| CPC B64C 1/18 (2013.01) [B64C 1/062 (2013.01); B64C 2001/0027 (2013.01)] | 20 Claims |

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1. A module for installation into an aircraft fuselage, the module comprising:
a support device comprising:
a lower end configured for connection to a fuselage structure in a lower deck of the aircraft fuselage;
an upper end configured for connection to an intermediate floor in the aircraft fuselage; and
an energy absorption element between the upper end and the lower end;
a wall panel which is connected to the support device and extends along a longitudinal axis and along a circumferential direction, wherein, as viewed from the longitudinal axis, the support device has a concave form;
wherein the energy absorption element is configured such that, in an event of a crash of an underside of the aircraft fuselage in which the module is installed, the energy absorption element is configured to undergo a plastic deformation and, in so doing, absorb an amount of kinetic energy of that a part of the fuselage structure connected to the lower end of the support device;
wherein the plastic deformation and the amount of kinetic energy are of such a magnitude that, in the event of the crash, the module is configured such that the fuselage structure will, at the underside of the aircraft fuselage, deform no more than a minimum height, which is defined as being between a seat surface of passenger seats provided in the lower deck and the intermediate floor.
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