Method for repairing a wall consisting of a plurality of layers

The invention relates to a method for repairing a wall ( 1 ), including a plurality of layers ( 2 ), each layer including fibers ( 3 ) extending in a main direction ( 4 ), and having a damaged area ( 5 ) over a plurality layers ( 2 ). The repair method includes a material removal step comprising making a recessed area ( 6 ) encircling the damaged area ( 5 ) and comprising a peripheral area ( 7 ) including steps ( 8 ) and adapted such that each step defines an interface area ( 9 ) having a width ( 10 ), the dimension of which in the main direction of the fibers of the lower layer adjoining the interface area ( 9 ) is greater than the dimension of said width in directions other than the main direction ( 4 ), a step of producing a replacement part ( 12 ) suitable for obstructing the recessed area, and a step of assembling the replacement part ( 12 ) onto the wall.

Repair part and repair method for repairing longitudinal elements made of a composite material

The present invention relates to a repair part and to a repair method. The repair part is an elongated part made of a composite material comprising two attached portions forming an angle and holes in each portion arranged in the direction of the line joining both portions. The repair method includes: providing a fragment of a repair part, being long enough to cover the damaged area of the part to be repaired, maintaining a border for fixing the fragment of the repair part; making holes in both portions of the part to be repaired, such that the distance between the centers of consecutive repair holes is the same as the distance between the centers of the consecutive holes; and attaching the fragment of the repair part to the part to be repaired.

Grinding device for scarf sanding

A grinding device for grinding a workpiece comprises: a main frame that rotates about a rotary shaft and is able to move in parallel on a horizontal plane vertically intersecting an axial direction; a first swingable frame that is disposed so as to be spaced from the main frame in the axial direction and is swingably mounted to the main frame; a pitch feed frame that is mounted to the first. swingable frame so as to be able to move in parallel on a horizontal plane intersecting the axial direction; and a second swingable frame that is swingably mounted to the pitch feed frame.

Method for Exchanging a Section of a Plastic Component

A method is provided for exchanging a section, in particular a damaged section, of a plastic component. The method includes: separating the section from the plastic component; providing at least one connecting element made from a plastic; pressing the at least one connecting element onto the plastic component such that the one connecting element abuts a remaining part of the plastic component; oscillating the connecting element by an ultrasonic sonotrode; and welding the connecting element to the remaining part of the plastic component; providing a replacement section for the separated section, wherein the replacement section has a hole, in particular a through-hole; applying the replacement section in the region from which the separated section was separated, such that the replacement section is clamped by its hole directly in a form-fitting and/or force-fitting manner onto the connecting element and/or the connecting element extends at least some way through the through-hole, wherein a clip element is clipped onto a section of the connecting element extending through the hole. The clip element projects beyond the through-hole and connects the replacement part to the remaining part of the plastic component in a form-fitting and/or force-fitting manner. 1. A method for exchanging a section of a plastic component , the method comprising the acts of:separating a section from the plastic component;providing at least one connection element made from a plastic;pressing the at least one connection element against the plastic component such that the connection element comes to bear against a remaining part of the plastic component;causing the connection element to vibrate via an ultrasonic sonotrode so as to weld the connection element to the remaining part of the plastic component;providing a replacing section that replaces the section separated from the plastic component, the replacing section having a hole; (i) clamping the replacing section directly onto the connection ...

METHOD FOR REPAIRING CERAMIC MATRIX COMPOSITE AND CERAMIC MATRIX COMPOSITE MEMBER

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. 1. A method for repairing a target member including a ceramic matrix composite reinforced by ceramic fiber , the method comprising: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; anda sintering step of sintering the target member on which the green body for repair is disposed, after the impregnation step.2. The method for repairing a ceramic matrix composite according to claim 1 , further comprising:a hole-forming step of forming at least one hole on the portion where the surface is removed, after the removal step.3. The method for repairing a ceramic matrix composite according to claim 2 ,wherein the portion where the surface is removed in the removal step includes a first region where a density of the ceramic fiber is relatively high and a second region where the density of the ceramic fiber is lower than that in the first region, andwherein the hole-forming step includes forming the at least one hole in the second region.4. The method for repairing a ceramic matrix composite according to claim 3 ,wherein the ceramic fiber includes a layer including a ...

