Abstract: A fitting method is for fitting a material to be repaired and a repair patch to be adhesively bonded to the material at adhesive surfaces, each adhesive surface having at least two or more of curved portions. The fitting method includes measuring a shape of the material; measuring a shape of the repair patch; dividing repair patch shape measurement data acquired at measuring the shape of repair patch into pieces of divided data each including one or less of the curved portions; performing, at the adhesive surfaces, fitting processing of the pieces of divided data acquired at dividing the repair patch shape measurement data to material-to-be-repaired shape measurement data acquired at measuring the shape of material; and calculating a gap amount between the material-to-be-repaired shape measurement data and repair patch shape fitting data acquired from the fitting processing at the adhesive surfaces.

Abstract: A method for repairing a crack in ships or other structures that includes adhesively applying fiber reinforced metal matrix composite tape across the crack of the structure to reduce propagation of the crack and provide additional structural stability until the crack can be permanently repaired.

Abstract: A toe link support is disclosed. In a first aspect, the toe link aperture of a hub has been bored out to receive inner and outer spacers. The spacers have bolt holes through which a toe link bolt is inserted to secure a toe link to the hub. The bolt is secured by a nut. The spacers protect the hub from damage by the bolt, and vice versa, resulting from motion of the toe link. In a second aspect, the outer spacer is further configured to be inserted into the bolt hole of the toe link, further protecting the bolt from damage. A method of supporting a toe link is also disclosed.

Abstract: A method, system, and computer program product for repairing cracks in structures by automatically transferring filler materials along a magnetic force pathway inside the structures. The method may include identifying a crack in a structure. The method may include analyzing dimensions and positions of the crack. The method may include identifying an array of magnetic coils near the crack, wherein the array of magnetic coils can create a magnetic path to the crack. The method may include determining an appropriate filler material reservoir connected with the structure based on the array of magnetic coils and the crack in the structure. The method may include transmitting instructions to release a quantity of the filler material mixture from the appropriate filler material reservoir connected with the structure for each of the one or more cracks.

Abstract: A method for repairing a target member including a ceramic matrix composite reinforced by ceramic fiber includes: a removal step of removing at least a part of a surface of the target member; an arrangement step of arranging a green body for repair which includes the ceramic fiber on a portion where the surface is removed in the removal step; an impregnation step of impregnating at least the portion of the target member where the green body for repair is disposed with slurry; and a sintering step of sintering the target member on which the green body for repair is disposed, after the impregnation step.

Abstract: A gap finishing tape for use with drywall applications includes a trim strip body extending along a central body axis, a hot melt adhesive extending along the central body axis, and a backing paper. The trim strip body includes a first surface, a second surface opposite the first surface, a first side, and a second side opposite the first side, and is at least partially constructed from a metallic material. The backing paper is at least partially secured to the second surface of the trim strip body. The trim strip body is at least partially embedded in the hot melt adhesive.

Abstract: Complex laminated composites may be repaired by removal of individual damaged plies through peeling in order to exploit the weaker interlaminar properties of these composites. Upon removal of the individual damaged plies through peeling, replacement plies may be added to restore the laminated composite. In addition, when damage extends through the thickness of a laminated composite, a plug may be used to allow plies to be replaced while maintaining contour within the repair region. A caul plate also may be used to stiffen and maintain the contour of a repair region while peeling and removing plies from the repair region.

Abstract: An interconnect for a fuel cell stack includes an interconnect body having an air surface having air flow channels and ribs and a fuel surface having fuel flow channels and ribs, an electrically conductive contact layer located on the air surface of the interconnect, the electrically conductive contact layer containing at least one of Co and Mn, and a corrosion barrier layer containing zirconium silicate and magnesium aluminosilicate crystals located over the electrically conductive contact layer.

Abstract: Provided is a method a method for reworking an article. The method includes forming a patch over an area of a composite structure requiring rework. The forming includes placing a first film-adhesive over the area of the composite structure requiring rework, wherein the first film-adhesive extends over a first surface area of the structure including beyond an entirety of the area requiring rework, placing a first pre-cured ply stack over the first film-adhesive, wherein the first pre-cured ply stack extends over a second surface area of the composite structure; placing a second film-adhesive over the first pre-cured ply stack, wherein the second film-adhesive extends over a third surface area of the composite structure; and placing a second pre-cured ply stack over the second film-adhesive, wherein the second pre-cured ply stack extends over a fourth surface area of the composite structure.

