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151-0366-00L  Aircraft Structures

SemesterFrühjahrssemester 2019
DozierendeP. Ermanni
Periodizitätjährlich wiederkehrende Veranstaltung

KurzbeschreibungThis course deals with the structural design, stress analysis and sizing of aircraft structures. The course, which is building-up on fundamental knowledge in mechanics and lightweight structures, also includes tutorials, discussion of practical cases and lab demonstrations. The complementary exercises include hand calculations and the usage of finite element tools.
LernzielDevelop the necessary skills to identify and solve typical engineering problems related to structural design, stress analysis and sizing of aircraft structures, such as wings and fuselage sections and their subcomponents. Familiarize yourself with the typical loads within aircraft structures and with the function of the different structural elements found in fuselages and wings.
InhaltThe course is addressing the following topics:

- Introduction
- Aircraft loads and aircraft design
- Materials and allowables in aircraft structures
- Wing and empennage structures: Design and Modelling aspects, Multi-Cell Design, ribs, cutouts, and shear lag
- Plane stress elements and load introduction
- Fuselage structures: Design and modelling aspects, buckling strength, design and analysis of fuselage frames
- Diagonal semi-tension field design
- Static and buckling analysis of cylindrical shells

Laboratory demonstrations:
- Structural test of a vertical empennage
- Stress concentration in panels with cutouts
- Buckling of cylindrical shells
SkriptLecture notes, handouts, exercises, and the script are available for download in a digital format. The lecture materials can be found via the lecture webpage (http://www.structures.ethz.ch/education/master/master/aircraftstructures.html) or directly via the moodle page (https://moodle-app2.let.ethz.ch/course/view.php?id=3093).
Voraussetzungen / BesonderesAttendance at Bachelor course "Leichtbau" (Lightweight Construction) or equivalent is recommended. Previous knowledge of buckling, profile failure, shear flow, and calculation of semi monocoques is required.