POWERED TIRE REPAIR TOOL

A tire repair tool includes a housing, an electric motor disposed within a motor housing portion, a battery receiving portion configured to receive a battery pack to power the electric motor, an actuator configured to selectively activate the electric motor, and a chuck rotatably driven by the motor and configured to receive one of a plurality of different tire repair accessories. The tire repair tool further includes a multi-speed gearbox disposed within the motor housing portion having a plurality of different gear ratios, a mode selector operative to adjust the multi-speed gearbox between the plurality of different gear ratios, and an electronic speed control system configured to operate the electric motor at less than its capable maximum operating speed when the gearbox is operated in each of the plurality of different gear ratios to further reduce a rotational speed of the chuck. 1. A tire repair tool comprising:a housing including a motor housing portion and a handle portion extending from the motor housing portion;an electric motor disposed within the motor housing portion;a battery receiving portion configured to receive a battery pack to power the electric motor;an actuator located on an outer surface of the housing configured to selectively activate the electric motor;a chuck rotatably driven by the motor and configured to selectively receive one of a plurality of different tire repair accessories;a multi-speed gearbox disposed within the motor housing portion having a plurality of different gear ratios corresponding to the plurality of tire repair accessories;a mode selector disposed on an outer surface of the motor housing portion operative to adjust the multi-speed gearbox between the plurality of different gear ratios; andan electronic speed control system configured to operate the electric motor at less than its capable maximum operating speed when the gearbox is operated in each of the plurality of different gear ratios to further reduce a rotational ...

REPAIR OF ORGANIC MATRIX COMPOSITE PARTS

A process for repairing a part made of organic matrix composite material coated with at least one layer of paint includes removing the paint at a damaged area of the part, removing the composite material at the damaged area so as to form a recessed portion, depositing a repair resin in the recessed portion, curing the repair resin, applying at least one layer of paint to the repair area. The repair resin is loaded with magnetically detectable particles. 1. A process for repairing a part made of organic matrix composite material coated with at least one layer of paint comprising the following steps:a) removing the at least one layer of paint at a damaged area of the part,b) removing the organic matrix composite material at the damaged area so as to form a recessed portion,c) depositing a repair resin in the recessed portiond) curing the repair resin,e) applying at least one layer of paint to the repair area, wherein the repair resin is loaded with magnetically detectable particles.2. The process as claimed in claim 1 , further comprising claim 1 , prior to steps a) through e) claim 1 , a step of checking for an absence of a repair resin at a determined distance from the damaged area.3. The process as claimed in claim 1 , wherein the magnetically detectable particles are ferromagnetic material particles.4. The process as claimed in claim 3 , wherein the repair resin contains between 10% and 50% by weight of ferromagnetic material particles.5. The process as claimed in claim 1 , wherein the magnetically detectable particles are paramagnetic or superparamagnetic material particles.6. The process as claimed in claim 5 , wherein the repair resin contains between 1% and 10% by weight of paramagnetic or superparamagnetic material particles.7. A part made of organic matrix composite material coated with at least one layer of paint claim 5 , the part having at least one repair portion present in the organic matrix composite material claim 5 , said portion comprising a ...

Method of Repairing, Splicing, Joining, Machining, and Stabilizing Honeycomb Core Using Pourable Structural Foam and a Structure Incorporating the Same

A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.

Tool and method for repairing tubular members

A rotatable tool for use in repairing composite hollow shafts, namely for sports equipment, for example, composite hockey stick shafts. The rotatable tool includes a plurality of aligned spaced-apart grinding surfaces and proximal and distal guide bearings coaxially arranged along a tool shaft. The rotatable tool is used to form grooves proximate the repair location so as to enhance mechanical bonding of a composite repair material which spans a region of abutment of hollow shaft segments.

Verfahren und Vorrichtung zum Reparieren eines aus einem Schichtverbundwerkstoff in mehreren Schichten aufgebauten Bauteils

A method for repairing a component constructed in multiple layers from a layer composite material comprises a step of removing material of the layer composite material of the component in the region of damage to the component in order to form a scarfed cutout, such that a scarfed peripheral contour formed from a plurality of layers of the component is formed. Furthermore, fiber-reinforced plastic strips, which exhibit a curable plastic material in an uncured state, are applied in layers in the cutout in order to create a replacement-structure semifinished product that is complementary to and butts against the scarfed peripheral contour of the component. In a further step, the curable plastic material contained in the fiber-reinforced plastic strips is cured in order to create a replacement structure and for joining the replacement structure to the component. 115-. (canceled)16. A method for repairing a component constructed in multiple layers from a layer composite material , which comprises the steps of:removing material of the layer composite material of the component in a region of damage to the component to form a scarfed cutout, such that a scarfed peripheral contour is formed from a plurality of layers of the component;applying fiber-reinforced plastic strips, which exhibit a curable plastic material in an uncured state, in layers in the scarfed cutout to create a replacement-structure semifinished product that is complementary to and butts against the scarfed peripheral contour of the component; andcuring the curable plastic material contained in the fiber-reinforced plastic strips to create a replacement structure and to join the replacement structure to the component.17. The method according to claim 16 , wherein the replacement structure corresponds in shape substantially to an original claim 16 , defect-free form of the component in the region of the scarfed cutout.18. The method according to claim 16 , wherein the step of removing material of the layer ...

