Aircraft Fuselage Loading
A new passenger plane is being designed with a composite fuselage skin. The
fibers will be placed in four different directions; 1) along the length of the
fuselage or longitudinal (long) direction, 2) around the circumferential (circ)
direction, 3) 30o from
the longitudinal fibers, and 4) -30o from the longitudinal fibers.
The skin is made from multiple layers of graphite reinforced epoxy, but the fibers
are only placed in the four directions as described.
What is known:
- The stress in the longitudinal direction, σlong,
is 50 ksi.
- The stress in the circumferential direction, σcirc,
is 25 ksi.
- The twisting of the fuselage causes a shear stress, τtwist of