The purpose of this book is to illustrate step by step the design
of the Composite Wing Structure of the external wing for an
Unmanned Aerial Vehicle- UAV. The design is conducted using
software tools for Finite Element Analysis, such as, NASTRAN and
ANSYS to find the structural integrity limits for composite
materials and fittings. Data for this study were obtained from
AEROTECH Research Group at Universidad de San Buenaventura, Bogota,
Colombia. Finite Element Methods are used in order to evaluate the
static strength, maximum stresses and buckling behavior of
composite structures. Sections, such as spars, webs and caps, ribs,
skins and stringers assemblies are analyzed to get the best
strength to weight ratio and its manufacturing procedure. The
analysis should be especially useful to professionals in Aerospace
and Mechanical Engineering, or anyone else who may be considering
utilizing design methodologies to analyze structural configurations
of composite structures using Finite Element Methods and the
conceptual manufacturing procedures for further fabrication.
General
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