Patent ID: 9371126
Filing Date: 2016-06-21
CPC Classification: B64C

Claim Text:
1. An aircraft fuselage comprising: an outer skin stiffened by a backing structure, the outer skin delimits at least one passenger cabin and one cargo hold, the cargo hold is arranged below the at least one passenger cabin in a vertical direction of the fuselage, the backing structure located in the cargo hold and above a cargo-hold floor framework comprises at least two lateral quasi-joints, and the backing structure located below the cargo-hold floor framework comprises at least one further quasi-joint, a multitude of energy absorption devices located in the cargo hold are arranged in a longitudinal direction of the fuselage, the multitude of energy absorption devices are arranged one behind the other and act in a transverse direction of the fuselage and are arranged for absorbing tensile loads, at least two structural components of the backing structure that are each pivotable about their respective lateral quasi-joints, wherein in the event of a crash the at least two structural components can be freely pivoted on the axes of rotation of the respective lateral quasi-joints.