Method of repairing composite material and composite material

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 S 2 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 S 3 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 S 5 of placing the repair material through an adhesive on the composite material where the frustum-shaped portion has been removed; and step S 6 of evacuating in a state in which the front side is sealed.

Processes for Repairing Complex Laminated Composites

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. 1. A method for repairing a laminated composite , the method comprising:locating and defining a repair region of the laminated composite, the laminated composite having a plurality of ply layers;creating a repair patch;peeling and removing one or more of the plurality of ply layers having damage from the repair region; andaligning and bonding the repair patch to the one or more of the plurality of ply layers remaining in the repair region.2. The method of further comprising:mapping dimensions and arrangement of the plurality of ply layers forming the laminated composite.3. The method of claim 2 , the step of creating the repair patch further comprising:forming a first layer that matches the mapped dimensions and arrangement of the plurality of ply layers forming the laminated composite;forming at least one additional layer that matches the mapped dimensions and arrangement of the plurality of ply layers forming the laminated composite; andaligning the first layer with the at least one additional layer.4. The method of claim 2 , wherein the number of layers forming the repair patch is at least equal to the number of ply layers having damage that are separately peeled and removed.5. The method of claim 1 , wherein each of the one or more of the plurality of ply layers having damage is separately peeled and removed.6. The method of claim 1 , wherein ...

REPAIR OR RESUMPTION OF MANUFACTURE OF A COMPOSITE MATERIAL PART WITH FIBROUS THREE-DIMENSIONAL WOVEN REINFORCEMENT

A method for repairing a part made of composite material includes producing a recessed section by removing the composite material at a damaged area, producing grooves extending on the two faces of the part from edges of the recessed section, producing orifices in the part opening out into the grooves, tree-dimensional weaving of a filling part fiber preforms including a central section having a shape corresponding to the shape of the recessed section and fiber bundles extending from the central section, placing the filling preforms respectively on either face of the part with the fiber bundles in the grooves on the faces of the part and in the orifices such that the fiber bundles open out into the grooves present on the opposite face of the part, impregnating the filling fiber preforms with a precursor resin of a matrix, transforming the resin into a matrix to obtain a filling part.

Systems and Methods for Actualizing Simulated Scarfs and Patches for Repair of Composite Laminates

Systems and methods for actualizing simulated scarfing and patching for repair of composite laminates. A virtual environment is provided that enables engineers to optimize a repair design and provide the most robust repair solution that meets structural requirements, while minimizing the material removal and the impact to the composite structure. An optimization algorithm is configured to adjust contour offsets for pad-up plies and adjust scarf taper ratios in any direction to reduce the amount of material removed or avoid underlying structures. Scarf repair designs are subsequently transmitted to repair technicians for manual scarfing via printed templates or automated/robotic scarfing using converted computer-readable code. The technology also provides digital data for automated repair ply cutting.

System for out of autoclave bonded repairs

A system for out of autoclave bonded repairs which including a fixing structure ( 1 ) to the composite area to be repaired, including a frame ( 4 ) and fixing parts ( 5, 19 ) attached to the frame ( 4 ), a movable structure ( 2 ) able to be attached either to the fixing structure ( 1 ) or to the patch manufacturing table ( 3 ), which includes three shafts ( 6, 6′, 6″ ) and three engines ( 7, 7′, 7″ ) configured to be able to move the tooling support in the three axes X, Y and Z, and a tooling support of either scanning tool ( 9 ), milling tool ( 10 ), patch cutting tool ( 11 ) or composite patch handle tool ( 11 ), and a patch manufacturing structure ( 3 ).

