A stiffening element comprises a tension and compression member, a shear member, an attachment member, and a plurality of beads. The tension and compression member is positioned spaced apart from the skin and configured to bear tension or compression forces that stiffen the skin and prevent the skin from buckling or bending. The shear member is connected to the tension and compression member and configured to bear shear forces between the skin and the tension and compression member. The attachment member is connected to the shear member and is configured to connect to the skin. The beads each create out-of-plane feature that is positioned in at least one of the shear member and the attachment member. The beads permit the stiffening element be reshaped to adjust a longitudinal curvature of the stiffening element.

A connecting rod coupling device for attaching a component to an aircraft fuselage and/or stiffening the fuselage has a first coupler, and a second coupler couplable to the first coupler. The first coupler has an elongate body with a first channel on a lateral surface along a first longitudinal axis. The second coupler has a hollow-cylindrical portion, which, on an inner face along a second longitudinal axis, has a second channel complementing the first channel. The hollow-cylindrical portion has a radial cutout through which the elongate body is radially insertable into the second channel from outside the hollow-cylindrical portion. The second coupler has a closure body, which closes the radial cutout, and can be positioned removably in the cutout to complete the second channel on a radially internal face. The second coupler also has an element, pushable onto the hollow-cylindrical portion to secure the closure body on the hollow-cylindrical portion.

An aircraft fuselage includes an element forming a skin and a load-carrying structure supporting the element forming the skin. The load-carrying structure includes a plurality of elements forming a spar disposed parallel to an axial direction defined by the fuselage and a plurality of elements forming a frame disposed spaced apart along the axial direction. Each element forming a frame being arranged substantially perpendicularly to the elements forming a spar, where the element forming the skin is fastened on an external perimeter of each element forming a frame by means of fastening elements configured to keep the element forming the skin away from the external perimeter and where the element forming the skin is made of a transparent material.

The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft; a cabin located within the main body and a transitional portion of the blended wing body; and a plurality of transparent panels in a ceiling of the cabin configured to transmit light from outside the blended wing body aircraft to inside the cabin.

The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft; a cabin located within the main body and a transitional portion of the blended wing body; and a plurality of transparent panels in a ceiling of the cabin configured to transmit light from outside the blended wing body aircraft to inside the cabin.

A method for producing an aircraft fuselage for simplifying and accelerating the production of the aircraft fuselage. The method includes providing a fuselage structure which surrounds an interior space and has an inner side facing the interior space, providing an insulating panel for insulating the fuselage structure, wherein the insulating panel has an inner surface and an outer surface, providing a film which is provided with electric strip conductors, fastening the film to the inner surface of the insulating panel, and attaching the insulating panel to the inner side of the fuselage structure.

In an example, a method for installing a decoration panel in a ceiling assembly in an aircraft is disclosed. The method comprises removing a generic panel from the ceiling assembly to produce an opening in the ceiling assembly. The method also comprises inserting the decoration panel through the opening in the ceiling assembly. The method also comprises coupling the decoration panel to the ceiling assembly using a plurality of fasteners such that the decoration panel extends across the opening in the ceiling assembly. The plurality of fasteners includes a first type of fastener and a second type of fastener.

Provided are methods and devices for supporting of variety of different pre-cured composite stringers after forming and prior to curing. A post-forming processing device comprises a base with a channel for receiving hat portions of different stringers. The device also comprises a support structure, at least partially extending within the channel. The support structure is configured to conform to different hat portions and to retain the shape of these hat portions. For example, the support structure is made from a flexible material, which conforms to any shape variations. In some examples, the support structure is made from a jamming material that is reshaped together with each of the pre-cured composite stringers. A post-forming processing device is used for supporting different pre-cured composite stringers while various operations are performed on these stringers, such as stringer trimming, inspection, installation of bladders and noodles, and the like.

Apparatuses and systems for more efficient construction and operations of a vehicle. A structural/storage system that includes a plurality of storage elements. Each of the storage elements includes a housing having an outer surface, an inner surface, and at least one opened end. The structural/storage system further includes first attachment devices disposed at the outer surface and second attachment devices disposed at the outer surface. The second attachment devices of a first one of the plurality of storage elements are configured to be removably attachable to the first attachment devices of a second one of the plurality of storage elements.

A conductive composite includes a first layer of elastomeric polymer, a layer of electrically conductive paste on the first layer of elastomeric polymer, and a second layer of elastomeric polymer on the layer of electrically conductive paste. A reinforcement mesh is in contact with the layer of electrically conductive paste.