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Analysis of circular Shell-Supported Frames

When shell~supported rings are externally loaded.
the agolied loading is resisted primarily by a system of
shearing forces within the shell.

The VQ/I and T/BA. shear-flow distribution, which—"‘"“
has been used frequently in past analyses, is consistent
with the assumption that the ring being loaded is rigid.
For smallwdiametsr shells with sturdy rings, this distriw

Vbution has proved reasonably satisfactory for assignment
purposes. However; as the size of airplanes increases,
the rings become relatiVely more flexible so that the
assumption of infinite ring stiffness may sometimes
introduce errors of several hundred percent in ring
designs Therefore, the necessity for a more accurate
analysis becomes apparent; Such an analysis_must con-
sider the finite stiffness of the ring.

Because of the added complexity involved in evaluating
the effect of finite ring stiffness, it is desirable to
present the results in the form of coefficient curves cal-
culated for typical cases. Then the tending moment, axial
load and transverse shear in a ring, and the corresponding
shear flow acting on the ring from the supporting shell .
may be readily obtained from these curVes by proper inter—
polation and superposition.

Ehis report is but the start of the contemplated ring
study and covers only the ease of a complete circular frame
subjected to a system of coplanar loadings. The method
will, in later reports, be extended to more general appli—
cations which include the following problems:

(1) Analysis of wing~fuselage intersection including
design data for the main frames, deflection of the main
frames, skin shear flows, and modification of axial stresses
(in the vicinity of the main frames) as a result of ring
flexibility.