Abstract: A wiring board (3) according to an embodiment of the present invention includes an inorganic insulating layer (11A); a first resin layer (12A) on one main surface of the inorganic insulating layer (11A); a second resin layer (13A) on another main surface of the inorganic insulating layer (11A); and a conductive layer (8) partially on one main surface of the second resin layer (13A), the one main surface being on an opposite side to the inorganic insulating layer (11A). The inorganic insulating layer (11A) includes a plurality of first inorganic insulating particles (14) which are bound to each other at a part of each of the first inorganic insulating particles and gaps (G) surrounded by the plurality of first inorganic insulating particles (14). A part of the first resin layer (12A) and a part of the second resin layer (13A) are located inside the gaps (G).

Abstract: A wiring substrate includes an adhesive layer, a wiring layer, and a support substrate. The adhesive layer includes a first surface and a second surface that is opposite to the first surface. The wiring layer is formed on the first surface of the adhesive layer. The support substrate is formed on the second surface of the adhesive layer. The wiring layer is partially exposed in a through hole extending through the adhesive layer and the support substrate in a thicknesswise direction. The support substrate is adhered to the adhesive layer in a removable manner.

Abstract: A method and apparatus for fabricating a composite part, such as a fuselage or internal stiffener, with a shape memory polymer (SMP) apparatus usable as a rigid lay-up tool. The SMP apparatus may be heated until malleable, shaped, and then cooled in a desired rigid tool configuration. For example, cavities may be formed into the SMP apparatus for nesting components therein to co-bond or co-cure with the composite part. The composite material and/or nested components may be heated and compressed against the SMP apparatus. The SMP apparatus may be configured to remain rigid during the composite cure cycle. Once the composite material is cured, the SMP apparatus may be triggered to a malleable state and urged away from the cured composite material.

Abstract: A damped composite structure is formed from a matrix material and a plurality of shape memory alloy wire fibers held in the material matrix for damping the structure. The wire fibers may be embedded in a viscoelastic interlayer to increase damping of the structure. The wire fibers may be interspersed with reinforcement such as carbon fibers, in tows or in a mesh of fibers. The wire fibers have an inherent material loss factor greater than approximately 0.10, and may be formed from superelastic metal alloys, such as Ni—Ti, Cu—Zn—Al, Cu—Al—Ni, OR Cu—Al—Be.

Abstract: A method for the production of a stiffener on a surface of an element that is to be made rigid, whereby at least one of the two is made of a composite material that is not completely polymerized, whereby the stiffener includes—in a transverse direction—two contact zones with the surface between which the stiffener and the element to be made rigid form a cavity that empties out at least one of the ends of the stiffener, includes using a core that is placed in the cavity and removed from the cavity after polymerization. The core has a first part that has a low expansion coefficient to ensure the geometric precision required and at least one second part that has a significant elongation coefficient to make possible the extraction of the part by traction on one of the ends of the second part so as to cause a contraction of its cross-section.

Abstract: A method and an apparatus for retaining magnetic properties of a magnet while undergoing manufacturing processes are presented. Ferrous materials with relatively good magnetic permeability are disposed adjacent to poles of magnet substantially containing magnetic field lines from the magnet within the ferrous materials. When the magnetic field lines are thereby substantially contained, the magnet can be exposed to elevated temperatures without losing magnetization strength. Adhesives, particularly adhesives that cure when exposed to elevated temperatures can be used with magnets configured to contain magnetic field lines without having the magnets lose magnetic strength.

Abstract: Paint film composites comprise sheet metal, a color layer, and an optional transparent protective layer. Methods of making and using the paint film composites, and shaped articles made thereby, are also disclosed.

Abstract: A friction device (1) for a clutch, comprising at least two opposite annular friction linings (2, 2?) each having at least one friction body attached to a support (4, 4?) and elastic means (3) arranged between the opposite supports (4, 4?) so as to allow the supports to move axially together or apart by compression or relaxation of the elastic means (3). The friction device (1) furthermore has means for limiting the axial spacing between the supports, formed by at least one stop member (15) extending axially from one support (4) to the other (4?) and disposed on the radially outer (14) or inner periphery of the supports (4, 4?).

Abstract: A method of manufacturing a composite panel is described. The method includes pre-stabilizing a honeycomb core with at least one layer of a pre-stabilizing material, surrounding the honeycomb core with at least one composite laminate skin layer, and curing the at least one composite laminate skin layer.

