Aircraft Structures for Engineering Students 4E Megson , T.H.G (구조역학 4판 대학교재솔루션 ) 솔루션
Aircraft Structures for Engineering Students 4E Megson , T.H.G (구조역학 4판 대학교재솔루션 ) 솔루션
Aircraft Structures for Engineering Students 4E Megson , T.H.G (구조역학 4판 대학교재솔루션 )
Aircraft Structures for Engineering Students 4판 솔루션(구조역학) Megson T.H.G 저 2007. 2. 25
Aircraft Structures
for engineering students
Fourth Edition
Solutions Manual
T. H. G. Megson
This page intentionally left blank
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) σI = i.e. σI = 100.2 N/mm2 From Eq. (1.12) σII = i.e. σII = ?20.2 N/mm2 The directions of the principal stresses are de?ned by the angle θ in Fig. 1.8(b) in which θ is given by Eq. (1.10). Hence tan 2θ = which gives θ = 24? 11 and θ = 114? 11 2 × 45 = 1.125 80 ? 0 80 1 ? 802 + 4 × 452 2 2 80 1 802 + 4 × 452 + 2 2
It is clear from the derivation of Eqs (1.11) and (1.12) that the ?rst 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) τmax = 100.2 ? (?20.2) = 60.2 N/mm2 2
and will act
자료출처 : http://www.ALLReport.co.kr/search/Detail.asp?pk=10974931&sid=sanghyun7776&key=
[문서정보]
문서분량 : 354 Page
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자료제목 : Aircraft Structures for Engineering Students 4E Megson , T.H.G (구조역학 4판 대학교재솔루션 )
파일이름 : Aircraft Structure 4판 megson 솔루션구조역학 4판.pdf
키워드 : 구조역학,Aircraft,Structures,Engineering,Students,4판,솔루션,for,4E,Megson
자료No(pk) : 10974931
Aircraft Structures for Engineering Students 4E Megson , T.H.G (구조역학 4판 대학교재솔루션 )
Aircraft Structures for Engineering Students 4판 솔루션(구조역학) Megson T.H.G 저 2007. 2. 25
Aircraft Structures
for engineering students
Fourth Edition
Solutions Manual
T. H. G. Megson
This page intentionally left blank
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) σI = i.e. σI = 100.2 N/mm2 From Eq. (1.12) σII = i.e. σII = ?20.2 N/mm2 The directions of the principal stresses are de?ned by the angle θ in Fig. 1.8(b) in which θ is given by Eq. (1.10). Hence tan 2θ = which gives θ = 24? 11 and θ = 114? 11 2 × 45 = 1.125 80 ? 0 80 1 ? 802 + 4 × 452 2 2 80 1 802 + 4 × 452 + 2 2
It is clear from the derivation of Eqs (1.11) and (1.12) that the ?rst 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) τmax = 100.2 ? (?20.2) = 60.2 N/mm2 2
and will act
자료출처 : http://www.ALLReport.co.kr/search/Detail.asp?pk=10974931&sid=sanghyun7776&key=
[문서정보]
문서분량 : 354 Page
파일종류 : PDF 파일
자료제목 : Aircraft Structures for Engineering Students 4E Megson , T.H.G (구조역학 4판 대학교재솔루션 )
파일이름 : Aircraft Structure 4판 megson 솔루션구조역학 4판.pdf
키워드 : 구조역학,Aircraft,Structures,Engineering,Students,4판,솔루션,for,4E,Megson
자료No(pk) : 10974931
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