By T.H.G. Megson

*Aircraft constructions for Engineering scholars, 6th version, *is the best self-contained airplane buildings direction textual content. It covers all primary matters, together with elasticity, structural research, airworthiness and aeroelasticity. Now in its 6th variation, the writer has improved the book’s assurance of research and layout of composite fabrics to be used in plane, and has extra new, real-world and design-based examples, besides new end-of-chapter difficulties of various complexity.

- Expanded assurance of composite fabrics and constructions
- New sensible and design-based examples and difficulties in the course of the textual content relief figuring out and relate options to actual global purposes
- Updated and extra Matlab examples and workouts aid use of computational instruments in research and layout
- Available on-line educating and studying instruments contain downloadable Matlab code, options guide, and snapshot financial institution of figures from the book

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**Additional info for Aircraft Structures for Engineering Students, Sixth Edition**

**Example text**

33 below the elastic limit. 5. 4 A rectangular element in a linearly elastic, isotropic material is subjected to tensile stresses of 83 and 65 N/mm2 on mutually perpendicular planes. Determine the strain in the direction of each stress and in the direction perpendicular to both stresses. Find also the principal strains, the maximum shear stress, the maximum shear strain, and their directions at the point. 3. See Ex. 1. 52), 1 ex ¼ ð83 À 0:3 Â 65Þ ¼ 3:175 Â 10À4 200; 000 ey ¼ 1 ð65 À 0:3 Â 83Þ ¼ 2:005 Â 10À4 200; 000 ez ¼ À0:3 ð83 þ 65Þ ¼ À2:220 Â 10À4 200; 000 In this case, since there are no shear stresses on the given planes, sx and sy are principal stresses, so that ex and ey are the principal strains and are in the directions of sx and sy.

This value is predicted by simple beam theory (Chapter 16) and does not include the contribution to deflection of the shear strain. This was eliminated when we assumed that the slope of the neutral plane at the built-in end was zero. A more detailed examination of this effect is instructive. The shear strain at any point in the beam is given by Eq. 17): gxy ¼ À P ðb2 À 4y2 Þ 8IG and is obviously independent of x. Therefore, at all points on the neutral plane, the shear strain is constant and equal to gxy ¼ À Pb2 8IG which amounts to a rotation of the neutral plane, as shown in Fig.

Timoshenko and Goodier1 consider a variety of polynomials for f and determine the associated loading conditions for a variety of rectangular sheets. Some of these cases are quoted here. 1 Consider the stress function f ¼ Ax2 þ Bxy þ Cy2 where A, B, and C are constants. 9) is identically satisfied, since each term becomes zero on substituting for f. The stresses follow from sx ¼ @2f ¼ 2C @y2 sy ¼ @2f ¼ 2A @x2 txy ¼ À @2f ¼ ÀB @x @y To produce these stresses at any point in a rectangular sheet, we require loading conditions providing the boundary stresses shown in Fig.