Abstract: The present disclosure provides a method including forming a polymer layer defining a side of an eye-mountable device. The method may also include providing an adhesive in a ring-shaped pattern on a ring-shaped substrate or on the first polymer layer. The method may also include providing the ring-shaped substrate on the first polymer layer in a predetermined rotational orientation. The method may also include applying a force to one or more of the ring-shaped substrate and the polymer layer to adhere the first polymer layer to the ring-shaped substrate. The method may also include curing the ring-shaped substrate and the first polymer layer.

Abstract: This invention provides a method for producing a structural component, particularly in the aerospace sector. An unhardened prepreg fabric is formed from a composite fiber material, hardenable at a first hardening temperature, into a predetermined shape. The unhardened prepreg fabric is then connected to at least one hardening part of a composite fiber material partially hardened at a second hardening temperature for holding the unhardened prepreg fabric in the predetermined shape, wherein the second hardening temperature is lower than the first hardening temperature. In a further method step the unhardened prepreg fabric connected to the at least one holding part is hardened at the first hardening temperature to form the structural component.

Abstract: A unitary reflector system and methods for forming that include a reflector and support structure. These two structures can form a single unitary structure. Such a reflector system can be constructed from composite laminate materials that are laid up or formed in during a single manufacturing process. The composite support structure can be formed on the back of the reflector using standard laminate techniques. An extractable tool, can include a rigid core, one or more foam blocks, which may be shape a memory polymer foam, an elastic membrane, and a nozzle. The foam blocks can be shaped to provide a mold of the composite structure being manufactured. This mold may require the extractable tool to be trapped by the composite structure after manufacture. Use of the foams can allow the extractable tool to shrink in at least one dimension in order to extract the tool from the trapped configuration.

Abstract: Methods and apparatus for molding and joining composite parts are disclosed herein. An example method includes positioning a base mandrel over a tool base, laying up plies of material over the base mandrel and the tool base to form a support structure base layup, curing the support structure base layup to form a support structure base, removing the support structure base from the tool base and the base mandrel, and configuring the support structure base to be a first support structure for use with a first radar assembly or a second support structure for use with a second radar assembly.

Abstract: Systems, tools, and methods for forming composite tubular stringers and stiffened composite structures having composite tubular stringers are disclosed. Systems include a tool, a supply of pliable blanks for forming composite tubular stringers with the tool, a supply of skin segments for forming a skin, and a layup mandrel for receiving the composite tubular stringers and the skin to form a stiffened composite structure. Tools include a wrapping mandrel for forming from a pliable blank a tubular structure with a first circumferential profile, and a transition mandrel for conforming the tubular structure to a second circumferential profile. Methods include wrapping a pliable blank around a wrapping mandrel to define a tubular structure having a first circumferential profile, and transitioning the tubular structure from having the first circumferential profile to having a second circumferential profile.

Abstract: A method for manufacturing a blade spar for a wind turbine blade includes positioning a first spar segment having a first adhering portion; positioning a second spar segment having a second adhering portion at the first spar segment such that the first adhering portion and the second adhering portion are at least partially overlapping, wherein an adhesive is at least partially provided between the overlapping adhering portions; providing at least one fiber layer impregnated with an uncured resin on the outer surfaces of the first and second spar segments at least in the joint region of the first and second spar segments; and simultaneously curing the adhesive and the resin, thereby fixating the first and the second spar segments to each other.

Abstract: A method for a composite panel having a desired void content is disclosed. The method comprises the step of laying on a surface a first ply of resin. A first filament is placed on the first ply, and a second ply of resin is laid on the first ply and the first filament to form a first intermediate composite panel. The first intermediate composite panel is cured in an autoclave to form a second intermediate composite panel. The second intermediate composite panel is submerged in a solution that dissolves the first filament.

Abstract: The present invention is directed to an air spring sleeve comprising: an outer layer, at least one reinforcing layer, and an inner layer that form the sleeve; the outer layer and the inner layer are formed of an elastomeric composition, with the proviso that the elastomeric composition does not comprise epichlorohydrin; and the at least one reinforcing layer comprises a plurality of reinforcing elements disposed between a layer of the elastomeric composition, wherein the elastomeric composition of the at least one reinforcing layer is identical to the elastomeric composition of the outer layer and the inner layer.