GUIDE DEVICE AND SCARFED SURFACE FORMING METHOD

Provided is a router guide that comprises: a guide part that has a first through-hole and a guide surface that guides a cutting tool attachment part of a router device along the first through-hole; a maintaining part that maintains the position of the guide surface; and a positioning part that positions the guide part. The guide surface is formed such that, in a state where the maintaining part is in contact with a surface of a composite material, the distance from the surface becomes smaller as the guide surface approaches a second through-hole. The guide part is formed so as to be elastically deformable. In a case where the guide part is caused to elastically deform along the surface shape of the composite material, the maintaining part maintains the position of the guide surface with respect to the surface at a position that corresponds to the surface shape. 1. A guide device which guides a router device , which rotates a cutting tool having an outer peripheral surface on which a cutting portion is formed and cuts a workpiece coming into contact with the cutting portion , in accordance with a surface shape of the workpiece having a curvature in at least a predetermined direction , comprising:a guide portion which includes a first through-hole into which the cutting tool can be inserted, and a guide surface which guides an attachment portion of the router device to which the cutting tool is attached in a state where the cutting tool is inserted into the first through-hole along the first through-hole;a holding portion which comes into contact with a surface of the workpiece and holds a position of the guide surface with respect to the surface of the workpiece; anda positioning portion which includes a second through-hole into which a positioning pin positioned in a positioning hole formed in the workpiece is inserted and positions the guide portion at a predetermined position in a radial direction intersecting an axis in which the positioning pin extends in a ...

CERAMIC MATRIX COMPOSITE MEMBER

A ceramic matrix composite member including a ceramic matrix composite reinforced by ceramic fiber, includes a body portion and a joint portion joined integrally to the body portion, the joint portion occupying a part of a surface of the ceramic matrix composite member, wherein the body portion includes at least one hole extending toward an inside of the body portion from a boundary surface between the body portion and the joint portion, and the at least one hole is filled with a matrix of the ceramic matrix composite, wherein the body portion includes a first region where a density of the ceramic fiber is relatively high and a second region where the density of the ceramic fiber is lower than that in the first region, and wherein the at least one hole exists so as to cut off a part of bundles of the ceramic fiber in the second region. 1. A ceramic matrix composite member comprising a ceramic matrix composite reinforced by ceramic fiber , comprising:a body portion; anda joint portion joined integrally to the body portion, the joint portion occupying a part of a surface of the ceramic matrix composite member,wherein the body portion includes at least one hole extending toward an inside of the body portion from a boundary surface between the body portion and the joint portion, and the at least one hole is filled with a matrix of the ceramic matrix composite,wherein the body portion includes a first region where a density of the ceramic fiber is relatively high and a second region where the density of the ceramic fiber is lower than that in the first region, andwherein the at least one hole exists so as to cut off a part of bundles of the ceramic fiber in the second region.2. The ceramic matrix composite member according to claim 1 ,wherein the ceramic fiber includes a layer including a first bundle of the ceramic fiber extending in a first direction, a second bundle of the ceramic fiber extending in the first direction adjacent to the first bundle, a third bundle of ...

Nozzle assembly for repairing or upgrading wind blades, method thereof and kit for the same

This invention relates generally to a nozzle, method thereof and a kit set for the same for spreading material on curved surface, in the field of repairing services for wind turbine blades and other similar composite components. More particularly, the present invention relates to a nozzle for spreading material on a leading edge of a wind turbine blade for guiding the material along the surface, generally, for repairing or upgrading. In addition it relates to a method and a kit for performing the application.

Cutting apparatus and method for cutting belts

A cutting apparatus for forming fingers in an end of a belt is provided and includes a blade for cutting the belt and a table for positioning the belt below the blade. The cutting apparatus includes an actuator that is connected to the blade via a primary shaft. The actuator is also connected to the table via both a secondary shaft and a cam assembly. Rotation of the actuator causes the primary shaft to continuously reciprocate the blade in upward and downward directions. Rotation of the actuator also causes intermittent movement of the table that includes both translation of the table to index the belt relative to the blade, and pivoting of the table to change an angle of the belt relative to the blade.

