| CPC B64D 37/30 (2013.01) [B64D 37/04 (2013.01); F17C 1/12 (2013.01); F17C 2201/0104 (2013.01); F17C 2201/0128 (2013.01); F17C 2203/0329 (2013.01); F17C 2203/0391 (2013.01); F17C 2203/0629 (2013.01); F17C 2203/0673 (2013.01); F17C 2221/012 (2013.01); F17C 2223/0161 (2013.01); F17C 2223/036 (2013.01); F17C 2227/0341 (2013.01); F17C 2270/0189 (2013.01)] | 18 Claims |
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1. A cryogenic fluid pressure vessel for an aircraft, comprising:
a first wall layer, which contains carbon fiber-reinforced plastic, having an inner contact surface for contact with a pressurized cryogenic fluid to be accommodated inside the cryogenic fluid pressure vessel;
a second wall layer, which is arranged on an outer surface of, and in contacting relationship with, the first wall layer and has a thermal barrier, wherein the thermal barrier includes an insulating device and a cooling device which is configured as a pipeline system comprising a plurality of pipes, such that both the cooling device and the insulating device are arranged inside the second wall layer, wherein the insulating device is interspersed between the plurality of pipes;
a closable inlet/outlet opening for cryogenic fluid, which extends through the first and the second wall layer; and
a structural insert integrated in the first and the second wall layer, which has a fastening connecting piece located on the outside of the cryogenic fluid pressure vessel for mechanically coupling the cryogenic fluid pressure vessel with external structures;
wherein the cryogenic fluid pressure vessel forms an essentially cylindrical main body.
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