Analysis of the Ultimate Strength and Optimum Proportions of Multiweb Wing Structures Page: 14 of 35
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NACA TN 3633
(2) Determine the solidity from figure 4. Find twIbs fromequa-
tion (13); thus,
2Sh
Find bslts from equation (9a); thus,
b C 1/3(\1/2 bS
or, from equation (9b),
b_ /1 bW bS1/2
The larger bs/tS value must be used to determine web spacing.
Buckling Below Limit Load
Many structures must satisfy not only strength and stiffness criteria
but also a requirement that there be no skin buckling below design limit
2
load; that is, -Mf. For each hitS value, there is one point on
the optimum curve which defines a structure that will buckle at limit -
load. Structures designed for higher index values will buckle above
limit load and structures designed for lower index values will buckle
below limit load. In order to determine the critical value of bs/tS
for any h/tS value, let
Mcr = Mf (18)
For the 7075-T6 aluminum allby, buckling will be elastic and the stress
distribution will be triangular. Hence, in equation (5),
6
and13
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Rosen, B. Walter. Analysis of the Ultimate Strength and Optimum Proportions of Multiweb Wing Structures, report, March 1956; (https://digital.library.unt.edu/ark:/67531/metadc57902/m1/14/: accessed July 16, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.