Design of a composite curved fuselage panel subjected to buckling loading conditions

Kriatsiotis, Ilias Marios; Κριατσιώτης, Ηλίας Μάριος

dc.contributor.author	Kriatsiotis, Ilias Marios	en
dc.contributor.author	Κριατσιώτης, Ηλίας Μάριος	el
dc.date.accessioned	2025-11-24T12:32:52Z
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/62930
dc.identifier.uri	http://dx.doi.org/10.26240/heal.ntua.30626
dc.description	Εθνικό Μετσόβιο Πολυτεχνείο--Μεταπτυχιακή Εργασία. Διεπιστημονικό-Διατμηματικό Πρόγραμμα Μεταπτυχιακών Σπουδών (Δ.Π.Μ.Σ.) “Υπολογιστική Μηχανική”	el
dc.rights	Default License
dc.subject	Aircraft	en
dc.subject	Composites	en
dc.subject	FEM	en
dc.subject	Buckling	en
dc.subject	Sructural	en
dc.subject	'Ατρακτος	el
dc.subject	Λυγισμός	el
dc.subject	Ανάλυση	el
dc.subject	Αεροσκάφος	el
dc.subject	Πάνελ	el
dc.title	Design of a composite curved fuselage panel subjected to buckling loading conditions	en
heal.type	masterThesis
heal.secondaryTitle	Σχεδιασμός ενός καμπυλωτού πάνελ ατράκτου από σύνθετα υλικά το οποίο υπόκειται σε εντατική κατάσταση λυγισμού	el
heal.classification	Aeronautical engineering	en
heal.dateAvailable	2026-11-23T22:00:00Z
heal.language	en
heal.access	embargo
heal.recordProvider	ntua	el
heal.publicationDate	2024-09-29
heal.abstract	This study investigates the feasibility of replacing metallic structural components of an aircraft, particularly fuselage skin panels, with composite materials under specific conditions, notably where high thermal effects are absent. The focus is on the upper aft fuselage panel of a typical multi-role fighter aircraft, where buckling due to axial compression and shear loads is the primary concern. Initial analysis involves hand calculations to determine the critical buckling stress of the metallic panel using semi- empirical methods, followed by a Finite Element Method (FEM) analysis conducted with the Abaqus software. The next phase of the research involves the design of a composite panel with the same geometric characteristics using carbon fiber-reinforced epoxy. A stacking sequence optimization is performed using MATLAB, generating and analyzing 29,472 configurations under the same load conditions based on aerospace industry guidelines. The study demonstrates that a majority of the composite panel configurations outperform the metallic panel in terms of buckling resistance, with a significantly higher margin of safety, particularly under axial compression. Additionally, the selected composite panel offers potential benefits in weight reduction and improved fatigue performance, validating the superiority of composite materials for aircraft structural components. This research paves the way for further development and analysis of composite structures in aerospace applications, highlighting their advantages in terms of strength-to-weight ratio and structural performance.	en
heal.advisorName	Tsamasphyros, George	en
heal.committeeMemberName	Τσαμασφύρος, Γεώργιος	el
heal.committeeMemberName	Θεοτόκογλου, Ευστάθιος	el
heal.committeeMemberName	Σιδερίδης, Αιμίλιος	el
heal.academicPublisher	Εθνικό Μετσόβιο Πολυτεχνείο. Σχολή Χημικών Μηχανικών	el
heal.academicPublisherID	ntua
heal.numberOfPages	64 σ.	el
heal.fullTextAvailability	false