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A platform for research: civil engineering, architecture and urbanism
Integrity of composite aircraft fuselage materials under crash fire conditions
This paper summarizes a series of small-scale tests carried out to evaluate and model the post-crash fire integrity of composite aircraft fuselage structures. The US Federal Aviation Administration regulations for the penetration of an external fuel fire into an aircraft cabin after crash require a burn-through period of 4 minutes (FAA § 25.856 Appendix F, Part VII). Different candidate structures for the next generation of composite aircraft fuselage, provided by Airbus, were investigated, including CFRP monolithic laminate and a folded-core CFRP sandwich. Those materials were subjected to constant heat flux from a propane gas burner, while being held under compressive load in a small, specially designed compression test rig with anti-buckling guides. The propane burner was calibrated to produce a constant heat flux up to 182 kW/m2. The sample time-tofailure was measured, along with the temperatures at various points through the thickness. Modelling the thermal and structural behaviour under load required the use of a modified version of the Henderson Equation, which describes heat transfer through composites under ablative fire conditions. This has been incorporated into the Com-Fire software model. Kinetic parameters for the resin decomposition reaction were determined from thermo-gravimetric data and other thermal parameters, conductivity and diffusivity were measured experimentally. The paper will compare the behaviour of single and double-skinned structures and will examine measured and modelled behaviour.
Integrity of composite aircraft fuselage materials under crash fire conditions
This paper summarizes a series of small-scale tests carried out to evaluate and model the post-crash fire integrity of composite aircraft fuselage structures. The US Federal Aviation Administration regulations for the penetration of an external fuel fire into an aircraft cabin after crash require a burn-through period of 4 minutes (FAA § 25.856 Appendix F, Part VII). Different candidate structures for the next generation of composite aircraft fuselage, provided by Airbus, were investigated, including CFRP monolithic laminate and a folded-core CFRP sandwich. Those materials were subjected to constant heat flux from a propane gas burner, while being held under compressive load in a small, specially designed compression test rig with anti-buckling guides. The propane burner was calibrated to produce a constant heat flux up to 182 kW/m2. The sample time-tofailure was measured, along with the temperatures at various points through the thickness. Modelling the thermal and structural behaviour under load required the use of a modified version of the Henderson Equation, which describes heat transfer through composites under ablative fire conditions. This has been incorporated into the Com-Fire software model. Kinetic parameters for the resin decomposition reaction were determined from thermo-gravimetric data and other thermal parameters, conductivity and diffusivity were measured experimentally. The paper will compare the behaviour of single and double-skinned structures and will examine measured and modelled behaviour.
Integrity of composite aircraft fuselage materials under crash fire conditions
Die Beständigkeit von Verbundwerkstoffen im Flugzeugrumpf unter den Bedingungen eines Feuers nach einer Kollision
Delfa, G. la (author) / Luinge, J.W. (author) / Gibson, A.G. (author)
2008
10 Seiten, 11 Bilder, 2 Tabellen, 17 Quellen
Conference paper
Storage medium
English
Feuerfestigkeit , carbonfaserverstärkter Kunststoff , Flugzeugrumpf , Werkstoff , Brand (Feuer) , Zusammenstoß , Messen thermischer Größen , Flugkraftstoff , Verbrennung (Oxidation) , Sandwich-Konstruktion , Wabenstrukturlaminat , Wärmeübergang , Brennverhalten , Dauerhaftigkeit , Epoxidharz , Hitzebeständigkeit
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