A method for connecting first and second plastic parts by a laser transmission bonding wherein the first plastic part absorbs laser light and the second plastic part is made of transparent plastic. The method includes the following steps: positioning the first plastic part in a first tool, positioning the second plastic part in a second tool so that the first plastic part and the second plastic part are spaced from each other thereby preventing mutual heat exchange between the parts, directing laser light through the second plastic part onto a connection zone of the first plastic part whereby the first plastic part is heated at least within the connection zone, after heating the first plastic part, moving the second plastic part into contact with the first plastic part, so that the second plastic part is firmly bonded to the first plastic part.

Disclosed is a welding machine for synthetic resins. The welding machine for synthetic resins performs welding of fabrics using ultrasonic waves and through preheating sufficient not to burn off a coating solution on the surfaces of the fabrics using hot air so as to achieve rapid and firm welding due to concentrated molecular decomposition and melting on the bonding surface between the fabrics, allows both an ultrasonic horn and a welding wheel to be rotated vertically so as to achieve rapid and stable entry of the fabrics and welding of the fabrics while preventing the fabrics from slipping, and achieves stable welding of various fabrics through adjustment of pressing force of the welding wheel depending on the thickness or the material of the fabrics, etc.

The aerospace component joints comprise a first component member comprising a first bonding face, a second component member comprising a second bonding face, one or more bond-enhancing features, and an adhesive layer forming a bond between the first and second bonding faces. The one or more bond-enhancing features comprises a plurality of reinforcing protrusions integral with the first component member, projecting from the first bonding face through the adhesive layer, and into the component member and/or one or more adhesive-receiving recesses defined in the first or second bonding faces and filled by the adhesive layer. The methods of preparing a component member for an aerospace component joint comprise integrating one or more bond-enhancing features into the component member. The methods of forming the aerospace component joint comprise positioning and adhesive-bonding the first bonding face to the second bonding face, and integrating the bond-enhancing feature(s) into the aerospace component joint.

Interfaces for positive pressure therapy having a mask assembly, a headgear assembly and a connection port assembly are disclosed herein. The connection port assembly has a ball joint connection with the mask assembly and includes a quick release button for easily disconnecting the gases source conduit from the mask assembly. The mask assembly may include a bias flow vent that is formed separately and attached to the mask assembly. The headgear assembly encircles the rear region of the user’s head and may include at least some portions that are substantially non-stretchable.

An inventive through transmission connecting device for connecting a first component made of a light absorbing material to a second component made of a light transmissive material by means of a light transmission bonding technology. The connecting device includes a first tool mounted to a first support retaining the first component and a second tool mounted to a second support retaining the second component. The first tool and the second tool are movable with respect to each other and the first tool is at least partly made of or includes a layer of a thermal isolator having a high thermal resistance.

The invention relates to a process (100) for manufacturing an object (1) made of thermoplastic polymer composite from at least two parts (10) made of thermoplastic polymer composite, said thermoplastic polymer composite comprising a fibrous reinforcement and a thermoplastic polymer matrix, said process comprising the steps of: arranging (120) the two parts (10) made of thermoplastic polymer composite adjacently or overlapping at an assembly interface zone (11), and heating (130) to melt the thermoplastic polymer matrix at said assembly interface zone (11), so as to form an object (1) made of thermoplastic polymer composite comprising a welded interface (12).

The present invention relates to a film wrapping machine for a product packing device using a stretch film, including a frame having vertical bars extending upward and spaced apart from each other, a film clamping unit including a pair of suction pads which are moved in a direction of being spaced apart from each other in a state of adsorbing the stretch film so that a front end portion of the stretch film supplied from a film supply device is opened, and a plurality of clamps configured to grip the front end portion of the stretch film opened by the suction pads, receive the stretch film whose upper end is cut and bonded by the film supply device in a wrinkled state, and process the stretch film to be covered on a product in a process of lowering the vertical bars, and a controller which controls operation of the film clamping unit and the film supply device.

The methods herein relate to assembling an elastic laminate with a first elastic material and a second elastic material bonded between first and second substrates. During assembly, an elastic laminate may be formed by positioning the first and second substrates in contact with stretched central regions of the first and second elastic materials. The elastic laminates may include two or more bonding regions that may be defined by the various layers or components of the elastic laminate that are laminated or stacked relative to each other. In some configurations, a first plurality of ultrasonic bonds are applied to the elastic laminate to define a first bond density in the first bonding region, and a second plurality of ultrasonic bonds are applied to the elastic laminate to define a second bond density in the second bonding region, wherein the second bond density is not equal to the first bond density.

A method for welding thermoplastic components, in particular, thermoplastic fiber composite structural components for an aircraft or spacecraft, having the following steps. Arranging an insert, which has a conductor structure having a plurality of parallel electrical conductor elements, in a joining zone between a first thermoplastic component and a second thermoplastic component such that at least some portions of the parallel electrical conductor elements are located in the joining zone; locally melting the components in the region of the joining zone by supplying current to the conductor structure; disconnecting the connector elements; and removing the insert from the joining zone by pulling out the disconnected conductor elements. An insert for the resistance welding of thermoplastic components is also provided.

The present disclosure relates to methods for assembling elastic laminates that may be used to make absorbent article components. Particular aspects of the present disclosure involve providing a first substrate and a second substrate, the first substrate and the second substrate, each having a width in a cross direction; providing an activated elastic material; elongating the activated elastic material; and ultrasonically bonding the first substrate together with the second substrate with the elongated activated elastic material positioned between the first substrate and the second substrate.