A composite stiffener for a stiffener reinforced panel is disclosed. The stiffener has a longitudinal direction and a run-out region which terminates at an end of the stiffener. The stiffener also has a constant section region inboard of the run-out region in the longitudinal direction and having a constant cross section transverse to the longitudinal direction with a crown between adjacent foot portions. The run-out region has a changing cross section transverse to the longitudinal direction with a crown between adjacent foot portions and the crown reduces in height towards the end of the stiffener forming a ramp. The composite stiffener includes a number of blankets of non-crimp fabric layers.

An aircraft composite panel assembly includes a first panel having upper and lower faces, the lower face having a recess on a first side of the panel, a second panel having upper and lower faces, the lower face having an outward projection at a first side of the panel, the outward projection received on the recess forming a lower continuous face; and a forward stack of plies of composite material bonded to the upper face of the first panel, the forward stack of plies having an edge overlapping the first side of the first panel, and the number of plies of the forward stack of plies decreasing toward the opposite side of the first side of the first panel.

A precast concrete panel and method for forming the panel are disclosed. A method of forming the panel to be used as a floor, wall, or roof structure includes positioning one or more forming members within a casting bed having a plurality of upright surfaces defining a generally rectangular interior area, the one or more forming members comprising an insulating material extending along a length dimension of the one or more forming members to define a plurality of rectangular-shaped channels in a parallel and spaced-apart relationship, placing uncured concrete within the casting bed and allowing the concrete to cover the one or more forming members and substantially fill the channels, and allowing the concrete to cure.

A foam-based expansion joint seal system packaging which facilitates transport and reduces the need for internal splices which includes laterally-flexible packaging bodies. The packaging bodies may include flutes, corrugations or prisms on their exterior to enable lateral bending of the foam-based expansion joint seal system packaging, even into coils.

A vehicle body may have an internal skeleton, and a skin fabricated in-situ over the internal skeleton. The internal skeleton may be fabricated via a first additive manufacturing system. The skin may be fabricated via a second additive manufacturing system that is different from the first additive manufacturing system.

A method of making a vacuum insulated refrigerator cabinet structure includes thermoforming a first polymer sheet to form a wrapper having a base wall and four sidewalls. The method also includes thermoforming a second polymer sheet to form a liner having a base wall and four sidewalls. Elongated corner stiffeners are adhesively secured to inside corners of the wrapper. A resilient ring is adhesively secured to the wrapper and liner. The resilient ring includes pins that are received in openings of the elongated corner stiffeners. Porous material is disposed in a vacuum cavity between the wrapper and the liner.

Freeform, additive manufacturing equipment, processes and products, including residential, commercial and other buildings. A movable extruder places extrudate that solidifies in open space to create scaffolding or skeletons of buildings and other products. Elongated extrudate elements are fused to each other or connected by other means to form a cellular structure. Filler material such as polymeric insulating foam may simultaneously or thereafter be placed within the cellular structure to contribute desired strength, rigidity, insulative, barrier or other properties. Finish materials may also be applied.

A panel for cladding a ceiling or wall in a cabin, especially the cabin of a passenger aircraft, in which a board is laminated on both sides with a cover layer which is made of fibrous material or fabric, which is impregnated with resin or a thermoplastic material, and is cured under the effects of pressure and temperature, said board having at least one core with a honeycomb structure formed by a large number of walls, said walls being compressed or bent in a pre-defined region of the board by between 5% and 50%.

A system and process of printing a package of expanded material (e.g., expanded starch, foam or other expanded material). The expanded material can be heated and extruded, poured, sprayed, or otherwise applied in malleable form that sets up to become a porous protective covering for an item to be packaged. In an example, a layer of expanded material is laid down, and the item in a protective covering (e.g., a plastic bag, sleeve, coating, etc.) is positioned on the layer of expanded material. Additional layers or expanded material may be applied, thereby encasing the item. The top surface of the expanded material may be flattened, such as by operation of a roller, press, or cutter. The top surface may be sprayed with a shellac sealant, paint, or other coating, to allow printing of a label on the top surface.

A method and apparatus is presented. Layers of composite material are laid down on a forming tool. A respective bend is formed in each of the layers to form the composite filler comprising bent layers on the forming tool. The composite filler comprising the bent layers is placed into a gap formed by at least one composite structure.