Aircraft Structure for Engineering (Record no. 4087)

MARC details
000 -LEADER
fixed length control field 08143nam a2200169Ia 4500
003 - CONTROL NUMBER IDENTIFIER
control field OSt
005 - DATE AND TIME OF LATEST TRANSACTION
control field 20190219150846.0
008 - FIXED-LENGTH DATA ELEMENTS--GENERAL INFORMATION
fixed length control field 140801s2013 xx 000 0 und d
020 ## - INTERNATIONAL STANDARD BOOK NUMBER
International Standard Book Number 9789382291053
100 ## - MAIN ENTRY--PERSONAL NAME
Personal name Megson, T H G
245 ## - TITLE STATEMENT
Title Aircraft Structure for Engineering
260 ## - PUBLICATION, DISTRIBUTION, ETC. (IMPRINT)
Name of publisher, distributor, etc Elsevier Pub
Date of publication, distribution, etc 2013
500 ## - GENERAL NOTE
General note PART A. Fundamentals of Structural Analysis<br/><br/>Section A1 Elasticity<br/><br/>Chapter 1. Basic elasticity<br/><br/>1.1 Stress<br/><br/>1.2 Notation for forces and stresses<br/><br/>1.3 Equations of equilibrium<br/><br/>1.4 Plane stress<br/><br/>1.5 Boundary conditions<br/><br/>1.6 Determination of stresses on inclined planes<br/><br/>1.7 Principal stresses<br/><br/>1.8 Mohr's circle of stress<br/><br/>1.9 Strain<br/><br/>1.10 Compatibility equations<br/><br/>1.11 Plane strain<br/><br/>1.12 Determination of strains on inclined planes<br/><br/>1.13 Principal strains<br/><br/>1.14 Mohr's circle of strain<br/><br/>1.15 Stress–strain relationships<br/><br/>1.16 Experimental measurement of surface strains<br/><br/>REFERENCES<br/><br/>Additional Reading<br/><br/>Chapter 2. Two-dimensional problems in elasticity<br/><br/>2.1 Two-dimensional problems<br/><br/>2.2 Stress functions<br/><br/>2.3 Inverse and semi-inverse methods<br/><br/>2.4 St. venant's principle<br/><br/>2.5 Displacements<br/><br/>2.6 Bending of an end-loaded cantilever<br/><br/>REFERENCE<br/><br/>Chapter 3. Torsion of solid sections<br/><br/>3.1 Prandtl stress function solution<br/><br/>3.2 St. Venant warping function solution<br/><br/>3.3 The membrane analogy<br/><br/>3.4 Torsion of a narrow rectangular strip<br/><br/>REFERENCES<br/><br/>Section A2 Virtual work, energy, and matrix methods<br/><br/>Chapter 4. Virtual work and energy methods<br/><br/>4.1 Work<br/><br/>4.2 Principle of virtual work<br/><br/>4.3 Applications of the principle of virtual work<br/><br/>REFERENCE<br/><br/>Chapter 5. Energy methods<br/><br/>5.1 Strain energy and complementary energy<br/><br/>5.2 Principle of the stationary value of the total complementary energy<br/><br/>5.3 Application to deflection problems<br/><br/>5.4 Application to the solution of statically indeterminate systems<br/><br/>5.5 Unit load method<br/><br/>5.6 Flexibility method<br/><br/>5.7 Total potential energy<br/><br/>5.8 Principle of the stationary value of the total potential energy<br/><br/>5.9 Principle of superposition<br/><br/>5.10 Reciprocal theorem<br/><br/>5.11 Temperature effects<br/><br/>REFERENCES<br/><br/>Further reading<br/><br/>Chapter 6. Matrix methods<br/><br/>6.1 Notation<br/><br/>6.2 Stiffness matrix for an elastic spring<br/><br/>6.3 Stiffness matrix for two elastic springs in line<br/><br/>6.4 Matrix analysis of pin-jointed frameworks<br/><br/>6.5 Application to statically indeterminate frameworks<br/><br/>6.6 Matrix analysis of space frames<br/><br/>6.7 Stiffness matrix for a uniform beam<br/><br/>6.8 Finite element method for continuum structures<br/><br/>REFERENCES<br/><br/>Further reading<br/><br/>Section A3 Thin plate theory<br/><br/>Chapter 7. Bending of thin plates<br/><br/>7.1 Pure bending of thin plates<br/><br/>7.2 Plates subjected to bending and twisting<br/><br/>7.3 