METHOD OF RESTORING THE TRANSPARENCY OF PLASTIC LENSES

A method for inexpensively cleaning plastic headlight lenses of a vehicle, whereby transparency is restored along with driver safety and visibility is provided. The method may remove oxidation and other indicia of opacity from the lens by a sequence of varying wet sanding applications. Following the wet sanding, the method may include the application of polish and sealant so as to obtain a high gloss finish. 1. A method of increasing the transparency of plastic lens by removing the indicia of opacity , comprising:applying water to the plastic lens;providing a second stage coated abrasive;wet sanding the second stage coated abrasive to the water-applied plastic lens until oxidation defects and scratches amounting to indicia of opacity are removed;reapplying the water to the plastic lens;providing a third stage coated abrasive; andwet sanding the third stage coated abrasive to the water-reapplied plastic lens until oxidation defects, scratches and roughness amounting to indicia of opacity are removed.2. The method of claim 1 , wherein the wet sanding is performed with a horizontal motion across the plastic lens.3. The method of claim 1 , wherein the second stage coated abrasive comprises a grit size ranging from approximately 800 to 1500.4. The method of claim 1 , wherein the third stage coated abrasive comprises a grit size ranging from approximately 1500 to 3500.5. The method of claim 1 , further comprising providing a first stage coated and wet sanding the first stage coated abrasive to the water-applied plastic lens until oxidation defects amounting to indicia of opacity are removed.6. The method of claim 1 , wherein the first stage coated abrasive comprises a grit size ranging from approximately 220 to 800.7. The method of claim 6 , further providing an initial inspection of the plastic lens to determine if the first stage coated abrasive is necessary.8. The method of claim 1 , further providing a polish and a sealant.9. The method of claim 8 , wherein the polish ...

Method and Apparatus for Reworking Inconsistencies on Parts

A method and apparatus for reworking an inconsistency on a part. Information about the inconsistency on the part may be identified using data generated by a nondestructive evaluation system. A portion of a section of the part in which the inconsistency is located may be removed based on the information about the inconsistency. A profile for the section of the part may be identified. Rework image data may be generated using the profile in which the rework image data comprises a number of patch images. The number of patch images may be projected onto a rework material as a number of patch projections for use in forming a patch to be applied over the section of the part. 1. A method for reworking an inconsistency on a part , the method comprising:identifying information about the inconsistency on the part using data generated by a nondestructive evaluation system;removing a portion of a section of the part in which the inconsistency is located based on the information about the inconsistency;identifying a profile for the section of the part;generating rework image data using the profile in which the rework image data comprises a number of patch images; andprojecting the number of patch images onto a rework material as a number of patch projections for use in forming a patch to be applied over the section of the part.2. The method of further comprising:forming a number of patch layers from the rework material using the number of patch projections of the number of patch images on the rework material.3. The method of claim 2 , wherein the step of forming the number of patch layers from the rework material using the number of patch projections of the number of patch images on the rework material comprises:cutting the number of patch layers out of the rework material using the number of patch projections of the number of patch images on the rework material.4. The method of further comprising:applying the number of patch layers over the section of the part having the portion ...

TRANSPARENCY REPAIR SYSTEM

The present invention provides a composition as well as a method for repairing deep scratches, gouges, etc. and which is particularly useful for aircraft and aerospace transparency repair. The composition is a polishable two-part, solvent-free, composition polyurethane coating for repairing the transparencies and which, after application, cures to a thermoset polyurethane. 1. A transparency repair composition comprising: a two-part system of:(a) a hydroxy-terminated polyol, a light stabilizer and a catalyst defining Part A;(b) an aliphatic polyisocyanate defining Part B; andWherein, when cured, provides a thermoset polyurethane.2. The repair composition of claim 1 , wherein Part A further includes a chain extender comprising a short chain diol.3. The composition of claim 1 , wherein the hydroxy-terminated polyol is either a polyether or polyester polyol having at least two primary hydroxy groups and mixtures thereof.4. The composition of claim 2 , wherein the hydroxy-terminated polyol is a polyester triol terminated by primary hydroxyl groups.5. The composition of claim 4 , wherein the hydroxy-terminated polyol is an aliphatic polyester primary hydroxy-terminated triol.6. The composition of claim 5 , wherein the light stabilizer is a liquid hindered amine light stabilizer.7. The composition of claim 1 , wherein the catalyst is a tin-based catalyst.8. The composition of claim 1 , wherein the diisocyanate is an aliphatic diisocyanate.9. The composition of claim 1 , wherein the first part and second parts are present in respect to weight ratio to about 1:1 to about 1:3.10. A method for preparing an aerospace or aircraft transparency repair kit comprising blending together at ambient conditions with stirring for a period of time ranging about twenty seconds to about thirty seconds claim 1 , the two-part repair kit being the components of .11. A method for repairing an aerospace or aircraft transparency comprising:{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, '(a) ...

Transparency repair system

The present invention provides a composition as well as a method for repairing deep scratches, gouges, etc. and which is particularly useful for aircraft and aerospace transparency repair. The composition is a blend of a polishable two-part, solvent-free, polyurethane coating composition for repairing the transparencies and which, after application, cures to a thermoset polyurethane. An optical grid is emplaced over the area to be repaired prior to applying the blend.

