Aerospace Stiffened Structures - Engineering Assignment Help

Assignment Task
 

Question 1 The tapered stiffened beam below is loaded by forces as shown. The beam is assumed to consist of stiffeners carrying only direct stress and shear panels carrying only shear stress. The material used has E = 10500 ksi, G = 3900 ksi, ty = 48 ksi,cy = 38 ksi, sy = 37 ksi. The values of a, b, A, C, E are taken from Question 0.

(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 0.30 in2 and a minimum possible thickness of 0.0052 in.

Question 2  The three-cell structure shown below uses stiffeners connected with shear panels. Note that the curved panel between stiffeners 1 and 3 is semi-circular. The structure is under the action of forces and moments as shown. Assume the shear panels do not carry any direct stress. The material properties are: E = 72 GPa, G = 28 GPa, ty = 270 MPa, cy = 240 MPa, y = 170 MPa. The values of a, b, B, D, F are taken from Question 0.

(a) Calculate the shear flow (N/mm) in each panel and determine the critical margin of safety in shear (not buckling or any other mode). 

(b) Re-size the thickness (mm) of the shear panels to reduce the cross-sectional area to achieve the following design requirements :

1. area fraction A/A0 less than 0.30 2. all margins of safety greater than or equal to 0.0 3. no panel thickness less than 0.2015 mm The area fraction is calculated as A/A0, where A is the cross-sectional area of all panels combined, and A0 is the cross-sectional area of all panels using thicknesses as shown in the figure below. In re-sizing the panels, you should consider that the beam cross-section dimensions and stiffener areas are fixed, and that only the panel thicknesses can be varied. You should only consider failure due to shear (not buckling or any other mode).

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