Abstract: An adhesive film, a method for preparing an adhesive film, and an organic electronic device are provided. According to the adhesive film in exemplary embodiments of the present invention, fluidity of an adhesive can be controlled in the case of applying the adhesive between objects to be subsequently adhered to each other and then thermal-compressing by including an adhesive layer with cured side faces contacting with the outside. The adhesive film is used, for example for assembling a panel and the like, and thereby a defect rate at the time of assembling a panel and the like can be reduced and excellent work characteristics can be provided. In addition, before being applied to a panel or the like, a moisture absorbent included inside an adhesive layer of an adhesive film can be protected from external moisture or the like, thereby being easily stored, and also when it is applied to a product, reliability of life span, and the like can be secured.

Abstract: Methods for using a reusable quick release fastener system include engaging and disengaging fastening devices composed of elastomers or shape memory polymers and their composites wherein the fastening devices may be of any number of geometrical shapes such that the mating geometries of each device are compatible with one another. The fastening devices provide an easy and near silent closure mechanism for a container, for example. Thus, the methods for using reusable quick release fastener systems including the fastening devices made of elastomers or shape memory polymers can be used to attach one part to another or to quietly close a pocket, box, or other container, for example.

Abstract: Cleanable articles having overcoats with hydrophilic front surfaces and which are siloxane-bonded to an underlying body member. Also, methods of making and using such articles.

Abstract: A method for manufacturing a composite structure. A filler material with a barrier material for a channel in the filler material is formed. A composite material and the filler material with the barrier material are laid up onto a tool in a shape of the composite structure. The composite material and the filler material in the shape of the composite structure are cured.

Abstract: A chemical sensor comprising: a hydrogel layer, comprising one or more molecular recognition agents and a 2DPC self-assembling array; and a mirror layer. A method for analyzing a sample or bodily fluid, comprising: obtaining a sample or bodily fluid; placing an amount of the sample or bodily fluid onto a chemical sensor, comprising: a hydrogel layer, comprising a molecular recognition agent and a 2DPC self-assembling array; a tethering hydrogel layer; a mirror layer; and a membrane filter layer, allowing the bodily fluid to interact with the hydrogel layer; and allowing ambient or artificial light to pass through the hydrogel layer onto the mirror layer and observing a change in diffraction versus a control.

Abstract: A composite structure is fabricated by staging at least a portion of an uncured, first composite component. The first composite component is assembled with a second composite component, and the staged portion of the first composite component is cocured with the second composite component.

Abstract: A method for producing an object of composite material comprising the steps of: placing one or several prepregs on a plane surface, forming a fiber stack; lifting over the fiber stack to a molding tool; downforming the fiber stack; curing the downformed fiber stack; where the method also comprises the step of: orienting the fiber directions so that all fibers, when the fiber stack is lifted over to the molding tool, will cross an edge of the molding tool only once.

Abstract: The present invention regards an aircraft structure comprising an aerodynamic composite shell (7), the interior face (9) of which in whole or in part is bonded with at least one two- or three-dimensional structural composite part (11) by means of a bonding material (15). It also regards a method of manufacture of the aircraft structure. The bonding material (15) comprises a non-structural fiber reinforced resin system, wherein at least one portion of the bonding material, which portion spatially corresponds with an interior face filling volume (21), is thicker than other portions of the bonding material (15), due to settlement of resin of the non-structural fiber reinforced resin system in said interior face filling volume (21) during the viscous phase of the curing of the non-structural fiber reinforced resin system.

Abstract: A method of making a microfluidic diagnostic device for use in the assaying of biological fluids, whereby a layer of adhesive in a channel pattern is printed onto a surface of a base sheet and a cover sheet is adhered to the base sheet with the adhesive. The layer of adhesive defines at least one channel, wherein the channel passes through the thickness of the adhesive layer.

Abstract: A method of forming a fan blade includes the step of applying an adhesive layer around a leading edge of a fan blade body. The adhesive layer includes an adhesive film supported by a scrim cloth, and the adhesive layer contacts a portion of an inner surface of the fan blade body and a portion of an outer surface of the fan blade body. A leading edge sheath is positioned relative to the fan blade body such that a first flank and a second flank of the leading edge sheath is positioned over the portion of the inner surface and the portion of an outer surface, respectively, of the fan blade body. Pressure is applied to the first flank and the second flank of the leading edge sheath to secure the leading edge sheath to the blade body and curing the adhesive film.

