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Question 1: Consider a stiffened beam using the "Q1 Beam" as provided in the Individual Parameters. The beam is assumed to consist of stiffeners carrying only direct stress and shear panels carrying only shear stress. The material used has E = 11500 ksi, G = 4100 ksi, σty = 52 ksi, σcy = 41 ksi, σsy = 39 ksi.
(a) Calculate the stiffener axial loads (lbf) at the end of each beam segment and the shear flows (lbf/in) along each panel edge.
(b) Size the beam by determining stiffener areas (in2) and shear panel thicknesses (in).
For stiffeners, size to yield stress (in tension or compression), considering the maximum load in each segment (i.e. each segment can have a different area). For the shear panels, size to yield stress (in shear, maximum in each panel) or shear buckling, whichever is critical. For the buckling calculation, assume that the shear panels are simply supported on all edges, and for the tapered panels use the smaller edge dimensions (i.e. assume a rectangular panel with the smaller of the width and height edge dimensions). When sizing, use a minimum possible area of 0.25 in2 and a minimum possible thickness of 0.0048 in.
The following data has been obtained experimentally for a composite based on an unidirectional carbon-epoxy prepreg (MR50 carbon fiber at 63% by volume in LTM25 epoxy). Determine if the restrictions on elastic constants are satisfied.
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