Composites are not yet introduced into the fuselage structure of large civil aircraft. The use of sandwich construction could facilitate this introduction. With the currently available materials sandwich structures can be realized which are reliable with respect to mechanical loads and which are resistant to environmental degradation. The combination of continuous fibre reinforced thermosets and thermoplastics can facilitate the production of these large sandwich fuselages. When prefabricated in-situ foamed panels are used, close fit joints can be obtained with filling thermoset joint strips which are weak at the time of jointing. Damage tolerance can be obtained with a combination of the soft skin principle and damage stoppers incorporated in the facings. Damage tolerance analysis can be done with the flat plate stress intensity approach. The curvature effect is shown to be small for large airplanes.
Towards an all composite aircraft fuselage
In Richtung auf einen Flugzeugrumpf ganz aus Verbundwerkstoff
1993
8 Seiten, 9 Bilder, 8 Quellen
Aufsatz (Konferenz)
Englisch
Aircraft fuselage section, aircraft fuselage and aircraft
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