A joint joining an aircraft wing to an aircraft body employs a splice panel that is engaged in surface engagement with a skin panel on a side of the aircraft body and is engaged in surface engagement with a leg panel extending upwardly from the aircraft wing. A plurality of fasteners extend through the splice panel and the leg panel and extend through the splice panel and the skin panel. The plurality of fasteners attach the splice panel to the skin panel and attach the splice panel to the leg panel and thereby attach the skin panel to the leg panel. After fastener holes have been drilled through the splice panel and the leg panel to attach the splice panel to the leg panel, the splice panel can be removed from the leg panel. This provides easy access to the fastener holes drilled through the leg panel for deburring of the fastener holes.

A vehicle, such as an aircraft, structural architecture for supporting a horizontal stabilizer with a back up beam having an upper longeron fitting connected to the front side and secured with a back up fitting on the back side, a lower longeron fitting connected to the front side and secured with a back up fitting on the back side, and a pivot fitting connected to the front side of the first back up beam in between the upper longeron fitting and the lower longeron fitting and secured with a third back up fitting on the back side of the back up beam.

An exterior panel is configured to accommodate high thermal stresses imposed on exterior surfaces of aerospace transport vehicles during hypersonic flight. The exterior panel is formed of a superplastic material such as a titanium alloy, and includes an exterior skin and a plurality of cooling tubes that extend through the panel. The exterior panel further includes an interior skin configured to be attached to a frame member such as a rib, stringer, or spar of the transport vehicle. The tubes pass through a multicellular core, which is sandwiched between the exterior and interior skins to impart tensile and compressive strength to the exterior panel. In one disclosed method, the core is superplastic formed and diffusion bonded to the exterior skin, the tubes, and the interior skin. A cooling fluid, which may be a gas or liquid, including a fuel, may be pumped through the tubes to cool the exterior panel.

A mechanical fastener system for EME protection, including at least one plated component, wherein the at least one plated component includes a base material, a bonding layer disposed over the base material, and a metal plating disposed over the bonding layer.

The method for producing an assembly is a method for producing an assembly equipped with a member to be reinforced (20), a reinforcing member body (41), and a filler (42), wherein the reinforcing member body (41) has a pair of flanges (44) arranged spaced on the surface (20B) of the member to be reinforced (20), a web (45), and a connection portion (46) which connects the flanges (44) and the web (45) and forms a filler space (V) with the surface (20B). The method for producing an assembly includes a step for inserting a filler (42) into the filler space (V), a step for attaching a crack control member (43) to cover the end of the filler (42), a step for joining the flanges (44) and the member to be reinforced (20), and a step for curing at least the member to be reinforced (20).

Beaded panels and method of forming beaded panels. A beaded panel as described herein includes a base structure comprising a sheet of material, and beads that comprise a protrusion on a first side of the base structure, and a concavity on an opposing second side of the base structure. A geometry of the beads comprises a center section having a conic shape about a longitudinal axis, flared sections symmetric about the center section along the longitudinal axis, and a transition section that curves outward from a base of the center section and the flared sections to blend with a flat surface on the first side of the base structure.

A method of additively manufacturing a fire and overheat detection system (FODS) clamp onto a rail tube is provided. The method includes building a base of a clamp body on the rail tube, sequentially building portions of a locking feature and holders of the clamp body on the base and sequentially building remaining portions of the holders and flanges forming grooves at each of the holders of the clamp body on the base.

A system and method of a structural panel includes a first outer sheet and a second outer sheet, the first outer sheet and second outer sheet including a polygon shape; a core arrangement sandwiched between the first outer sheet and the second outer sheet, the core arrangement comprising two or more discrete members arranged adjacent each other, the discrete members shaped or structured to reduce crack initiation and propagation within the core arrangement.

A frame component for a frame of a fuselage structure of an aircraft includes a central web extending along a longitudinal direction and having an inner edge region with respect to a radial direction running transversely with respect to the longitudinal direction and an outer edge region with respect to the radial direction. An inner web is bent from the inner edge region of the central web towards a first side. An outer web is bent from the outer edge region of the central web towards the first side. The central web, the outer web and the inner web are produced integrally from a metal sheet and together define a C-shaped cross section of the frame component. At least one stringer recess is formed in the outer web and in the outer edge region of the central web. The central web has, in the region of the stringer recess, a first reinforcing formation which forms a protrusion on the first side of the central web.

A heated floor panel assembly with an impact layer is made to absorb blunt force and protect a heating element inside the assembly. The assembly further includes a plurality of structural layer made of a reinforced polymer matrix, one or more core layer with a honeycomb or foam structure for absorbing shear stress, and a heating layer containing the heating element. The impact layer is a composite layer with a resin impregnated fiber matrix.