Abstract: Novel methods and kits for creating defects in composite materials, as well as an engineered part or structure with one or more designed defects, are disclosed. The disclosed inventions advantageously permit the intentional introduction of one or multiple defects of any desired size and shape, either between the same two chosen laminae or on different layers within a multi-layer composite, having mechanical and thermal properties that are akin to those found for actual defects. One disclosed method involves creating a mask having a cut-out in the size and shape of a desired defect, placing the mask at a location on a first substrate where the defect is desired, applying a release agent, removing the mask, and adding a second substrate over the first substrate with release agent. The first substrate may be a cured lamina or an uncured lamina pre-impregnated with resin having a barricade in the size and shape of the outline of the desired defect.

Abstract: A composite structure is fabricated by staging at least a portion of an uncured, first composite component. The first composite component is assembled with a second composite component, and the staged portion of the first composite component is cocured with the second composite component.

Abstract: A chemical two-component mortar compound including a resin component (A) that contains at least one radically curable, ethylenically unsaturated compound (a) as the curable component, and including a separately arranged so as to inhibit reaction curing component (B) that contains a curing agent for the resin of the resin component (A), with improved adhesion to the surface of partially cleaned and/or moist holes in mineral substrates, characterized by a content of 0.

Abstract: A method for making a structural element comprising a panel in composite material with fiber reinforcement in an organic matrix obtained by laying up and curing. The panel comprises a side likely to be exposed to contact with hydrocarbons. The required layer structure is obtained by laying up the plies of fibers pre-impregnated with resin having a curing temperature T1. A ply made of a thin film of polymer that can withstand hydrocarbons and the curing temperature T1, referred to as the protective film, is applied on the side exposed to hydrocarbons. The entire layered structure is cured under pressure at the temperature T1.

Abstract: Provided is a dry lamination method, and a laminate having superior appearance obtained by the method. The method in which an adhesive having a solid matter content of 35 wt % or more diluted in a solvent is applied onto a film according to a gravure process, the solvent is volatilized, and the resulting film is adhered with another film to obtain a laminate, wherein the adhesive is applied by: a gravure cylinder in which the screen number of gravure cylinder is 135 to 270 lines/inch and cell volume is 10 to 30 cc/m2; a gravure cylinder which is engraved by an electronic engraving machine to have a stylus angle of 120 to 140° and the screen number of gravure cylinder of 120 to 270 lines/inch; or a ceramic roll in which the screen number of gravure cylinder is 135 to 350 lines/inch and cell volume is 10 to 30 cc/m2.

Abstract: The invention relates to a method for joining cured stringers to at least one structural component of an aircraft or spacecraft, including placing the stringers onto the at least one structural component, depositing and pressing respective vacuum film strips such that each strip is attached to a pair of stringers and present between the pair of stringers with the use of vacuum sealing means in such a manner that a continuous vacuum arrangement, comprising the covering vacuum films and the vacuum film strips, is formed, and pressurized joining of the stringers to the at least one structural component by means of the continuous vacuum arrangement formed.

Abstract: The disclosed embodiments offer a solution for controlling the thickness of a finished structural composite part when precise tolerances must be complied with for the quality of the assembly and in order to ease the assembly operations of this part. In order to implement the method according to the disclosed embodiments, an additional layer of plies made out of a non-structural composite material, called calibrating plies, is applied onto the structural plies of the structural part, at least in an area where the thickness must be maintained within close tolerances and, after the composite material has been cured, the calibrating plies are machined in order to obtain the thickness required for the finished part. The thickness of the calibrating plies applied is determined according to the possible thicknesses of structural plies, taking into account the manufacturing spreads so that the machining operation for the calibrating plies does not affect the structural plies.

Abstract: The invention relates to a method for bonding a thermoplastic polymer to a thermosetting polymer component, the thermoplastic polymer having a melting temperature that exceeds the curing temperature of the thermosetting polymer. The method comprises the steps of providing a cured thermosetting polymer component comprising an implant of a thermoplastic polymer at least at the part of the thermosetting polymer component to be bonded, locating a thermoplastic polymer in contact with at least the part to be bonded, heating the assembly to the melting temperature of the thermoplastic polymer, whereby the thermoplastic polymer of the implant melts and fuses with the thermoplastic polymer, and cooling the assembly.

