A method for joining together different components or different sections of a single component, wherein at least one of the components is a thermoplastic fiber composite component, by using a threaded fastener. Heat is used for softening the thermoplastic fiber composite component to be joined together with the threaded fastener. A joined-together fiber composite component of a vehicle, aircraft or spacecraft, can be obtained by the disclosed 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.

Method of making golf ball comprising aligning thermoformed depressions with dimpled mold cups and applying sufficient heat and suction to the thermoformed depressions without exposing any preselected subassembly to the heat and suction to soften the polymeric material of each thermoformed depression and draw air outward from a volume located between an inner surface of the dimpled mold cup and an outer surface of the thermoformed depression to form a thermoformed pre-form half-shell having an outer surface with the size, shape and contour of the inner surface of the dimpled mold cup(s) and an inner surface with the size, shape and contour of the outer surface of a preselected subassembly. Afterwards, a preselected subassembly is loaded between a pair of thermoformed pre-form half-shells and molded under sufficient short-term heat and suction to form the golf ball. The thickness of each thermoformed depression and thermoformed pre-form half-shell may be tapered.

Provided among other things is a method of affixing a small, single chip to a plastic item, the chip having a top surface having length and width dimensions, and having a height, the method comprising: (1) vacuum adhering a top-oriented surface of the chip to a probe of outer dimensions comparable to or smaller than those of the length and width; (2) conveying heat to the chip via the probe such that a bottom-oriented surface of the chip is sufficiently hot to melt the plastic; (3) applying via the probe the chip to the plastic such that the chip embeds in the plastic; and (4) releasing the chip from the probe, wherein the largest of the length and width is about 500 microns or less, and height is no more than about the smallest of length and width.

A method of making a joint for a structure comprises forming a thermoplastic filler, applying an uncured first thermoset layer into direct contact with the thermoplastic filler, applying an uncured second thermoset layer into direct contact with the thermoplastic filler, and applying an uncured third thermoset layer into direct contact with the thermoplastic filler. The method additionally comprises curing the uncured first thermoset layer, the uncured second thermoset layer, and the uncured third thermoset layer at a temperature below a melting temperature of the thermoplastic material to form a cured first thermoset layer, a cured second thermoset layer, and a cured third thermoset layer and bonding together the cured first thermoset layer, the cured second thermoset layer, the cured third thermoset layer, and the thermoplastic filler.

A device comprising a first fixing element, a further fixing element, and a folded planar composite is disclosed. The first fixing element comprises a first fixing surface and the further fixing element comprises a further fixing surface. The folded planar composite is at least partially fixed between the first fixing surface and the further fixing surface. The folded planar composite comprises a first composite region and a further composite region.

A method of making a storage bag comprising the following steps performed in any order: (a) forming a composite tube having an inner surface comprising a higher melting polymer, an outer surface comprising a lower melting polymer, two ends, and a diameter; (b) flattening the tube in a direction perpendicular to the diameter; (c) forming a joint at one of the ends at a temperature between respective melting points of the higher melting polymer and the lower melting polymer; (d) providing a composite sheet having a first side comprising a higher melting polymer and a second side comprising a lower melting polymer; and (e) disposing the composite sheet over the joint such that the first side comprising a lower melting polymer engages the joint and forming a lap seam over the joint at a temperature between respective melting points of the higher melting polymer and the lower melting polymer, and a storage bag made by such method.

A centrifugal blood pump prevents a shaft member from oscillating due to expansion of a pump housing resulting from pressurization of the blood. The centrifugal blood pump is manufactured by assembling a bottom member 21 and a lid member 22, and compressing them in a direction in which the bottom member 21 and the lid member 22 approach each other by a deformation amount along their outer circumferential walls. The lid member and the bottom member are joined while in the compressed state in order to create a preloading force between the shaft member and bearings to resist the expansion due to pressurization of the blood during use.

A method for connecting two aircraft components composed of thermoplastic composite material by a rivet. The two aircraft components are arranged, in sections, areally on one another, before bores in the two aircraft components are expanded by a mandrel element such that the bores, after the expansion, form one continuous bore for receiving the rivet. Here, the two aircraft components are locally warmed by the mandrel element such that, during the expansion of the bores, the components are thermoplastically deformed. The mandrel element is inserted through the first bore into the second bore. The rivet is introduced into the continuous bore. A system for carrying out the method is also disclosed.

A process for producing a polymeric stiffened sheet-like component, for example a panel, for aircraft construction. Production includes integration of hollow stiffening profiles, for example closed omega stringers, onto a sheet-like component, for example an external skin, where the stringers and external skin are produced from thermoplastic composite material. The stringers are integrated onto the external skin by establishing contact between the stringers and the external skin and melting thermoplastic composite material with exposure to heat and pressure at the areas of contact between external skin and stringers. Melting of the other sections of the stringers is avoided with a pressurized cooling fluid with a temperature significantly below the melting point of thermoplastic composite material, the fluid flowing through the airtight enclosed space in the stringers. Use of closed airtight thermoplastic omega stringers allows integration of the stringers onto the external skin in absence of any flexible tube within the stringers.