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Aircraft Structures for Engineering Students 4th Edition Solutions Manual PDF
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  • ENG101
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  • University Of San Andrés (UdeSA )
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  • Aircraft Structures For Engineering Students

Complete Answers Solutions Manual PDF for Aircraft Structures for Engineering Students 4th Edition by T.H.G Megson. Includes the answers for all of the exercises of the book.

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  • March 20, 2024
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  • 2007/2008
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,Solution-1-H6739.tex 24/1/2007 9: 28 Page 1




Aircraft Structures
for engineering students
Fourth Edition

Solutions Manual




T. H. G. Megson

,This page intentionally left blank

, Solution-1-H6739.tex 24/1/2007 9: 28 Page 3




Solutions Manual


Solutions to Chapter 1 Problems
S.1.1

The principal stresses are given directly by Eqs (1.11) and (1.12) in which
σx = 80 N/mm2 , σy = 0 (or vice versa) and τxy = 45 N/mm2 . Thus, from Eq. (1.11)

80 1  2
σI = + 80 + 4 × 452
2 2
i.e.
σI = 100.2 N/mm2
From Eq. (1.12)
80 1  2
σII = − 80 + 4 × 452
2 2
i.e.
σII = −20.2 N/mm2
The directions of the principal stresses are defined by the angle θ in Fig. 1.8(b) in
which θ is given by Eq. (1.10). Hence
2 × 45
tan 2θ = = 1.125
80 − 0
which gives
θ = 24◦ 11 and θ = 114◦ 11
It is clear from the derivation of Eqs (1.11) and (1.12) that the first value of θ
corresponds to σI while the second value corresponds to σII .
Finally, the maximum shear stress is obtained from either of Eqs (1.14) or (1.15).
Hence from Eq. (1.15)

100.2 − (−20.2)
τmax = = 60.2 N/mm2
2
and will act on planes at 45◦ to the principal planes.

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