Processes, systems, and methods described herein can be used for manufacturing reinforced carbon fiber structures. For example, processes can include forming a plurality of foam substructures. The foam substructures can be made of heat expanding foam that further expands when heated to a first threshold temperature. Processes can also include positioning carbon fiber on at least a portion of surfaces of the foam substructures, assembling the plurality of foam substructures with the carbon fiber into a superstructure, wrapping an outer surface of the superstructure with additional carbon fiber to form a wrapped superstructure, and curing the wrapped superstructure within a mold to form a reinforced carbon fiber structure. The reinforced carbon fiber structures can include internal truss structures within the foam. The reinforced carbon fiber structures can be used to form reinforced carbon fiber bicycle frame components.

A radome structure for a multilayered broadband radome structure is described. The radome structure may include a central core layer comprising a first dielectric constant, an interior intermediate core layer adjacent to an interior side of the central core layer, comprising a second dielectric constant less than the first dielectric constant, an exterior intermediate core layer adjacent to an exterior side of the central core layer, comprising a third dielectric constant less than the first dielectric constant, and an interior outside core layer adjacent to an interior side of the interior intermediate core layer, comprising a fourth dielectric constant less than the second dielectric constant. In some examples of the radome structure described above may further include an exterior outside core layer adjacent to an exterior side of the exterior intermediate core layer, comprising a low dielectric constant.

A load structure may include a panel having a core, and a coating of polyurethane around the core. The load structure may also have a layer of carpet or felt on at least a portion of a first side of the panel. The load structure may further include an over mold coating on a second side of the panel.

A composite duct with reinforcement comprises an inner ply, an outer ply, and a plurality of cellular core rings. The inner ply forms a channel with a circular cross-section. The plurality of cellular core rings is positioned at set intervals along a length of the composite duct and between the inner ply and the outer ply.

A manufactured building panel having a building panel frame that defines a cavity and having an injection aperture in fluid communication with the cavity, and an expanded foam disposed within and filling the cavity. A fabric covers and is bonded to a front surface and a rear surface of the frame to enclose the cavity. The expanded foam is formed by injecting an expandable polymer through the injection aperture and into the cavity, which expands to fill the cavity and permeate the fabric, and to cure to form the expanded foam that bonds to the frame and the fabric.

A long fiber sheet molding compound and a manufacturing method thereof are illustrated. The long fiber sheet molding compound has a first resin layer, a second resin layer and a hybrid layer being disposed between the first resin layer and the second resin layer. The hybrid layer has a fiber mesh structure being formed by a plurality of fiber silks which are discontinuous and twisted to each other to have a non-directional distribution. The manufacturing method of the long fiber sheet molding compound at least has following steps: a material providing step, an adhesion step and a lamination step. Thus, compared to the prior art, the long fiber sheet molding compound of the present disclosure can efficiency reduce a fiber content, a thickness and a weight, and an anti-slicing strength, an anti-bending strength and an anti-bending modulus can be uniform in any direction.

An acoustic panel comprising a cellular structure, such as a honeycomb structure, having cells that open at least onto a first frontal face of the structure. The panel comprises a capsular skin which is fastened to the first frontal face of the cellular structure next to a plurality of cells. The capsular skin including a continuous layer of material, in one piece, forming capsules that extend into the cellular structure. At least one channel is provided at the apex of each capsule for the passage of acoustic waves. Such a panel effectively attenuates the noise of aircraft engines, in particular, the low frequencies. It is extremely easy to manufacture industrially, the capsular skin being able to be obtained by molding with polymerization in situ, the polymerizable material then adhering to the cellular structure while it polymerizes.

An airframe assembly for an aircraft includes a first airframe member having first and second skins with a large cell core and a solid insert joined therebetween. The solid insert has a side surface at least a portion of which is adjacent to the large cell core. The first airframe member has a first set of openings extending through the first skin, the solid insert and the second skin. The airframe assembly also includes a second airframe member having a second set of openings operable to be aligned with the first set of openings of the first airframe member. Each of a plurality of fasteners extends through one of the openings of the first set of openings and one of the openings of the second set of openings securably coupling the first airframe member to the second airframe member.

A sandwich structure with an outer cover layer, inner cover layer, core layer, and pins extending through the core layer. The sandwich structure has a large core thickness resistant to crack formation and to detachment of the cover layers from the core layer. An anchor layer is between the outer and inner cover layers and divides the core layer, at least in areas, into an outer core layer section and inner core layer section. An outer group of pins extends through the outer core layer section and an inner group of pins extends through the inner core layer section. The outer group pins are connected to the anchor layer with their first end and to the outer cover layer with their opposite second end, and the inner group pins are connected to the anchor layer with their first end and to the inner cover layer with their opposite second end.

An airframe assembly for an aircraft. The airframe assembly includes a first airframe member having a first skin, a second skin, a large cell core joined between the first and second skins and a solid insert having a side surface. The solid insert is joined between the first and second skins such that at least a portion of the side surface is adjacent to the large cell core. The first skin has a first surface disposed opposite the solid insert. The airframe assembly also includes a second airframe member having a second surface. An adhesive joint is disposed between the first and second surfaces structurally bonding the first airframe member to the second airframe member such that the second airframe member is positioned opposite the solid insert.