رسالة جامعية
Μεθοδολογία ανάλυσης και προκαταρκτικού σχεδιασμού μη-συμβατικών αεροναυπηγικών δομών ; Analysis methodology and preliminary design of unconventional aeronautical structures
| العنوان: | Μεθοδολογία ανάλυσης και προκαταρκτικού σχεδιασμού μη-συμβατικών αεροναυπηγικών δομών ; Analysis methodology and preliminary design of unconventional aeronautical structures |
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| المؤلفون: | Stamatelos, Dimitrios, Σταματέλος, Δημήτριος |
| بيانات النشر: | University of Patras Πανεπιστήμιο Πατρών |
| سنة النشر: | 2010 |
| المجموعة: | National Archive of PhD Theses (National Documentation Centre Greece) |
| مصطلحات موضوعية: | Πτέρυγα από σύνθετα υλικά, Πολυάριθμες κύριες δοκούς, Ανάλυση τάσεων, Λυγισμός πλακών με ενισχυτικές δοκούς, Πεπερασμένα στοιχεία, Προκαταρκτικός σχεδιασμός, Μεθοδολογία διαστασιολόγησης, Composite wing, Multispar wing, Stress analysis, Buckling of stiffened panels, Conceptual design, Sizing methodology, Επιστήμες Μηχανικού και Τεχνολογία, Μηχανική Υλικών, Engineering and Technology, Materials Engineering |
| الوصف: | The design and development of a modern aerospace structure consists of many design stages. The most important stages are the conceptual and the preliminary where the initial sizing of the structure is obtained. It is known that the conventional design of the aircraft’s main structural members has reached a high optimization level, where margins for further improvement are small. The current demands of the lightweight structures such as weight reduction, payload increase etc. have led the aerospace industries develop unconventional structures and partially substitute the metallic materials of the primary structures with composites. The current trend of designing and evolving unconventional aerospace structures, without performing extended experimental tests, leads to the development of behavior models. The simulation of the experimental tests (through the behavior models) is achieved using high performance computers and numerical methods (Finite Element Method, Boundary Element Method etc). To apply simulation methods during the conceptual and preliminary stage is not an easy task. Most of the difficulties are the numerous geometrical, material parameters and the structural details that alter during the iterative process of the design. So, the exclusive usage of numerical analysis methods becomes very time consuming, if it is not accompanied by analytical or semi analytical methods of the sub-problems of the design. Part of the preliminary design of an unconventional wing structure is to prevent upper skin from failure. The stiffened panels that comprise the upper skin of the wing suffer from buckling due to the applied compressive loads. The sizing of the composite stiffened panels usually requires numerous of iterative calculations for various geometries, loading and boundary conditions etc. The examination of each case separately, with the use of numerical methods, results to time consuming analyses of the entire structure. Therefore, the development of appropriate analytical or semi analytical methods for ... |
| نوع الوثيقة: | doctoral or postdoctoral thesis |
| اللغة: | Greek, Modern (1453-) |
| العلاقة: | http://hdl.handle.net/10442/hedi/28015Test |
| DOI: | 10.12681/eadd/28015 |
| الإتاحة: | https://doi.org/10.12681/eadd/28015Test http://hdl.handle.net/10442/hedi/28015Test |
| رقم الانضمام: | edsbas.AED30407 |
| قاعدة البيانات: | BASE |
| DOI: | 10.12681/eadd/28015 |
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