Abstract: A wall repair device comprising a thin, flexible disc having an inside portion surface area, an outside portion surface area and an outside perimeter located around the outside edge of the disc and a center portion located in the center of the disc, wherein the center portion is an attachment means; a wand removeably attachable to the center portion of the disc; and wherein the outside perimeter of the disc is collapsible towards and in the direction of the length of the wand when the wand is attached to the center portion of the disc. A method to repair a hole in a wall, wherein the wall is made of drywall plaster or plaster lathe, is also disclosed herein.

Abstract: A system. The system includes a liquid container and an energy absorbing system positioned. The liquid container includes a wall which defines an interior volume of the liquid container. The energy absorbing system is within an interior volume of the liquid container. The energy absorbing system is configured such that if an object passes through the wall of the liquid container and impacts the energy absorbing system, an amount of energy absorbed by the energy absorbing system is at least 18% greater than an amount of energy absorbed by the wall of the liquid container. The energy absorbing system includes one or more energy absorbing members, wherein at least one of the one or more energy absorbing members comprises a metal and has a Brinell hardness of at least 150.

Abstract: A method for producing a smooth aerodynamic surface of an aircraft component is depicted and described. The method includes: provision of an aircraft component with an aerodynamic surface, which has an uneven section, introduction of a liquid or viscous, uncured sealing compound into the uneven section, introduction of a solid, precured sealing body into the uneven section in such a way that the sealing body presses into the sealing compound until the sealing compound at least partially surrounds the sealing body, curing of the sealing compound.

Abstract: A repair apparatus for an electrically conductive layer of a composite structure includes a dielectric layer, having a perimeter, secured to the composite structure, a first adhesive layer, and a conductive layer, secured over the dielectric layer and to the composite structure via the first adhesive layer around an entirety of the perimeter of the dielectric layer, the first adhesive layer being scored along a perimeter region thereof to improve a conductive path between the conductive layer and the composite structure.

Abstract: A resin joined body includes a thermoplastic resin molded body and a thermosetting resin molded body. The thermosetting resin molded body has a thermoplastic resin portion embedded in the thermosetting resin molded body and exposed at a portion of a surface of the thermosetting resin molded body. The thermoplastic resin portion of the thermosetting resin molded body is welded to the thermoplastic resin molded body thereby joining the thermosetting resin molded body to the thermoplastic resin molded body.

Abstract: The present invention relates to a hybrid modified bitumen composition containing functionalized polymer, crumb rubber and a dual functional agent. The present invention also relates to a process of preparation of hybrid modified bitumen composition containing functionalized polymer, crumb rubber and a dual functional agent.

Abstract: A prepreg comprising a fibrous reinforcement layer at least partially impregnated with a matrix resin having a first viscosity, a coating of a wet resin having a second viscosity on a first side of the fibrous reinforcement layer, the first viscosity being higher than the second viscosity, both the matrix resin and the wet resin being curable by ultraviolet radiation, a first removable flexible film which acts as a barrier to ultraviolet radiation on a second side of the fibrous reinforcement layer, and optionally a second removable protective flexible film covering the coating of wet resin.

Abstract: A method for modifying a ceramic matrix component is disclosed including identifying a non-conforming region of a composite component capable of operating in a gas turbine engine; removing at least a portion of the non-conforming region to create an exposed surface of the composite component; preparing a preform in response to the removing at least a portion of the non-conforming region; applying a reactive constituent surface region to at least one of the exposed surface of the composite component and the preform, the reactive constituent surface region being capable of producing a non-equilibrium condition; positioning the preform to provide a contact region between the exposed surface of the composite component and the preform proximate the reactive constituent surface region; and reacting the reactive constituent surface region in an equilibrium reaction at the contact region to form a bond structure between the exposed surface of the composite component and the preform.