Abstract: A process for bonding a semi-crystalline or crystalline thermoplastic polymer to a thermosetting polymer component, the process including selecting compatible semi-crystalline thermoplastic polymer and uncured thermosetting polymer components wherein the curing temperature of the uncured thermosetting polymer components is above the melting temperature of the semi-crystalline thermoplastic polymer. The process includes locating the thermoplastic polymer in contact with the uncured thermosetting polymer component and heating the thermoplastic polymer and uncured thermosetting polymer or thermosetting polymer composite component to the curing temperature of the thermosetting polymer components and the thermoplastic polymer are able to at least partly interpenetrate before the thermosetting polymer cures. The thermoplastic polymer and cured thermosetting polymer component are then cooled such that the thermoplastic polymer is very strongly bonded to the cured thermosetting polymer component.

Abstract: A method for joining fittings to a composite sandwich shell edge includes laying up an inner facesheet and positioning a wrapped flute mandrel on top; applying a layer of adhesive on the inner facesheet and positioning spacer-supported fittings on top; applying adhesive over the co-bonded fittings and laying up an outer facesheet forming an assembly; curing the assembly under heat and pressure; removing the fittings by first collapsing the spacers and removing the flute mandrel; placing an adhesive layer on the fittings with collapsible spacers inserted therein; reinserting the fittings between the inner and outer facesheets and effecting bonding and curing; and removing the spacers from the fittings by collapsing the spacers.

Abstract: A method of producing a building panel (1), including: providing a core (2), applying a balancing layer (6) having a first moisture content on a first surface (3) of the core (2), the balancing layer (6) comprising a sheet impregnated with a thermosetting binder, applying a surface layer (12) having a second moisture content on a second surface (4) of the core (2), the surface layer (12) comprising a thermosetting binder, adjusting the first moisture content of the balancing layer (6) such that the first moisture content of the balancing layer (6) is higher than the second moisture content of the surface layer (12) prior to curing, and curing the surface layer (12) and the balancing layer (6) by applying heat and pressure. Also, a semi-finished product adapted to be cured for forming a building panel (1).

Abstract: Provided is a process for production of composite fine particles with heterogeneous surfaces. The process ensures a high productivity and enables a voluntary control of particle diameters. Further, the process imposes no restrictions on heterogeneous substances added for functional expression, and allows a heterogeneous substance to be encapsulated in central portions of composite fine particle spheres. A composite film obtained by laminating two or more kinds of films is cut into minute pieces, followed by melting the same to obtain spherical minute pieces. Particularly, liquid films are separately formed with two or more kinds of liquids containing polymerizable monomers. Further, two or more kinds of films can thereby be obtained through polymerization. The two or more kinds of films thus obtained are then laminated to further allow polymerization to take place, thus obtaining the composite film.

Abstract: Embodiments of the present disclosure present electrically conductive, thermosetting compositions for use in surfacing films and adhesives. The surfacing films possess enhanced electrical conductivity, comparable to metals, without the use of embedded metal screens or foils. Such surfacing films may be incorporated into composite structures (e.g., prepregs, tapes, and fabrics), for example, by co-curing, as an outermost surface layer. In particular, compositions formed using silver flakes as conductive fillers are found to exhibit very high electrical conductivity. For example, compositions including greater than 45 wt. % silver flake exhibit resistivities less than about 55 m?/sq. In this manner, the surfacing films as an outermost conductive layer may provide lighting strike protection (LSP) and electromagnetic interference (EMI) shielding when used in applications such as aircraft components.

Abstract: A sport ball may include a casing, a bladder, and a valve. The casing forms at least a portion of an exterior surface of the ball. The bladder is located within the casing for enclosing a pressurized fluid, and the bladder may be formed from a material that includes a first layer of thermoplastic polymer material and a second layer of a barrier material. The valve is for introducing the fluid to the bladder, and the valve is secured to the bladder and accessible from an exterior of the casing. A tie layer may be located between the flange and a surface of the bladder to join the flange to the bladder.

Abstract: A process for fabricating an integrated panel structures and the structures thereby fabricated are provided with first and second stiffeners positioned on a base skin so that the stiffeners intersect at respective intersecting regions. First and second fiber-reinforced resin-composite overlapping layers are provided on the first and second stiffeners so that at least lateral regions thereof are laminated to a corresponding region of the base skin. The base skin and the overlapping layers may be assembled with the first and second stiffeners to form a panel preform which may then be subjected to curing conditions so as to co-cure all previously uncured components and thereby form an integrated composite panel structure with mutually intersecting first and second stiffeners.

