A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, the uncured second component is brought into contact with the connecting region and heat is supplied. An interdiffusion layer is formed which fixedly connects the second component and the connecting region to one another and thus joins the first component to the second component.

An object is to provide a composite pre-bonding treatment method that stabilizes quality of a bonded part. The present disclosure provides a composite pre-bonding treatment method performed when bonding a composite material to a member. The method includes: (S2) attaching an absorber adapted to absorb a contaminant to a surface of a prepreg laminate that is a precursor of the composite material; (S3) covering the prepreg laminate with a packaging material from above the absorber; (S4) vacuuming the packaging material and heating the prepreg laminate at a temperature lower than a curing temperature of a prepreg; (S5) then removing the packaging material; (S6) peeling off the absorber; (S7) attaching, to a surface of the prepreg laminate with the absorber peeled off, a release member that does not transfer silicone or fluorine to a resin, and then (S9) curing the prepreg laminate to mold the composite material; and (S11) peeling off the release member from the composite material before bonding the member.

A method of manufacturing a closed cross-section structural member is disclosed. The closed cross-section structural member includes: a first panel and a second panel joined to each other to form a closed cross-section; and a fiber reinforced plastic (FRP) material bonded to the first panel. The method includes: attaching the FRP material to the first panel with an adhesive; curing the FRP material and the adhesive by heating the FRP material and the adhesive together with the first panel; and joining the second panel to the first panel in which the FRP material and the adhesive are cured.

This disclosure is directed to methods directly adhering epoxy-based, and other thermosetting surfacing films to solid thermoplastic surfaces and the structures derived or derivable from these methods. In some embodiments, the disclosure is also directed to composite structures comprising a thermoplastic substrate directly bonded to a thermoset(ting) surfacing film; wherein the direct bonding defines an interface between a thermoplastic surface of the thermoplastic substrate and a first surface of the thermoset(ting) surfacing film.

The present disclosure describes a three-dimensional object. The three-dimensional object includes a light polymerized body, at least one internal chamber residing within the light polymerized body, the at least one internal chamber having at least one frangible wall, and a curable component contained within the at least one internal chamber. The three-dimensional object may further include at least one channel extending inwardly from an outer surface of the light polymerized body toward the internal chamber and at least a portion of the at least one channel being adjacent to the at least one frangible wall of the at least one internal chamber. Methods of bonding an insertable object to a three-dimensional object and kits are also described.

A method of the invention produces a composite material conjugate in which a first composite material and a second composite material are adhered without using an adhesive, wherein a first prepreg laminate to which a release member is attached is cured to form the first composite material, the release member being made of a material that does not transfer silicone and fluorine to the first prepreg laminate, after detaching the release member from the first composite material, surface treatment that imparts polar functional groups to the surface of the first composite material to which the release member was bonded is carried out to activate the surface, a second prepreg laminate is placed directly on the activated surface of the first composite material, and the second prepreg laminate is cured to form a second composite material adhered to the first composite material.

A method for surface preparation of composite substrates prior to adhesive bonding. A curable surface treatment layer containing blocked isocyanate compounds is applied onto a curable composite substrate, followed by co-curing. The surface treatment layer may be a resin layer without fibers or a removal peel ply composed of resin-impregnated fabric. After surface preparation, the composite substrate is provided with a chemically-active, bondable surface that can be adhesively bonded to another composite substrate to form a covalently-bonded structure.

A shear tie connector system for securing a frame component to a composite fuselage skin, which includes a shear tie connector and a fuselage mandrel, which defines a slot within which the shear tie connector is positioned.

A method of forming a structural web for a wind turbine blade comprises providing a web member having a web portion and a flange portion extending away from each other, where 5 a heel of substantially curvilinear form is located between the web portion and the flange portion. A planar flange extender comprising a cured composite material is arranged together with the web member with the flange extender positioned adjacent to the flange portion so that a portion of the flange extender projects past the heel and away from the web portion. The flange extender is integrated with the web member in a resin matrix, or 10 with an adhesive, to form the structural web. A structural web and a wind turbine blade comprising the web is disclosed.

A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, the uncured second component is brought into contact with the connecting region and heat is supplied. An interdiffusion layer is formed which fixedly connects the second component and the connecting region to one another and thus joins the first component to the second component.