Abstract: A composite rework patch and method. The composite rework patch comprises a trapezoidal shape, a first region, and a second region. The trapezoidal has a first base and a second base, the first base parallel to the second base. The first region comprises a first composite material portion and a first adhesive portion. The second region comprises a second composite material portion and a second adhesive portion.

Abstract: An external adjustment device includes at least one permanent magnet configured for rotation about an axis with a first handle extending linearly at a first end of the device and a second handle at a second end of the device, the second handle extending in a direction substantially off axis to the first handle. The external adjustment device further includes a motor mounted inside the first handle and a first button located in the proximity to one of the first handle or the second handle, the first button configured to be operated by the thumb of a hand that grips the one of the first handle or second handle. The first button is configured to actuate the motor causing the at least one permanent magnet to rotate about the axis in a first direction.

Abstract: A repair method includes the steps of: (A) forming a repair cavity 14 by removing a honeycomb core 11 including a damaged portion with a front-side skin 12; (B) inserting, into the repair cavity 14, a repair honeycomb core 21 whose end surface 30 on a side to which a repair patch 22 is bonded is subjected to flattening treatment; (C) disposing the repair patch on the flattened end surface 30 of the repair honeycomb core 21 via a film-like adhesive 24; and (D) bonding the repair honeycomb core 21 to an existing portion of the honeycomb sandwich structural body 10 and to the repair patch 22, and curing the repair patch 22 under a reduced-pressure atmosphere associated with heating.

Abstract: A method for repairing an open shrinkage crack in a concrete slab employs expansive mortar. A saw cut is created next to the shrinkage crack, and then expansive mortar is applied into the open saw cut. The expansive mortar material gradually expands and urges the saw cut apart. This shifts the portion of the slab between the saw cut and the slab in the direction to close the shrinkage crack tightly. The expanded mortar material is removed from the saw cut and a rigid spacer is installed in the saw cut. An adhesive can be installed between the two sides of the crack. The surface of the repaired slab can be given cosmetic repairs, and let dry before applying a sealer.

Abstract: A septum includes two septum plates and the edges of the septum plates are brought into contact at one of the junction edges of the septum plates. In particular, an angle (?) between one of the junction edges of the septum plates and one of the sides of the septum plates adjacent to the one of the junction edge is less than 90°.

Abstract: A repair part enables rapid and efficient repair of damaged metal structures, in particular airframe fuselage skins having internal and external faces, without necessitating any additional thickness compromising the transmission of waves. To this end, the repair part includes a double internal/external plate adapted to be fastened to the internal face and the external face of the metal structure, respectively. The repair part also includes a central hub connecting the internal plate and the external plate and forming a groove between the plates. The part is constituted of a single composite material block, and a glass ply, lining the groove, may be positioned between the plates and the structure. The hub may have passing through it at least one orifice adapted to allow connections to pass through the structure.

Abstract: An article comprises a multi-directional textile of first reinforcing fiber tows extending in a first direction and second reinforcing fiber tows extending in a second direction. Filaments in the first fiber tows extend past a boundary of the textile and are spread. The tows are embedded in resin.

Abstract: Sulfur-containing polyurea compositions comprising a polyisocyanate and a polyamine are disclosed. The polyisocyanate comprises the reaction product of reactants comprising a diisocyanate having isocyanate groups with different reactivities toward thiol groups, and a thiol-terminated sulfur-containing polymer such as a thiol-terminated polythioether polymer and/or a thiol-terminated polyformal polymer. The polyamine can be an aromatic polyamine and/or an aromatic amine-terminated polythioether adduct. The sulfur-containing polyurea compositions are useful as aerospace sealants.

Abstract: A seal assembly (10) is provided for sealing a core hole (52) formed in a concrete slab (54) having opposite first and second surfaces, with the core hole (52) extending between the first and second surfaces. The seal assembly (10) comprises a cover assembly (12) having a cover plate (14) that is configured for engaging the first surface of the concrete slab (54) and seating over and covering the core hole (52). The cover assembly (12) has a lower plate (16) that is configured for being received within the core hole (52). The lower plate (16) is coupled to the cover plate (14) through a support member (20) so that the lower plate (16) is spaced apart from the cover plate (14) when the cover plate (14) is seated over the core hole (52) to define a cavity between the lower plate (16) and the cover plate (14). A locking element carrier (26) is coupled to the cover assembly (12).

