The stiffened top skin of a wing structure is modelled as a panel has simply supported edges as shown in the figure below. Oc a The sheet is 4.7 mm thick and the stringers are spaced at b 0.6 m. Assume the dimension of the panel in spanwise direction is much longer than the chordwise direction. The material constants are: E 70 x 10 N/m2, Poisson's ratio v0.34. Determine the spanwise stress at which the sheet between the stringers will begin to buckle. Give your answer in MPa to three decimal places.

Structural Analysis
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Author:KASSIMALI, Aslam.
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Chapter2: Loads On Structures
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The stiffened top skin of a wing structure is modelled as a panel has simply
supported edges as shown in the figure below.
a
The sheet is 4.7 mm thick and the stringers are spaced at b 0.6 m. Assume
the dimension of the panel in spanwise direction is much longer than the
chordwise direction. The material constants are: E 70 x 10' N/m2, Poisson's
ratio v 0.34.
Determine the spanwise stress at which the sheet between the stringers will
begin to buckle. Give your answer in MPa to three decimal places.
Transcribed Image Text:The stiffened top skin of a wing structure is modelled as a panel has simply supported edges as shown in the figure below. a The sheet is 4.7 mm thick and the stringers are spaced at b 0.6 m. Assume the dimension of the panel in spanwise direction is much longer than the chordwise direction. The material constants are: E 70 x 10' N/m2, Poisson's ratio v 0.34. Determine the spanwise stress at which the sheet between the stringers will begin to buckle. Give your answer in MPa to three decimal places.
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