AE362 Aerospace Structures (4-0) 4

Course Description:
Main structural elements in aircraft and spacecraft. Long, flexible space trusses. Torsional and flexural analysis of open and closed section box beams. Bending of unsymmetrical sections. Rib analysis. The stability of long and short columns: dimensionless stress-strain curves. Local buckling, crippling. Buckling of plates under combined loading. Effective-width analysis of post-buckled plates. Cozzone method. Round tubes under combined loading.

Prerequisite(s):
AE264 'Mechanics of Materials' or consent of the department.

Textbook(s) and/or Other Required Material:
Textbook:
D.J. Peery and J.J. Azar, "Aircraft Structures", McGraw-Hill Book Company, USA, 1982, 2nd Edition, ISBN 0-07-049196-8.

Reference books:
· E.F. Bruhn , "Analysis and Design of Flight Vehicle Structures", Tri-State Offset Company, USA, 1973.
· T.H.G. Megson, "Aircraft Structures for Engineering Students", Second Edition, Edward Arnold, UK, 1990, ISBN 0-7131-3676-6.
· H.D. Curtis, "Fundamentals of Aircraft Structural Analysis", Irwin, 1997, ISBN: 0-256-19260-X.
· R.M. Rivello, "Theory and Analysis of Flight Structures", McGraw-Hill Book Company, New York, 1969, ISBN: 07-052985-X.
· D.H. Allen and W.E. Haisler, "Introduction to Aerospace Structural Analysis", John Wiley & Sons, USA, 1985, ISBN 0-471-88839-7.

Course Objectives:
To teach students fundamental knowledge of science and engineering in the area of structural mechanics and educate them to apply this knowledge in the solution of aerospace structure problems, namely, in the analysis of basic structural elements in aircraft and space structures and the usual assumptions in the analysis of such elements.

Syllabus:
· Introduction: Main structural elements in aircraft and spacecraft, their functions. Flexible truss structures used in space applications. 3 hrs
· Torsion of open sections. Flexural analysis of tapered and non-tapered open-section beams: stiffener loads, web shear flows, shear center. 7 hrs
· Flexural and torsional analysis of tapered and non-tapered wing and fuselage and spacecraft structures as closed-section multi cell box beams. Usual assumptions for such structures in the analysis of stiffener loads, shear flow, shear center and angle of twist. 8 hrs
· Bending of unsymmetrical sections with emphasis on unsymmetrical wing-box cross-sections. 3 hrs
· Analysis of wing ribs and remarks on fuselage and spacecraft frames and rings. 3 hrs
· The stability of long and short columns: Euler buckling; inelastic buckling, dimensionless stress strain curves as applied to aircraft materials. 7 hrs
· The stability (local buckling) of wing and fuselage skin panels as flat and curved plates under compression, bending, shear, and combined loading; local buckling of round tubes. 8 hrs
· Post-buckling behavior of stiffened flat and curved plates : effective width concept used in the analysis of wing and fuselage skin panels.4 hrs
· Failure criteria for isotropic brittle and ductile materials. 2 hrs
· Yield and ultimate strength in bending, Cozzone method. 3 hrs
· Ultimate strength of round tubes in bending and torsion; combined loading of round tubes. 4 hrs

Class/Laboratory Schedule:
The course has four lecture hours and no laboratory sessions. The duration of each lecture hour is 50 minutes.

Homeworks, Quizzes and Projects:
Homeworks will be given.
Quizzes will be given.

Computer Usage: None.
Laboratory Work: None.

Contribution of Course to Meeting the Professional Component:
Mathematics and Basic Sciences: None
Engineering Design: None
Engineering Sciences: 2 credits
Humanities and Social Sciences: None
Departmental Content: 2 credits

Relationship of Course to Program Objectives:
The course intends to satisfy the first objective of the Department of Aerospace Engineering.

Prepared By:
Mehmet A. AKGÜN
11-06-2001