Apparatus and Method for Surface Rehabilitation

A lens refinishing process includes preparing the surface of the lens, determining whether to coat the lens with a polymer coating or polish the lens, either applying a polymer coating to the lens or polishing the lens, and then applying a protective coating. The preparation step includes applying a removal compound to the lens to remove an anti-reflective coating and to create nano-scratches, applying a coupling agent to the exposed substrate, and heating the coupling agent. The polishing step includes iteratively polishing the substrate using different combinations of polishing compound with different grit values together with different types of polishing pads.

PROFILED PLANE ABRADING TOOL FOR TIRE REPAIRS

The present invention includes methods and apparatus for controlling the abrasion of a tire surface. Particular embodiments provide an abrading tool for abrading a surface of a tire, the tool comprising means for rotating an abrading wheel, an abrading wheel rotatably attached to the means for rotating, and a depth guide secured to the means for rotating, wherein the depth guide includes a pair of freely rotatable, spaced apart guide wheels. Further embodiments include a depth guide configured for use with an abrading tool which includes a abrading wheel and a means for rotating the abrading wheel, the depth guide comprising a mounting member securable to the means for rotating and a pair of freely rotatable, spaced apart guide wheels rotatably attached to the mounting member. Particular embodiments further include a method for preparing a portion of a tire for repair. 1. An abrading tool configured for abrading a surface of a tire , the tool comprising:a rotary drive for rotating an abrading wheel;the abrading wheel rotatably attached to the rotary drive; anda depth guide including a pair of rotatable guide wheels rotatably attached to the depth guide, the pair of guide wheels being spaced apart along a common rotational axis such that the abrading wheel is arranged between the pair of guide wheels, where the abrading wheel is configured to extend a distance beyond the diameter of the guide wheels corresponding to a desired grinding depth, and where the abrading wheel has a rotational axis arranged substantially perpendicular to the common rotational axis of the guide wheels.2. The abrading tool of claim 1 , where a circumference of the abrading wheel extends into a hollow of each guide wheel and where the circumference of the abrading wheel is configured to contact the surface of the tire when abrading the surface of the tire.3. The abrading tool of claim 2 , wherein the guide wheels are frustocones.4. The abrading tool of claim 1 , wherein the circumference of ...

Methods of joining and repairing composite components

A first thermoplastic component and a second thermoplastic component including a first joint portion and a second joint portion, respectively, are provided. A least a portion of a surface area of each of the first and second joint portions include a respective first and second mating surface. The first and second mating surfaces of the respective first and second joint portions are positioned in contact with one another. The first and second joint portions are fusion joined. Fusion joining the first and second joint portions forms a fused unitary portion of the first and second thermoplastic components.

REPAIR AND REINFORCEMENT METHOD FOR AN AIRCRAFT

A repair and reinforcement method for an aircraft is provided. The method includes cleaning a corroded portion of a structure of the aircraft, applying an adhesive layer to the cleaned portion of the structure and forming a polymer matrix composite (PMC) patch for application to the adhesive. 1. A repair and reinforcement method for an aircraft , the method comprising:cleaning a corroded portion of a structure of the aircraft;applying an adhesive layer to the cleaned portion of the structure; andforming a polymer matrix composite (PMC) patch for application to the adhesive.2. The method according to claim 1 , further comprising identifying the corroded portion of the structure.3. The method according to claim 1 , wherein the cleaning comprises cleaning an area of the structure around the corroded portion.4. The method according to claim 1 , wherein the applying of the adhesive layer comprises applying a primer.5. The method according to claim 4 , wherein the primer comprises an epoxy resin or polymer based primer.6. The method according to claim 4 , wherein the primer includes a corrosion inhibitor.7. The method according to claim 1 , wherein the forming of the PMC patch comprises forming the PMC patch using a flexible and conformable prepreg.8. The method according to claim 1 , wherein the forming of the PMC patch comprises:saturating fibers in a resin matrix; andcuring the resin in place.9. The method according to claim 1 , wherein the forming of the PMC patch comprises conforming the PMC patch to irregular surface features.10. A repair and reinforcement apparatus for an aircraft claim 1 , the apparatus comprising:a corroded portion of a structure of the aircraft;a polymer matrix composite (PMC) patch formed to conform to the portion of the structure once cleaned; andadhesive disposed to adhere the PMC patch to the portion of the structure.11. The apparatus according to claim 10 , wherein the PMC patch encompasses an area of the corroded portion of the structure ...