Abstract: A beaded composite panel is fabricated using composite plies. An opening is formed in each of plies, and each ply is laid up on a bead feature and drawn down over the bead feature in the area of the opening so as to widen the opening into a gap allowing the ply to conform to the contour of the bead feature. Patches are fabricated and placed on the plies overlying over the openings. The laid-up plies are compacted and cured.

Abstract: A repair method includes the steps of: (A) forming a repair cavity 14 by removing a honeycomb core 11 including a damaged portion with a front-side skin 12; (B) inserting, into the repair cavity 14, a repair honeycomb core 21 whose end surface 30 on a side to which a repair patch 22 is bonded is subjected to flattening treatment; (C) disposing the repair patch on the flattened end surface 30 of the repair honeycomb core 21 via a film-like adhesive 24; and (D) bonding the repair honeycomb core 21 to an existing portion of the honeycomb sandwich structural body 10 and to the repair patch 22, and curing the repair patch 22 under a reduced-pressure atmosphere associated with heating.

Abstract: The present invention sufficiently heats a repairing material while preventing change in quality of a base material provided with the repairing material so as to securely bond the repairing material to a repair target portion. The repair method of the present invention, in order to repair a repair target portion 14 existing in an outer panel 1, includes: a repairing material disposing step of disposing a repairing patch 21 including a resistance heating element 23 and a carbon fiber reinforced resin, and an adhesive 22A including a thermosetting resin before being hardened for bonding the repairing patch 21 on the repair target portion 14; and a heating-hardening step of heating and hardening the thermosetting resin of the adhesive 22A by causing the resistance heating element 23 to generate heat through supply of electricity thereto.

Abstract: The present invention relates to a repair method using a pre-cured repairing patch, and a repaired product obtained from repairing using the repairing patch, and the present invention securely bonds a repairing patch, where an out-of-plane stiffness is required, to a repair target. In order to cover a repair target portion 23 formed in an outer panel 2 with a repairing patch 30, and bond the repairing patch 30 to a repair target, repairing plates 31, 32 that are formed of fibers and thermosetting resin, and pre-cured before repairing are used as the repairing patch 30, and a laminating step S4 of laminating the repairing plates 31, 32, and a bonding step S7 of bonding the repairing plates 31, 32 to each other are performed.

Abstract: A method for repairing a honeycomb core sandwich structural body according to the present invention is a method in which a damaged portion that is formed in a honeycomb core sandwich structural body where a honeycomb structured core is held between a first outer skin and a second outer skin and that reaches the core through the first outer skin is repaired, the method including: a repair material mounting step of mounting a repair material on the damaged portion, the repair material including a patch that covers an opening of the damaged portion, and one or a plurality of braces that support the patch; a patch bonding step of bonding the patch to the first outer skin; and a brace bonding step of bonding the brace to the second outer skin or the core.

Abstract: A method for modifying a ceramic matrix component is disclosed including identifying a non-conforming region of a composite component capable of operating in a gas turbine engine; removing at least a portion of the non-conforming region to create an exposed surface of the composite component; preparing a preform in response to the removing at least a portion of the non-conforming region; applying a reactive constituent surface region to at least one of the exposed surface of the composite component and the preform, the reactive constituent surface region being capable of producing a non-equilibrium condition; positioning the preform to provide a contact region between the exposed surface of the composite component and the preform proximate the reactive constituent surface region; and reacting the reactive constituent surface region in an equilibrium reaction at the contact region to form a bond structure between the exposed surface of the composite component and the preform.

Abstract: A restructured, recycled or repurposed slab such as stone, wood or the like which includes a primary component and a secondary component which fills a fissure, crack or break in the slab. The secondary component being configured to restore the structural integrity and/or providing a continuous surface. The secondary component configured to provide a noticeable contrast in appearance to the primary component.

