Please use this identifier to cite or link to this item: http://hdl.handle.net/10889/13875
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dc.contributor.authorΤζανάκης, Γεώργιος-
dc.contributor.otherTzanakis, Georgios-
dc.date.accessioned2020-10-02T09:53:21Z-
dc.date.available2020-10-02T09:53:21Z-
dc.date.copyright2020-09-29-
dc.identifier.urihttp://hdl.handle.net/10889/13875-
dc.description.abstractThe increase of the air transfer requires an extensive variety of legal regulations that focus on the safety of the flight. The main objective of these regulations is the safe flight of the aircraft and the survival of the occupants in the event of an emergency landing. One of the most important mechanical structures responsible for the safety of the occupants is the aircraft seat, which consist an interface between the passenger and the aircraft. Aircraft seats must ensure the protection of occupants from fatal injuries in the occasion of crash landing, increasing their probability of safely evacuating the cabin. Except for the occupant’s safety, the manufacturing of lightweight structures is considered one of the most important factors that affect greatly the aircraft seat’s study, making the use of low density materials, such as aluminum alloys or composites, a valuable choice. Rapid growth of fiber polymer composite materials in aerospace has made them an important section of the aircraft structure study. Their significant mechanical properties and low density characteristic, in accordance with their efficient applicability, has accelerated their growth in aerospace structures and made them one of the most commonly used material. Aircraft structures certification requires a great number of time consuming and high cost tests, including full scale tests, which must be conducted in order to reach an acceptable design of the seat configuration that meets the structural and injury criteria requirements. Thus, computer simulations and Finite Element Methods have become an essential engineering tool, for the purpose of the efficient and accurate seat design. The objective of this thesis is the development of an aircraft seat configuration of three passengers, which is designed to satisfy the dynamic criteria of the FAR 25.562 regulation for the scenario of the aircraft’s emergency landing. There are developed two versions of the seat configuration, where the second is an optimized version, as a matter of the mass reduction of the structure, with the use of fibrous composite materials, while maintaining the structural and occupant safety requirements.el
dc.language.isoenel
dc.subjectAircraft seatsel
dc.subjectAdvisory circularel
dc.subjectFederal aviation administrationel
dc.subjectEuropean aviation safety agencyel
dc.subjectComputer aided engineeringel
dc.subjectAnthropomorphic test dummyel
dc.subjectFinite element analysisel
dc.subjectCrash analysisel
dc.subjectAircraft composite seatel
dc.titleDesign analysis and optimization of an aircraft composite seat under dynamic loading conditions according to far 25.562el
dc.title.alternativeΣχεδιασμός, ανάλυση και βελτιστοποίηση αεροπορικού καθίσματος από σύνθετα υλικά υπό δυναμικές συνθήκες φόρτισης σύμφωνα με το κανονισμό far 25.562el
dc.subject.alternativeΑεροπορικά καθίσματαel
dc.subject.alternativeΑνάλυση πεπερασμένων στοιχείωνel
dc.subject.alternativeΑνάλυση πρόσκρουσηςel
dc.degreemasterThesisel
datacite.rightshttp://purl.org/coar/access_right/c_abf2el
oaire.licenseConditionnullel
datacite.contributor.SupervisorΒασίλειος Κωστόπουλος-
datacite.contributor.RelatedPersonΘεόδωρος Λούτας-
datacite.contributor.RelatedPersonΔημοσθένης Πολύζος-
Appears in Collections:Τμήμα Μηχανολόγων και Αεροναυπηγών Μηχανικών (ΜΔΕ)

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