Page 459 - Aircraft Stuctures for Engineering Student

440 Stress analysis of aircraft components

A B C

D

j', kN
I 1
1OOOmm I 2000mm
Fig. P.10.16

Ans. q(ABEF) = 4N/mm, q(BCDE) = 2N/mm.
PBE increases linearly from zero at B to 6000 N (tension) at E
Pm and PCB increase linearly from zero at A and C to 4000N (compression) at B

P.10.17 Calculate the shear flows in the web panels and direct load in the flanges
and stiffeners of the beam shown in Fig. P.10.17 if the web panels resist shear stresses
only.
Ans. q1 = 21.6N/mm, q2 = -1.6N/mm, q3 = 10N/mm.

Pc = 0, PB = 6480 N (tension), PA = 9480 N (tension)
PF = 0, PG = 480N (tension), PH = 2520N (compression)
PE in BEG = 2320N (compression), PD in ED = 6928 N (tension)
PD in CD = 4320N (tension), PD in DF = 320N (tension)

mm

mm

1 /
300 mm 300 mm

Fig. P.10.17