A marine deck member and the process for forming the same. The marine deck member comprises a sandwich-type composite panel made by a compression molding process. In such a process, the panel is made by subjecting a heated stack of layers of material to cold-pressing in a mold. The cellular core has a 2-D array of cells, with end faces open to the respective layers or skins. The surface traction of this type of composite panel can be enhanced for marine deck applications by controlled debossing, or embossing, of the first skin while it cools in the compression mold. The debossing effect can be affected by applying pressurized gas, e.g., pressurized air, onto the outer surface of the first skin while in the compression mold. The embossing can be affected by applying vacuum pressure on the outer surface of the first skin while in the compression mold.

Disclosed is a system for connecting two panels together. A recess is formed in the edge of one panel, and an insert is pressed into and held within the recess. The top of the insert includes holes for receiving epoxy, and epoxy conducting shafts and circuits formed on the outside of the insert assist in the encapsulation of the insert within the panel edge. The top of the insert includes an aperture formed such that a fastener can be received into a cavity formed in the recess and then driven to be secured into a fastener-receiving insert installed into the second panel.

A spacecraft panel includes a first skin, a second skin spaced apart from the first skin, and a first truss structure connecting the first skin to the second skin. The first truss structure includes a plurality of truss members, and each truss member is integral with the first skin and the second skin, such that the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure.

A marine deck member and the process for forming the same are provided. The marine deck member comprises a sandwich-type composite panel made by a compression molding process. In such a process, the panel is made by subjecting a heated stack of layers of material to cold pressing in a mold. The cellular core has a 2-D array of cells, with end faces open to the respective layers or skins. The surface traction of this type of composite panel can be enhanced for marine deck applications by controlled debossing, or embossing, of the first skin while it cools in the compression mold. The debossing effect can be affected by applying pressurized gas, e.g., pressurized air, onto the outer surface of the first skin while in the compression mold. The embossing can be affected by applying vacuum pressure on the outer surface of the first skin while in the compression mold.

A shear pin assembly for securing to a face sheet of a honeycomb core sandwich panel structure and to engage a support structure, which includes a head member having a first width dimension and a neck section secured to the head member with the neck section having a second width dimension less than the first width dimension. Further included is a flange secured to the neck section with the flange extending in a direction away from the neck section and a pin member which extends from the flange in a direction away from the head member.

A shear pin assembly for securing to a face sheet of a honeycomb core sandwich panel structure and to engage a support structure, which includes a head member having a first width dimension and a neck section secured to the head member with the neck section having a second width dimension less than the first width dimension. Further included is a flange secured to the neck section with the flange extending in a direction away from the neck section and a pin member which extends from the flange in a direction away from the head member.

A fastener for attachment to a panel, having an inner skin and an outer skin, via a panel aperture in the outer skin. The fastener including an insert pillar, a base plate, a spring, and a top insert arranged and configured to allow longitudinal compression of the spring resulting in movement and deflection of components to promote ease of use, security, and durability.

A method for manufacturing furniture using extruded polymeric honeycomb profiles, capable of providing the market with a sustainable product which can be exposed to moisture. The method includes three polymeric extruded honeycomb profiles, the extruded profile being fitted to the profile by inserting the flanges into the angled conformation, being anchored by the contact of the external flexible flaps with the flexible flaps. The union of profiles and provides an intermediate fitting allowing fixating the shelves, for example, being anchored by inserting the appendage into the angled conformations, fixating them through contact of the flexible external flanges with the external flexible flaps, allowing the formation of a three-part conjugation, being one profile and two profiles. The method allows the union of two profiles through the union of the external flexible flaps of the appendage, anchored to the internal flexible flaps of the flanges. After fitting the three profiles, which can be bottom, bases and shelves, the furniture is semi finished, the sides are mounted using profiles also fitted to the bottom, which refer to and position them, allowing the use of self-tapping screws attached to the hole of the support, allowing it to be anchored internally to the profiles, thus improving the finish in view of its honeycomb structure, after being finished with the cap to conceal the hole and the screw. The cutting edges are covered with adhesive border strips along the side walls, internal structural elements and supports.

A method for manufacturing furniture using extruded polymeric honeycomb profiles, capable of providing the market with a sustainable product which can be exposed to moisture. The method includes three polymeric extruded honeycomb profiles, the extruded profile being fitted to the profile by inserting the flanges into the angled conformation, being anchored by the contact of the external flexible flaps with the flexible flaps. The union of profiles and provides an intermediate fitting allowing fixating the shelves, for example, being anchored by inserting the appendage into the angled conformations, fixating them through contact of the flexible external flanges with the external flexible flaps, allowing the formation of a three-part conjugation, being one profile and two profiles. The method allows the union of two profiles through the union of the external flexible flaps of the appendage, anchored to the internal flexible flaps of the flanges. After fitting the three profiles, which can be bottom, bases and shelves, the furniture is semi finished, the sides are mounted using profiles also fitted to the bottom, which refer to and position them, allowing the use of self-tapping screws attached to the hole of the support, allowing it to be anchored internally to the profiles, thus improving the finish in view of its honeycomb structure, after being finished with the cap to conceal the hole and the screw. The cutting edges are covered with adhesive border strips along the side walls, internal structural elements and supports.

The present disclosure provides an insert that includes a locking mechanism that may either be formed integrally to the component or attached separately to the insert body. The top of the locking mechanism is offset from the first surface by an offset distance to enable the insert to be coupled to a recess of a component such as an aircraft component. An aperture formed in a top surface of the first portion is configured to allow additional elements to be coupled to the aircraft component. The coupling of the insert to the aircraft component is further promoted by a compression mechanism that forces the locking mechanism to couple to an overhang portion of the top layer after the force applied to the insert once it is positioned in the recess is removed, such that the top surface of the insert is co-planar with an outermost surface of the aircraft component.