Provided is a molded article which contains a first enclosure; a second enclosure adjoined with the first enclosure; and a transparent member held by the second enclosure, each of the first enclosure and the second enclosure being independently made from a resin composition that contains a polyamide resin having a semi-crystallization time of 10 to 60 seconds, and a melting point of 200 to 280° C., and the transparent member having a pencil hardness of 8H or larger, and a linear expansion coefficient of 1×10.sup.−6 to 9×10.sup.−6/° C., where the semi-crystallization time means a time measured by depolarization photometry at a temperature 20° C. higher than the melting point of the polyamide resin, for a melting time of polyamide resin of 5 minutes, and at a temperature of crystallization bath of 150° C.

A method and apparatus for attaching a branch polymeric fitting to a host polymeric pipe in which a flexible heating blanket is inserted between and used to heat the respective branch and host pipe surfaces. When the parts reach the appropriate temperature, the pipes are separated a small distance and the heating blanket is removed. The branch fitting and host pipe are then fused by placing the heated pipe ends in contact and applying pressure.

Described herein is a process for producing a molded body which encloses a cavity, by welding two partial bodies. Also described herein is a die with which the process of producing the molded body can be carried out. Also described herein is a molded body which can be obtained by the process.

There is provided a method for producing a metal-resin composite including a metal member and a resin member which are joined together, the resin member containing at least a thermoplastic resin. The method includes a step of joining together the resin member and the metal member by melting the resin member with the frictional heat generated in the surface of the metal member on its side opposite to the resin member in a state where the metal member and the resin member are superposed. The melting point of the thermoplastic resin is 260° C. or more.

There is provided a method for producing a metal-resin composite including a metal member and a resin member which are joined together, the resin member containing at least a thermoplastic resin. The method includes a step of joining together the resin member and the metal member by melting the resin member with the frictional heat generated in the surface of the metal member on its side opposite to the resin member in a state where the metal member and the resin member are superposed. The melting point of the thermoplastic resin is 260° C. or more.

A pair of thermoplastic resin members are placed on an anvil. A pressing force of a tool horn vibrating ultrasonically in a direction not perpendicular to but along upper surfaces of the pair of thermoplastic resin members is applied to the upper surfaces. The application of the pressing force of the tool horn vibrating ultrasonically allows melting of a vicinity of the upper surfaces of the pair of thermoplastic resin members. A welded structure part is formed on an unwelded structure part, thereby welding the pair of thermoplastic resin members as an overlap structure including the welded structure part arranged on the unwelded structure part. The distance and positional relationship between the pair of thermoplastic resin members after the welding are unchanged before and after the welding. The surfaces, placed on the anvil, of the thermoplastic resin members are neither burned nor discolored.

Aspects of the disclosure relate to manufacturing a balloon envelope for use in a stratospheric balloon system. For instance, a stream of polyethylene mixture us extruded through an extruder in order to orient molecules of polymer chains of polyethylene and to provide an oriented film. The oriented film is passed through an electron beam and thereby crosslinking the polymer chains to provide a cross-linked film. The cross-linked film is heat sealed to form the balloon envelope.

A fluid impervious stitching method for a seam of a vapor-permeable virus-barrier laminate. The laminate comprises: at least one thermoplastic resin fiber layer; at least one vapor-permeable virus-barrier thermoplastic elastomer film layer; and a bonding layer located between the two layers and formed of an adhesive capable of being fused with the two layers. In the stitching method, overlapping or stacking is performed to form a seam, and heat sealing is performed on the laminate at the seam. The temperature of heat sealing is higher than the melting point of a material layer having the highest melting point in the laminate, but lower than the temperature at which perforation or decomposition occurs in any material layer in the laminate. The heat-stitched seam has excellent windproof, vapor-permeable, virus barrier and liquid-barrier performance, has a smooth appearance without wrinkles, and feels soft. Also provided is a protective textile product prepared by means of the stitching method.

A method of producing flexible polypropylene fabric bags with heat fused seams comprising providing fabric pieces, wherein each fabric piece has a coated side and an uncoated side; positioning fabric pieces so that a coated side of one fabric piece faces a coated side of another fabric piece; selecting an area of fabric to be joined for forming a seam or joint; applying heat to the area to be joined that is less than the melting point of the fabrics, for forming one or more seams or joints and wherein the heat fused seams or joints of a resulting polypropylene bag retains at least 85% of the fabric strength without using sewing machines.

A fuselage structure of an aircraft includes a fuselage skin, and a plurality of frame elements spaced apart from one another in a direction parallel to the aircraft longitudinal axis for supporting the fuselage skin. The fuselage skin includes a plurality of interconnected fiber-reinforced composite skin panels that extend between each pair of frame elements and are connected thereto. The composite skin panels further comprise a stiffener integrally formed in each composite skin panel. A method for manufacturing the fuselage skin. The composite skin panels may be interconnected and/or connected to a frame element through an induction welded connection.