Abstract: A method for producing a molded body in which the matrix of a composite material is prevented from penetrating into carbon foam. The method includes: disposing a thermosetting adhesive (3) on a porous body (2), disposing a composite material (4) containing a thermosetting resin as a matrix on the adhesive, curing the adhesive, and liquefying and curing the matrix of the composite material after the adhesive has been cured. In this production method, because the cured adhesive bonds strongly to the porous body before the matrix of the composite material is liquefied, the subsequently liquefied matrix of the composite material can be prevented from penetrating into the interior of the porous body.

Abstract: A method of manufacturing or surface treating a wire wrapped screen for use in a wellbore improves the erosion resistance of the wire-wrapped screen. The wire-wrapped screen can be disposed on an axle positioned in a chamber containing a source of erosion resistant surface coating. The coating is then deposited on the exterior of the wire-wrapped screen using a deposition process, such as physical vapor deposition or thermal spraying. Alternatively, a spray system proximate the wire-wrapped screen can have a deposition nozzle to coat the exterior surface of the screen with an elastomer coating by spraying an elastomer. In additional embodiments, the wire for the wire-wrapped screen can first be treated for erosion resistance and then wound about a mandrel to form the wire-wrapped screen.

Abstract: An actinic radiation activated, thermally curable solid film adhesive is disclosed that includes a film forming polymeric binder, a cationically curable resin, and a cationic photoinitiator. The solid film adhesive is capable of being processed at temperatures up to 120° C. prior to exposure to actinic radiation without curing, has a latency period at room temperature following activation of the initiator, and is curable at temperatures above 50° C. following activation of the initiator.

Abstract: A method of forming an adhesive bond between a first substrate and a second substrate includes applying a semi-crystalline polymeric adhesive composition to a bonding area of the first substrate, and, after applying, disposing the second substrate adjacent to and in contact with the composition to form a workpiece. After disposing, the method includes heating the workpiece to cure the composition and thereby form a crosslinked polymeric adhesive material. After heating, the method includes cooling the workpiece such that the material has a crystalline molecular structure. Concurrent to cooling, the method includes imposing a stress on the material to thereby orient the crystalline molecular structure in a desired direction, and, after imposing, dissipating the stress along the crystalline molecular structure in the desired direction to thereby form the adhesive bond between the first substrate and the second substrate.

Abstract: A handling layer and adhesive parts having the handling layer are formed according to the present invention along with used therefore.

Abstract: An elastomeric composition and method incorporating a hydrocarbon polymer modifier with improved permanence. The composition comprises elastomer, filler and silane-functionalized hydrocarbon polymer modifier (Si-HPM) adapted to couple the Si-HPM to the elastomer, filler or both, wherein the Si-HPM comprises an interpolymer of monomers chosen from piperylenes, cyclic pentadienes, aromatics, limonenes, pinenes, amylenes, and combinations thereof. The method comprises melt processing a mixture to form the elastomeric composition in the shape of an article, wherein the mixture comprises elastomer, Si-HPM, silica, bifunctional organosilane crosslinking agent; and curing the elastomeric composition to form the article. Also disclosed are a silylated hydrocarbon polymer modifier coupled with a bifunctional organosilane crosslinking agent, and a silica-coupled hydrocarbon polymer modifier coupled to the silica via the bifunctional organosilane crosslinking agent.

Abstract: The invention provides an aircraft lifting surface with a torsion box (13) of a composite material comprising an upper skin (21), a lower skin (23), a front spar (18), a rear spar (20), one or more intermediate spars (19, 19?) and a plurality of transverse ribs (25, 25?, . . . ) arranged between the rear spar (20) and its adjacent intermediate spar (19?) and/or between the front spar (18) and the adjacent intermediate spar (19) for improving its structural behavior. The invention also provides a manufacturing method of said torsion box.

Abstract: A bonding material is placed on an electronic component. a heat conductive member is superposed on the surface of the bonding material so that a thermosetting adhesive is interposed between the heat conductive member and a substrate. The thermosetting adhesive is then cured at a temperature lower than the melting point of the bonding material. The bonding material melts after the thermosetting adhesive has cured. While a distance is maintained between the heat conductive member and the substrate, the thermosetting adhesive is cured. The heat conductive member is thus reliably prevented from a downward movement regardless of the melting of the bonding material. A space is maintained between the heat conductive member and the electronic component. The cured bonding material is reliably prevented from suffering from a reduction in the thickness.