A method of fabricating a composite assembly may include providing a first laminate and a second laminate respectively formed of first and second composite plies, and having a respective first and second cured section and a respective first and second uncured section. The method may further include interleaving the first composite plies in the first uncured section with the second composite plies in the second uncured section to form an interfacial region. The method may additionally include curing the interfacial region to join the first laminate to the second laminate and form a unitized composite assembly.

A method for manufacturing a fuel cell assembly includes: arranging an end face of a gas diffusion layer on a placement jig in a state abutting an end face of a resin frame; melting a part of the frame member and causing to penetrate into the gas diffusion layer by pressurizing the projecting part by way of a heat-transfer member, and heating the projecting part via the heat-transfer member by abutting a heating member against of the heat-transfer member; and solidifying the part of the resin frame having penetrated into the gas diffusion layer, in which an abutting position of the heating member relative to the heat transfer member is set in the melting step so that a central axis of the heating member is positioned more to a side of the gas diffusion layer than the central axis of the projecting part.

A three-dimensional object includes an outer-layer member and an inner structural member. The outer-layer member is a layer to constitute the surface of the three-dimensional object, and includes an inner space. The outer-layer member is made up of a plurality of divided outer-layer pieces formed of build material, which is functional ink ejected from a droplet ejection head and cured. The inner structural member is disposed in the inner space of the outer-layer member and configured to support the outer-layer member.

A composite product having a junction structure includes a first unit formed of a composite material, a first connector formed of a metal and provided with one end inserted into one end of the first unit and formed integrally with the first unit and another end extending outwards from the first unit, a second unit formed of a composite material, and a second connector formed of a metal and provided with one end inserted into one end of the second unit and formed integrally with the second unit and another end extending outwards from the second unit, wherein the other end of the first connector and the other end of the second connector are joined and fixed by welding under a condition that the ends of the first unit and the second unit are opposite each other adjacently.

A method for producing a thermoplastic fiber composite component, in particular for an aircraft or spacecraft, has the following method steps: material-removing processing of a first face of a first plate, wherein the first plate comprises a thermoplastic fiber composite material and a local reduction in thickness of the first plate is made by the material-removing processing of the first face; positioning a second plate relative to the first plate such that the first face of the first plate is brought into alignment with a third face of the second plate; and joining the first plate to the second plate to form a single component, wherein the surface of the first face of the first plate is integrally bonded to the surface of the third face of the second plate.

A joint structure according to an embodiment of the present invention is provided with: a first member that is made of a metal material and has a plurality of holes having an opening diameter of 30-100 μm formed in a surface thereof; a third member that is made of a metal material the same as or different from that of the first member, or a thermoplastic resin, and that has a plurality of independent holes having an opening diameter of 30-100 μm formed in a surface thereof; and a second member that is made of a curable resin and joins the surface of the first member in which the holes are formed and the surface of the third member in which the holes are formed.

A method for producing a component from two or more sub-components includes the steps of: producing each of the sub-components using an additive manufacturing process in which a resin, which is radiant-energy-curable, is partially cured using a selective application of radiant energy, wherein each sub-component includes a joint surface in which the resin is partially cured which is cured to a lesser degree than the remainder of the respective sub-component, so as to leave the joint surfaces in a condition suitable for bonding; assembling the sub-components with their respective joint surfaces in mutual contact; and performing a secondary cure of the partially-cured resin at the joint surfaces using an application of radiant energy, so as to further cure the partially-cured resin and bond the sub-components to each other, thereby forming the component.

Disclosed are embodiments of a versatile storage bag and methods of making same. The versatile storage bag may have first and second sidewalls, a double-locking closure mechanism with a first closure element extending along the first sidewall and a second closure element extending along the second sidewall, each closure element having a channel and an elongated member configured for interlocking with one another. A double-seal along three sides of the first sidewall and the second sidewall form a gusset between two seals, leaving an opening through the double-locking closure mechanism. Corner seals may be formed at the corners of the first and second sidewalls, further reinforcing the double-locking closure mechanism for an airtight and hence waterproof seal. The versatile storage bag may be made of a food-grade polyethylene vinyl acetate blend, approximately 90% or less ethylene vinyl acetate and approximately 10% or less polyethylene.

A method for manufacturing a thermoplastic composite product includes: providing a first and second thermoplastic composite component made from a consolidated stack of thermoplastic composite plies, said first and second component having a first and second ply drop off, respectively. The first and second components are positioned such that the first ply drop off and the second ply drop off are aligned, and the first and second components are fixedly connected by means of heating. The stacks of plies for the first and second components are constructed by stacking the plies in a stacking direction wherein the plies are arranged such that plies at a different position along the stacking direction are laterally offset relative to each other for the purpose of forming the first ply drop off and the second ply drop off, respectively, before consolidating.

A non-woven textile may be formed from a plurality of thermoplastic polymer filaments. The non-woven textile may have a first region and a second region, with the filaments of the first region being fused to a greater degree than the filaments of the second region. A variety of products, including apparel (e.g., shirts, pants, footwear), may incorporate the non-woven textile. In some of these products, the non-woven textile may be joined with another textile element to form a seam. More particularly, an edge area of the non-woven textile may be heatbonded with an edge area of the other textile element at the seam. In other products, the non-woven textile may be joined with another component, whether a textile or a non-textile.