Plates subjected to a distributed transverse load<br/><br/>7.4 Combined bending and in-plane loading of a thin rectangular plate<br/><br/>7.5 Bending of thin plates having a small initial curvature<br/><br/>7.6 Energy method for the bending of thin plates<br/><br/>Further reading<br/><br/>Section A4 Structural instability<br/><br/>Chapter 8. Columns<br/><br/>8.1 Euler buckling of columns<br/><br/>8.2 Inelastic buckling<br/><br/>8.3 Effect of initial imperfections<br/><br/>8.4 Stability of beams under transverse and axial loads<br/><br/>8.5 Energy method for the calculation of buckling loads in columns<br/><br/>8.6 Flexural–torsional buckling of thin-walled columns<br/><br/>REFERENCES<br/><br/>Chapter 9. Thin plates<br/><br/>9.1 Buckling of thin plates<br/><br/>9.2 Inelastic buckling of plates<br/><br/>9.3 Experimental determination of the critical load for a flat plate<br/><br/>9.4 Local instability<br/><br/>9.5 Instability of stiffened panels<br/><br/>9.6 Failure stress in plates and stiffened panels<br/><br/>9.7 Tension field beams<br/><br/>REFERENCES<br/><br/>Section A5 Vibration of structures<br/><br/>Chapter 10. Structural vibration<br/><br/>10.1 Oscillation of mass–spring systems<br/><br/>10.2 Oscillation of beams<br/><br/>10.3 Approximate methods for determining natural frequencies<br/><br/>PART B. Analysis Of Aircraft Structures<br/><br/>Section B1 Principles of stressed skin construction<br/><br/>Chapter 11. Materials<br/><br/>11.1 Aluminum alloys<br/><br/>11.2 Steel<br/><br/>11.3 Titanium<br/><br/>11.4 Plastics<br/><br/>11.5 Glass<br/><br/>11.6 Composite materials<br/><br/>11.7 Properties of materials<br/><br/>Chapter 12. Structural components of aircraft<br/><br/>12.1 Loads on structural components<br/><br/>12.2 Function of structural components<br/><br/>12.3 Fabrication of structural components<br/><br/>12.4 Connections<br/><br/>REFERENCE<br/><br/>Section B2 Airworthiness and airframe loads<br/><br/>Chapter 13. Airworthiness<br/><br/>13.1 Factors of safety-flight envelope<br/><br/>13.2 Load factor determination<br/><br/>REFERENCE<br/><br/>Chapter 14. Airframe loads<br/><br/>14.1 Aircraft inertia loads<br/><br/>14.2 Symmetric maneuver loads<br/><br/>14.3 Normal accelerations associated with various types of maneuver<br/><br/>14.4 Gust loads<br/><br/>REFERENCES<br/><br/>Chapter 15. Fatigue<br/><br/>15.1 Safe life and fail-safe structures<br/><br/>15.2 Designing against fatigue<br/><br/>15.3 Fatigue strength of components<br/><br/>15.4 Prediction of aircraft fatigue life<br/><br/>15.5 Crack propagation<br/><br/>REFERENCES<br/><br/>Further reading<br/><br/>Section B3 Bending, shear and torsion of thin-walled beams<br/><br/>Chapter 16. Bending of open and closed, thin-walled beams<br/><br/>16.1 Symmetrical bending<br/><br/>16.2 Unsymmetrical bending<br/><br/>16.3 Deflections due to bending<br/><br/>16.4 Calculation of section properties<br/><br/>16.5 Applicability of bending theory<br/><br/>16.6 Temperature effects<br/><br/>REFERENCE<br/><br/>Chapter 17. Shear of beams<br/><br/>17.1 General stress, strain, and displacement relationships for open and single-cell closed section thin-walled beams<br/><br/>17.2 Shear of open section beams<br/><br/>17.3 Shear of closed section beams<br/><br/>REFERENCE<br/><br/>Chapter 18. Torsion of beams<br/><br/>18.1 Torsion of closed section beams<br/><br/>18.2 Torsion of open section beams<br/><br/>Chapter 19. Combined open and closed section beams<br/><br/>19.1 Bending<br/><br/>19.2 Shear<br/><br/>19.3 Torsion<br/><br/>Chapter 20. Structural idealization<br/><br/>20.1 Principle<br/><br/>20.2 Idealization of a panel<br/><br/>20.3 