Aircraft structure problem


question in the attached file.
1.The tapered stiffened beam below is loaded by forces S1, S2 and S3 as shown. The beam is assumed to consist of stiffeners carrying only direct stress and shear panels carrying only shear stress. The values of a and S are taken from Question 0.
2.
The three-cell cross-section shown below uses 9 stiffeners connected with shear panels, where the outer panel between booms 1 and 6 is semi-circular and all other panels are straight. 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 = 250 MPa, ?cy = 225 MPa, ?y = 150 MPa, ? = 0.3. The values of a and S are taken from Question 0.

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Other Engineering: Aircraft structure problem
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