Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

Problems 83

Fig. P.3.4

τmax(atcenterofeachside)=−

a

2

G

dθ

dz

dθ

dz

=

15

√

3 T

Ga^4

w=

1

2 a

dθ

dz

(y^3 − 3 x^2 y).

P.3.5 DeterminethemaximumshearstressandtherateoftwistintermsoftheappliedtorqueTforthesection
comprisingnarrowrectangularstripsshowninFig.P.3.5.

Fig. P.3.5

Ans. τmax= 3 T/( 2 a+b)t^2 ,dθ/dz= 3 T/G( 2 a+b)t^3.