Effect of idealization on the analysis of open and closed section beams<br/><br/>20.4 Deflection of open and closed section beams<br/><br/>Section B4 Stress analysis of aircraft components<br/><br/>Chapter 21. Wing spars and box beams<br/><br/>21.1 Tapered wing spar<br/><br/>21.2 Open and closed section beams<br/><br/>21.3 Beams having variable stringer areas<br/><br/>Chapter 22. Fuselages<br/><br/>22.1 Bending<br/><br/>22.2 Shear<br/><br/>22.3 Torsion<br/><br/>22.4 Cut-outs in fuselages<br/><br/>Chapter 23. Wings<br/><br/>23.1 Three-boom shell<br/><br/>23.2 Bending<br/><br/>23.3 Torsion<br/><br/>23.4 Shear<br/><br/>23.5 Shear center<br/><br/>23.6 Tapered wings<br/><br/>23.7 Deflections<br/><br/>23.8 Cut-outs in wings<br/><br/>Chapter 24. Fuselage frames and wing ribs<br/><br/>24.1 Principles of stiffener/web construction<br/><br/>24.2 Fuselage frames<br/><br/>24.3 Wing ribs<br/><br/>Chapter 25. Laminated composite structures<br/><br/>25.1 Elastic constants of a simple lamina<br/><br/>25.2 Stress–strain relationships for an orthotropic ply (macro approach)<br/><br/>25.3 Thin-walled composite beams<br/><br/>REFERENCES<br/><br/>Section B5 Structural and loading discontinuities<br/><br/>Chapter 26. Closed section beams<br/><br/>26.1 General aspects<br/><br/>26.2 Shear stress distribution at a built-in end of a closed section beam<br/><br/>26.3 Thin-walled rectangular section beam subjected to torsion<br/><br/>26.4 Shear lag<br/><br/>REFERENCE<br/><br/>Chapter 27. Open section beams<br/><br/>27.1 I-Section beam subjected to torsion<br/><br/>27.2 Torsion of an arbitrary section beam<br/><br/>27.3 Distributed torque loading<br/><br/>27.4 Extension of the theory to allow for general systems of loading<br/><br/>27.5 Moment couple (bimoment)<br/><br/>REFERENCES<br/><br/>Section B6 Introduction to aeroelasticity<br/><br/>Chapter 28. Wing problems<br/><br/>28.1 Types of problem<br/><br/>28.2 Load distribution and divergence<br/><br/>28.3 Control effectiveness and reversal<br/><br/>28.4 Introduction to “flutter”<br/><br/>REFERENCES<br/><br/>Appendix: Design of a rear fuselage<br/><br/>A.1 Specification<br/><br/>A.2 Data<br/><br/>A.3 Initial calculations<br/><br/>A.4 Balancing out calculations<br/><br/>A.5 Fuselage loads<br/><br/>A.6 Fuselage design calculations
700 ## - ADDED ENTRY--PERSONAL NAME
Personal name T H G Megson
856 ## - ELECTRONIC LOCATION AND ACCESS
Uniform Resource Identifier <a href="https://books.google.co.in/books?id=z39Y6CGu7OsC&printsec=frontcover&dq=aircraft+structures+for+engineering+students&hl=en&sa=X&ved=0ahUKEwj6_tKvucfgAhWcw4sBHQFLDkUQ6AEILTAB#v=onepage&q=aircraft%20structures%20for%20engineering%20students&f=false">https://books.google.co.in/books?id=z39Y6CGu7OsC&printsec=frontcover&dq=aircraft+structures+for+engineering+students&hl=en&sa=X&ved=0ahUKEwj6_tKvucfgAhWcw4sBHQFLDkUQ6AEILTAB#v=onepage&q=aircraft%20structures%20for%20engineering%20students&f=false</a>
942 ## - ADDED ENTRY ELEMENTS (KOHA)
Source of classification or shelving scheme Dewey Decimal Classification
Koha item type Books
Holdings
Withdrawn status Lost status Source of classification or shelving scheme Damaged status Not for loan Collection code Home library Current library Shelving location Date acquired Cost, normal purchase price Total Checkouts Full call number Barcode Date last seen Date checked out Price effective from Koha item type
    Dewey Decimal Classification   Not For Loan Reference Amity Central Library Amity Central Library ASET Aerospace 30/12/2013 1895.00 1 629.13431 MEG-A 19517 19/02/2019 12/04/2016 30/12/2013 Reference Book
Web Counter

Powered by Koha