Chapter 12: Structural components of aircraft

Example 12.1 Pg.No. 390

In [7]:
from __future__ import division
import math

D=4              #diameter of rivet(mm)
t_skin=2.5         #thickness of fuselage skin(mm)
t_strap=1.2          #thickness of straps (mm)
T=120               #shear stress (N/mm^2)
A=math.pi*D**2/4    #rivet area
Pfb=2*A*T

b=Pfb/t_skin/12.5/10+4
print "allowable rivet spacing = %2.1f mm \n"%(b)

allowable rivet spacing = 13.7 mm

Example 12.2 Pg.No.392

In [11]:
from __future__ import division
import math

l1=20          #distace between A&D (mm)
l2=25          #distace between C&D (mm)
l3=75          #distace between C&force location (mm)
P=5        #external load(kN)
r=(l1**2+l2**2)**0.5
sum_r2=2*l1**2+4*r**2

#eqn 12.6 S=Pe*r/Sum(r2)
Pe=P*l3
S=Pe/sum_r2*r
print "Resultant shear force in the A and B = %2.2f kN\n"%(S)

Resultant shear force in the A and B = 2.45 kN
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