A method for the connection of moulded parts, wherein a locking collar pin with locking grooves or with an external thread, is driven through the moulded parts and subsequently a locking collar is locked together with at least some of the locking grooves, or with threaded sections of the locking collar pin, by the application of radial pressure, or by means of a screwing operation. A connecting system with a locking ring pin, which has a punching section for purposes of punching through the moulded parts, and also locking grooves for purposes of active engagement with a locking ring; the latter extends over at least two adjacent locking grooves in the axial direction, or over at least two adjacent threads in the axial direction.

A method for the connection of moulded parts, wherein a locking collar pin with locking grooves or with an external thread, is driven through the moulded parts and subsequently a locking collar is locked together with at least some of the locking grooves, or with threaded sections of the locking collar pin, by the application of radial pressure, or by means of a screwing operation. A connecting system with a locking ring pin, which has a punching section for purposes of punching through the moulded parts, and also locking grooves for purposes of active engagement with a locking ring; the latter extends over at least two adjacent locking grooves in the axial direction, or over at least two adjacent threads in the axial direction.

When overlapping and joining together end portions of a rubber member, it becomes possible to join them at a joining area smaller than a conventional one by increasing the joining area. There is provided a joining device for overlapping end portions, of a rubber member (tire constituent member) with one upper end portion placing on the other lower end portion and joining the end portions of the rubber member, in which a pressing roll (disk-shaped roll) rotating about an inclined shaft is rolled while being pressed against the overlapped upper end portion of the rubber member, and the upper end portion is extended by a shearing force generated at this time to increase a joining area between the both end portions.

When overlapping and joining together end portions of a rubber member, it becomes possible to join them at a joining area smaller than a conventional one by increasing the joining area. There is provided a joining device for overlapping end portions, of a rubber member (tire constituent member) with one upper end portion placing on the other lower end portion and joining the end portions of the rubber member, in which a pressing roll (disk-shaped roll) rotating about an inclined shaft is rolled while being pressed against the overlapped upper end portion of the rubber member, and the upper end portion is extended by a shearing force generated at this time to increase a joining area between the both end portions.

The present disclosure is directed to a method of assembling a modular rotor blade of a wind turbine. The method includes identifying a main blade structure, constructed at least in part, from at least one of a thermoset or a thermoplastic material. The method also includes identifying at least one blade segment, constructed at least in part, of a thermoplastic material reinforced with at least one of glass fibers or carbon fibers. Thus, the method also includes securing the at least one blade segment to the main blade structure, e.g. via welding.

The present disclosure is directed to a method of assembling a modular rotor blade of a wind turbine. The method includes identifying a main blade structure, constructed at least in part, from at least one of a thermoset or a thermoplastic material. The method also includes identifying at least one blade segment, constructed at least in part, of a thermoplastic material reinforced with at least one of glass fibers or carbon fibers. Thus, the method also includes securing the at least one blade segment to the main blade structure, e.g. via welding.

Disclosed are thermoset/thermoplastic composites that include a thermoset component directly or indirectly bonded to a thermoplastic component via a crosslinked binding layer between the two. The crosslinked binding layer is bonded to the thermoplastic component via epoxy linkages and is either directly or indirectly bonded to the thermoset component via epoxy linkages. The composite can be a laminate and can provide a route for addition of a thermoplastic implant to a thermoset structure.

Disclosed are thermoset/thermoplastic composites that include a thermoset component directly or indirectly bonded to a thermoplastic component via a crosslinked binding layer between the two. The crosslinked binding layer is bonded to the thermoplastic component via epoxy linkages and is either directly or indirectly bonded to the thermoset component via epoxy linkages. The composite can be a laminate and can provide a route for addition of a thermoplastic implant to a thermoset structure.

Systems, methods, and apparatus for using aircraft bondline embedded current sensors to determine a lightning damage index are disclosed. A method of predicting lightning strike damage to at least one type of aircraft involves sensing, with at least one current sensor node embedded in at least one type of aircraft, induced current. The method further involves generating, with at least one current sensor node, at least one current signal representative of the induced current. Also, the method involves determining, electromagnetic density data associated with at least one region of at least one type of aircraft by using at least one current signal. Further, the method involves creating an index that provides a numeric representation for predicted lightning strike damage to at least one type of aircraft based on the electromagnetic density data, dimensions of at least one type of aircraft, and design features of at least one type of aircraft.

Systems, methods, and apparatus for using aircraft bondline embedded current sensors to determine a lightning damage index are disclosed. A method of predicting lightning strike damage to at least one type of aircraft involves sensing, with at least one current sensor node embedded in at least one type of aircraft, induced current. The method further involves generating, with at least one current sensor node, at least one current signal representative of the induced current. Also, the method involves determining, electromagnetic density data associated with at least one region of at least one type of aircraft by using at least one current signal. Further, the method involves creating an index that provides a numeric representation for predicted lightning strike damage to at least one type of aircraft based on the electromagnetic density data, dimensions of at least one type of aircraft, and design features of at least one type of aircraft.