Abstract:
This project studies theoretically and practically the composite materials used in
aircraft structure to save the weight resulting from using other materials also by designing
a tapered wing span using (CATIA) drawing and then dividing it into ten equal segments
to know the values of bending moments and shear loads in each segment along the wing
spar after applying the loads on it by using ANSYS application to prove that the resulting
deformation is very small and can be neglected and carbon fiber is suitable to fabricate
tapered wing spar.