Method for Repairing Vinyl Window Frames

A method for recovering vinyl window frames. The method of recovering vinyl window frames includes identifying damages in an existing vinyl frame having a plurality of planes, wherein the damages exist in at least one plane, measuring the area of the frame to be covered, creating a template of the frame by securing pre-cut plates together with a gap between to allow for bending along the gap, such that the template can conform to the frame, marking cuts to be made to the replacement cover using the template, cutting the replacement cover to duplicate the existing frame, and applying the replacement cover over the existing vinyl frame. 1) A method for recovering vinyl window frames , comprising:identifying damages in an existing vinyl frame having a plurality of planes, wherein the damages exist in at least one plane;measuring the area of the existing vinyl frame to be covered;creating a template of the existing vinyl frame by securing pre-cut plates together such that a gap sufficient to allow the pre-cut plates to bend about the gaps to conform to each plane of the existing vinyl frame is formed between each plate;marking cuts to be made in a replacement cover following the gaps in the template;cutting the replacement cover to duplicate the existing vinyl frame; andapplying the replacement cover over the existing vinyl frame.2) The method for recovering vinyl window frames of claim 1 , further comprising sanding the edges of the replacement cover to blend the cover with the existing vinyl frame.3) The method for recovering vinyl window frames of claim 1 , further comprising cutting at least one weep hole in the replacement cover claim 1 , wherein the weep hole is configured to drain liquid accumulated within the existing vinyl frame.4) The method for recovering vinyl window frames of claim 1 , further comprising painting the replacement cover to match the color of the existing vinyl frame.5) The method for recovering vinyl window frames of claim 1 , further ...

ABRASIVE COMPOSITION

Provided herein are abrasive compositions that use surfactants containing block copolymers of both propylene oxide and ethylene oxide moieties. Abrasive compositions derived from these copolymers were capable of providing both superior levels of cut rate while preserving a high quality surface finish on gelcoat surfaces comparable to those achieved using conventional rubbing compounds. 1. An abrasive composition comprising:an organic solvent;a nonionic surfactant comprising a block copolymer of polypropylene oxide and polyethylene oxide;a particulate abrasive;water; anda co-surfactant enabling the abrasive composition to form a stable oil-in-water emulsion in combination with the remaining components of the abrasive composition.2. The composition of claim 1 , wherein the nonionic surfactant has a hydrophilic-lipophilic balance ranging from 1 to 12.3. The composition of claim 1 , wherein the co-surfactant is nonionic and has a hydrophilic-lipophilic balance ranging from 10 to 20.4. The composition of any one of claim 1 , wherein the block copolymer has a polypropylene oxide: polyethylene oxide ratio ranging from 60:40 to 99:1 by weight.5. The composition of claim 4 , wherein the block copolymer has a polypropylene oxide: polyethylene oxide ratio ranging from 90:10 to 99:1 by weight.6. The composition of claim 1 , wherein the block copolymer is an ABA triblock copolymer represented by polyethylene oxide-block-polypropylene oxide-block-polyethylene oxide.7. The composition of claim 1 , wherein the block copolymer comprises terminal hydroxyl groups.8. The composition of claim 1 , wherein the block copolymer is present in an amount ranging from 0.1 percent to 10 percent by weight relative to the overall weight of the composition.9. The composition of claim 8 , wherein the block copolymer is present in an amount ranging from 0.5 percent to 2 percent by weight relative to the overall weight of the composition.10. The composition of claim 1 , further comprising a lubricant ...

BLADE CLEANING FOR AUTOMATED FIBER PLACEMENT MACHINES

Systems and methods are provided for cleaning composite fabrication machinery. One embodiment is a method for cleaning of a composite application machine, comprising: displacing an anvil of a head of an Automated Fiber Placement (AFP) machine from an operation location relative to a cutter, cleaning at least one of the cutter and the anvil, and relocating the anvil to the operation location relative to the cutter. 1. A method for cleaning of a composite application machine , comprising:displacing an anvil of a head of an Automated Fiber Placement (AFP) machine from an operation location relative to a cutter;cleaning at least one of the cutter and the anvil; andrelocating the anvil to the operation location relative to the cutter.2. The method of wherein:displacing the anvil comprises extending a first actuator;the cutters slide along a back face of the anvil when the anvil is in the operation location; andrelocating the anvil comprises retracting the first actuator until the back face of the anvil contacts the front faces of the cutters.3. The method of wherein: sliding a cleaning element into contact with a face of the cutter;', 'scouring the face of the cutter with the cleaning element;', 'retracting the cleaning element from the cutter;, 'cleaning at least one of the cutter and the anvil comprises4. The method of wherein:sliding the cleaning element comprises driving a second actuator, and comprises sliding the cleaning element into contact with a back face of the anvil;scouring comprises cleaning the back face of the anvil and the face of the cutter dependent to remove residue; andretracting the cleaning element comprises moving the cleaning element away from the anvil.5. The method of wherein:the scouring comprises driving the cleaning element across the back face of the anvil and the face of the cutter.6. The method of wherein:the scouring comprises spinning the cleaning element.7. The method of wherein:relocating the anvil to the operation location comprises ...

