A joint structure includes a first material (1), a second material (2) weldable to the first material, and a third material (3) at least a portion of which being sandwiched between the first material and the second material, having a through opening portion at the sandwiched portion, and including a material that is difficult to be welded to both the first material and the second material, the first material and the second material welded the via through opening portion. At least one of the first material and the second material is provided with a protrusion (14) inserted in the through opening portion. A first gap (4) is provided between an inner peripheral surface of the through opening portion and the protrusion. A second gap (5) is provided between the first material and the second material, the second gap having a size depending on a plate thickness of the first material in a region corresponding to the protrusion. Under a condition in which the second gap has a size of greater than or equal to 0.1 mm but less than or equal to 40% of the plate thickness of the first material in the region, the first material and the second material are welded by emitting a laser beam from a side on which the first material is disposed.

A method for joining two substantially planar fiber-composite structural components, includes stacking the two components on a support jig to overlap along a joining region. A lower component end section within the joining region borders a gap between the upper component and the jig, where the upper component is unsupported by the jig. The gap is bordered on an opposite side of the lower component end section by a filling portion of the upper component or a planar filler element supported by the jig. The lower component is joined to the upper component within the joining region by applying temperature and pressure to the components. A width of the gap allows the upper component to elastically deform along the gap under the pressure and bend down into the gap to abut the jig along the gap and thereby compensate thickness tolerances between the components during the pressure application.

A joint for a composite frame includes a first composite rod, a first shell abutting the first composite rod, a second shell abutting the first composite rod and disposed opposite the first shell relative to the first composite rod. The first and second shells are joined together such that composite rod is fixed therebetween. A method of forming joints of composite frame includes forming a composite frame by interconnecting a plurality of composite rods formed by an Automated Fiber Placement (AFP) manufacturing method around a mandrel, applying a first shell to the plurality of composite rods at a first location where composite rods are interconnected, applying a second shell at the first location opposite the first shell relative to the composite rods, and joining the first and second shells together with the composite rods at the first location disposed between the first and second shells.

A container may include a body assembly comprising a shell, an inner liner forming a storage compartment, a foam layer positioned between the shell and the inner liner, and an opening providing access to the storage compartment. The container may also include a lid assembly attached to the body assembly and configured to seal the opening. The lid assembly may include an upper inner liner, an upper insulating portion, and an upper shell portion, and the upper insulating portion may be positioned between the upper inner liner portion and the upper shell portion.

A process for post curing a composite product made from a filament winding process comprises the steps of: surrounding the composite product, that is disposed about a rotatable mandrel, with an outer jacket; and simultaneously rotating and heating the mandrel resulting in post curing of the composite product according to a process that can be referred to as being a combo-semi-centrifugal post curing process.

An apparatus including a shell defining a first side and a second side, wherein the shell is formed from a one-piece integral structure, wherein the one-piece integral structure is joined together to form a seam, and wherein the seam is on one of the second side or the first side, a storage compartment, and an opening configured to provide access to the storage compartment.

Methods for making structural shims (220) for the mating assembly of parts, such as for installation between a skin (212) and substructure (214) of an aircraft. The methods include the steps of disposing a hardenable composition (216) into a gap between the first (212) and second parts (214), hardening the hardenable composition to provide a shim pattern (218) that is dimensionally stable, and removing the shim pattern from the gap without damage. The shim pattern can be used to provide a digital model thereof, which can in turn be used to fabricate the structural shim (220).

An insulating device can include an aperture having a waterproof closure which allows access to the chamber within the insulating device. The closure can help prevent any fluid leakage into and out of the insulating device if the insulating device is overturned or in any configuration other than upright. The closure also prevents any fluid from permeating into the chamber if the insulating device is exposed to precipitation, other fluid, or submersed under water. This construction results in an insulating chamber impervious to water and other liquids when the closure is sealed.

A method of manufacturing a closed cross-section structural member is disclosed. The closed cross-section structural member includes: a first panel and a second panel joined to each other to form a closed cross-section; and a fiber reinforced plastic (FRP) material bonded to the first panel. The method includes: attaching the FRP material to the first panel with an adhesive; curing the FRP material and the adhesive by heating the FRP material and the adhesive together with the first panel; and joining the second panel to the first panel in which the FRP material and the adhesive are cured.

Connections of sub-elements formed at least partly from fiber composite materials of a component for an aircraft with relatively low manufacturing complexity and the same or improved reliability and improved sealing, by providing different seam connections between the sub-elements. For this purpose, at least an edge region, formed from fiber composite material, of the first sub-element is formed to give a foldover that engages with an edge region of the other sub-element. Preferably, the forming is effected especially with use of thermoplastic materials while heating preferably the entire edge region.