Fuselage of an aircraft or spacecraft of crp/metal hybrid...

Details Fuselage of an aircraft or spacecraft of crp/metal hybrid... Fuselage of an aircraft or spacecraft of crp/metal hybrid...

B - Operations, Transporting

64

C

B64C 1/00 (2006.01)

Patent

CA 2671896

The present invention provides an inherently rigid fuselage of an aircraft or spacecraft comprising shell elements or fuselage barrels of CRP construction, wherein the shell elements or fuselage barrels each have an outer skin and an inner skin, which each at least partially or completely consist of a CRP material, wherein a composite core element is provided between the outer skin and the inner skin, and wherein the fuselage in the interior has a metal framework (1) which is connected to the shell elements or fuselage barrels.

La présente invention concerne un fuselage d'aéronef ou de véhicule spatial à rigidité intrinsèque, comprenant des éléments d'enveloppe ou des tubes de fuselage présentant une construction en PRFC (plastique renforcé de fibre carbone), les éléments d'enveloppe ou tubes de fuselage comprenant une peau externe et une peau interne qui sont chacune constituée entièrement ou partiellement d'un matériau PRFC, les peaux interne et externe étant séparées par un noyau composite, et le fuselage comprenant à l'intérieur une ossature métallique (1) reliée aux éléments d'enveloppe ou tubes du fuselage.

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