennaro Scarselli
Keyword(s):  
Composite Materials ◽  
Unmanned Aerial Vehicles ◽  
Composite Plate ◽  
Stacking Sequence ◽  
Total Thickness ◽  
Aerodynamic Efficiency ◽  
Aerodynamic Pressure ◽  
Aerial Vehicles ◽  
Discrete Surface ◽  
Lever Effect

Morphing structures suitable for unmanned aerial vehicles (UAVs) have been investigated for several years. This paper presents a novel lightweight, morphing concept based on the exploitation of the “lever effect” of a bistable composite plate that can be integrated in an UAV horizontal tail. Flight dynamics equations are solved in Simulink environment, thus being able to simulate and compare different flight conditions with conventional and bistable command surfaces. Subsequently, bistable plates are built by using composite materials, paying particular attention to dimensions, asymmetric stacking sequence and total thickness needed to achieve bistability. NACA0011 airfoil is chosen for proving this concept. Wind tunnel tests demonstrate that the discrete surface is capable of withstanding the aerodynamic pressure. A remotely piloted vehicle is employed to test the discrete horizontal tail command during the take-off. The results show that, choosing a proper configuration of constraints, stacking sequence and aspect ratio for the bistable laminate, it is possible to tailor the snap-through mechanism. The proposed concept appears lighter and increases aerodynamic efficiency when compared to conventional UAV command surfaces.

Multi-step blended stacking sequence design of panel assemblies with buckling constraints

2009 ◽  
Vol 40 (4) ◽  
pp. 329-336 ◽  
Author(s):  
Samuel T. IJsselmuiden ◽  
Mostafa M. Abdalla ◽  
Omprakash Seresta ◽  
Zafer Gürdal
Keyword(s):  
Stacking Sequence ◽  
Sequence Design ◽  
Buckling Constraints
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