Abstract: In some examples, a method includes identifying a damaged area in a ceramic matrix composite coating of an in-service component; applying a restoration slurry to the damaged area of the ceramic matrix composite coating, wherein the restoration slurry comprises a liquid carrier and a restoration coating material; drying the restoration slurry to form a dried restoration slurry; and heat treating the dried restoration slurry to form a restored portion of the ceramic matrix composite coating. In some examples, an assembly may include a component including a substrate and a coating on the substrate, where the coating defines a damaged portion; masking around the damaged portion on undamaged portions of the coating; and a restoration slurry in the damaged portion, wherein the restoration slurry comprises a liquid carrier and a restoration coating material.

Abstract: A patch for reworking an inconsistent area in a composite structure includes a composite laminate patch and a layer of adhesive for bonding the laminate patch to the composite structure. The laminate patch has at least first and second regions for releasing strain energy around the inconsistent area respectively at different rates.

Abstract: A method for repairing cracked concrete (8) using expansive mortar (13) comprising the steps of installing a saw cut (10) next to an open shrinkage crack (8) and opening the saw cut (10) with expansive mortar (13) to create a wider saw cut (11) and shift half the saw cut (10) toward the open shrinkage crack (8) to close the shrinkage crack (12) tightly. Install a rigid spacer (16) to maintain the width of the control joint. Install adhesive (18) from the top of finished concrete slab (9) into the closed shrinkage crack (12). The surface of the finished concrete slab (9) will receive cosmetic repair (7) to the closed shrinkage crack (12) and let dry before applying sealer. Other embodiments are described as shown.

Abstract: A device and method to repair a structural component. The device includes a plug that bonds to the structural component. The plug includes a flange and a solid shank extending from the flange, the solid shank being disposable in an opening of the structural component. The device further includes disc that bonds to the structural component such that, when bonded, the disc covers the solid shank of the plug. The method includes bonding the plug to the structural component such that the solid shank of the plug is disposed in the opening of the structural component. The method further includes bonding the disc to the structural component.

Abstract: A patch for reworking an inconsistent area in a composite structure includes a composite laminate patch adapted to cover the inconsistent area and bonded to the structure by a layer of adhesive. The patch includes a plurality of composite plies having a tapered cross section, and at least first and second regions respectively having differing fracture toughnesses.

Abstract: A method for reworking an electrically conductive layer of a composite skin is disclosed in which a patch replaces the altered section of the electrically conductive layer. The method is performed by removing a portion of the electrically conductive layer to reveal the underlying composite skin. A patch is formed, having an electrically conductive section coupled to an adhesive having a low dielectric breakdown strength, and is then introduced over the underlying composite skin such that the adhesive layer covers the underlying composite skin and overlaps an unremoved portion of the electrically conductive layer. The patch is applied such that the electrically conductive section within the patch covers the adhesive layer and overlaps the unremoved section of the electrically conductive layer. The adhesive layer preferably has a low dielectric breakdown strength, so that electricity from lightning which strikes the composite skin may be conducted through the adhesive.

Abstract: A method for strengthening glass substrate includes: preheating a glass substrate; spraying a molted salt onto the substrate to form a ion exchange layer; forming a titanium dioxide layer on the ion exchange layer. The ion exchange layer infills some microcracks. The titanium dioxide layer reinforces the infilling of microcracks and applying further toughness. An article manufactured by the method is also provided.

Abstract: A method of repairing a composite material is provided in which a frustum-shaped portion of a composite material is removed, and the composite material and a repair material are bonded with each other while evacuating. The repair method includes step S2 of removing a damaged part 11 from the front side so as to pass through in the thickness direction while leaving a support wall protruding inward in the radial direction from the periphery of the top face of the frustum-shaped portion; step S3 of sealing the back side by placing a sealing plate, which is inserted from the front side into a through hole formed by the removing step, on the support wall; step S5 of placing the repair material through an adhesive on the composite material where the frustum-shaped portion has been removed; and step S6 of evacuating in a state in which the front side is sealed.

Abstract: One possible embodiment of the invention could be a methodology of preventing an existing crack or break in the vehicle windshield from becoming larger comprising of the steps, providing a laminate with a UV light-permeable barrier film having least one side to which UV light curable adhesive is applied to it, a peel-able cover reversibly applied over the adhesive; providing a windshield with at least a small crack or chip in its surface; removing the peel-able cover from the adhesive; applying the barrier film to the windshield in a manner to cover the crack or chip so that the adhesive comes in contact with the windshield; and transmitting UV light through the film to the adhesive to cure it into a rigid substrate connection between the barrier film and the windshield that resists various forces acting upon the windshield that would otherwise increase the size of crack or chip.

