Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

22.2 Bending 589

Fig.22.2

Idealized section of a multicell wing.

Fig.22.3

Wing section of Example 22.1.

Table 22.1

Boom y(mm) σz(N/mm^2 )

1 165 61.2

2 230 85.3

3 200 74.2

4 − 200 −74.2

5 − 230 −85.3

6 − 165 −61.2

inwhich

Ixy= 2 ( 2580 × 1652 + 3880 × 2302 + 3230 × 2002 )= 809 × 106 mm^4

Hence,

σz=

300 × 106

809 × 106

y=0.371y (ii)

ThesolutionisnowcompletedinTable22.1inwhichpositivedirectstressesaretensileandnegative
directstressescompressive.