Abstract: A personal card carrier is configurable into open and closed positions, in which both broad faces of a contained card are effectively covered and protected against loss in the closed position, but are uncovered in the open position such that a data-embedded portion of the card is presentable to a card reader without necessitating removal of the card from the carrier.

Abstract: The invention relates to a device for producing, repairing and/or replacing a component, particularly an aircraft component, by means of a powder that can be solidified by energy radiation of an energy radiation source, characterized in that the device comprises an application unit that is designed such that the powder can be applied onto an uneven surface by means of the application unit.

Abstract: A seal assembly (10) is provided for sealing a core hole (52) formed in a concrete slab (54) having opposite first and second surfaces, with the core hole (52) extending between the first and second surfaces. The seal assembly (10) comprises a cover assembly (12) having a cover plate (14) that is configured for engaging the first surface of the concrete slab (54) and seating over and covering the core hole (52). The cover assembly (12) has a lower plate (16) that is configured for being received within the core hole (52). The lower plate (16) is coupled to the cover plate (14) through a support member (20) so that the lower plate (16) is spaced apart from the cover plate (14) when the cover plate (14) is seated over the core hole (52) to define a cavity between the lower plate (16) and the cover plate (14). A locking element carrier (26) is coupled to the cover assembly (12).

Abstract: The disclosure provides, in part, adhesive patches for repairing damaged surfaces of health care devices. In one of its aspects the disclosure provides a method of repairing the surface of health care device by applying an adhesive patch over a damaged portion of the surface, the patch comprising a film layer and an adhesive layer. In another one of its aspects, the disclosure provides an adhesive patch for repairing the surface of a health care device comprising a film layer and an adhesive layer.

Abstract: A turbine repair process, a repaired coating, and a repaired turbine component are disclosed. The turbine repair process includes providing a turbine component having a higher-pressure region and a lower-pressure region, introducing particles into the higher-pressure region, and at least partially repairing an opening between the higher-pressure region and the lower-pressure region with at least one of the particles to form a repaired turbine component. The repaired coating includes a silicon material, a ceramic matrix composite material, and a repaired region having the silicon material deposited on and surrounded by the ceramic matrix composite material. The repaired turbine component a ceramic matrix composite layer and a repaired region having silicon material deposited on and surrounded by the ceramic matrix composite material.

Abstract: Technologies described herein are generally related to repairing graphene on a porous support. In some examples, a method is described that may include receiving a graphene layer on a support. The graphene layer may include a hole and a pore. The method may further include applying a first reactive material to a first side of the graphene layer. The first reactive material may include molecules larger than the pore. A second reactive material may be applied through the support to a second side of the graphene layer. The second reactive material may include molecules larger than the pore. The first and second reactive materials may react in the hole to produce a plug in the hole and to repair the graphene layer.

Abstract: According to a first aspect of the present invention, a process for production of a water-absorbing article including a substrate and a coating film formed on the substrate and formed of a water-absorbing urethane resin is characterized in that: the process comprises an application step of applying a coating liquid to the substrate; the application step includes a step of supplying the coating liquid from a nozzle disposed above the substrate to a surface of the substrate conveyed horizontally; the coating liquid includes a solid matter and a solvent; the solid matter includes a mixture of a polyisocyanate, a polyol having ethylene oxide and a hydrophobic polyol; a concentration of the solid matter in the coating liquid is adjusted within a range from 5 to 30% in mass; and a viscosity of the coating liquid is adjusted within a range from 1 to 3 mPa·s.

Abstract: A repair patch for reworking an inconsistent area of a composite structure includes a patch body adapted to cover the inconsistent area and having a first patch region, a second patch region outside the first patch region and a first separation zone between the first patch region and the second patch region, with the first patch region, the first separation zone and the second patch region having increasing interlaminar fracture toughness from a center to an edge of the patch body; and a layer of adhesive for bonding the patch body to the composite structure.