MACHINE VISION ACOUSTIC PANEL REPAIR WITH RETENTION OF ACOUSTIC PROPERTIES

An acoustic panel () for an aircraft nacelle () may comprise a perforated first skin (), a second skin (), and a core () sandwiched between them. A camera system () may scan a perforation pattern of a damaged portion () of the perforated first skin (). The damaged portion () of the perforated first skin () may be removed. A replacement patch () may be formed. A CNC machine () may drill the replacement patch () according to the perforation pattern. The perforations () in the replacement patch () may be aligned with perforations () in the perforated first skin. 1. A method of repairing an acoustic panel for an aircraft nacelle comprising:scanning, using a camera system, a perforation pattern in a damaged portion of the acoustic panel;forming a replacement patch;drilling a plurality of perforations in the replacement patch with a computer numeric control machine, wherein the computer numeric control machine uses the perforation pattern to drill the plurality of perforations;removing the damaged portion from the acoustic panel; andbonding the replacement patch to the acoustic panel.2. The method of claim 1 , further comprising storing the perforation pattern in a tangible non-transitory memory of a computer.3. The method of claim 1 , wherein the computer numeric control machine drills the perforations perpendicular to a surface of the replacement patch.4. The method of claim 1 , further comprising curing the replacement patch in a shape of the damaged portion prior to the drilling.5. The method of claim 1 , further comprising aligning the perforations in the replacement patch with perforations in the acoustic panel.6. The method of claim 1 , further comprising blowing air through the perforations and removing adhesive from the perforations.7. The method of claim 1 , wherein the computer numeric control machine comprises a six axis system.8. The method of claim 1 , wherein the scanning comprises capturing an image of the damaged portion.9. The method of claim 8 , wherein ...

METHOD FOR REPAIR OF A STIFFENED PANEL OF ISOGRID TYPE AND STIFFENED PANEL OF ISOGRID TYPE THUS REPAIRED

A method for repair of a damaged stiffened panel of isogrid type, wherein the repair method comprises a step of removal of material with the aim of removing at least one damaged rib and also steps of fitting at least one structural reinforcement connecting at least two nodes positioned about the damaged zone and of at least one wall reinforcement connecting the wall of the stiffened panel and the structural reinforcement. 1. A method for repair of a stiffened panel of isogrid type , comprising a wall , a network of ribs and nodes arranged in such a manner as to form cells , each cell having a triangular contour , said stiffened panel having at least one damaged zone , wherein the repair method comprises:removing material to remove at least one damaged rib from the damaged zone,fitting at least one structural reinforcement,connecting at least two nodes positioned around the damaged zone, and of at least one wall reinforcement connecting the wall of the stiffened panel and the structural reinforcement.2. The repair method according to claim 1 , wherein the step of removal of material comprises removing all the damaged ribs from the damaged zone.3. The repair method according to claim 2 , wherein the removal of material forms a large cell corresponding to six adjacent cells of the stiffened panel claim 2 , and wherein the step of removal of material comprises making an orifice in the wall.4. The repair method according to claim 1 , wherein the structural reinforcement is fitted and connected to the nodes surrounding the damaged zone claim 1 , then each wall reinforcement is fitted and connected to the wall and also to the structural reinforcement.5. The repair method according to claim 1 , wherein the wall reinforcement is fitted and connected at least to the wall claim 1 , then the structural reinforcement is fitted and connected to the nodes surrounding the damaged zone and to the wall reinforcement.6. A stiffened panel repaired using the repair method according to ...

Composiciones y metodos para restaurar cubiertas y lentes de plastico.

Equipos y métodos de restauración de plástico para restaurar efectivamente las propiedades de transmisión de luz y claridad óptica a una cubierta de luz de plástico sobre un automóvil u otra superficie de plástico tal como lentes para el sol o lente óptica correctiva. Los equipos y métodos restauran superficies de plástico que se han dañado mediante rayado y/u oxidación inducida por UV. Los equipos y métodos utilizan composiciones pulidoras y lustradoras que tienen partículas seleccionadas para pulir y lustrar una superficie de plástico y una composición protectora de UV que forma un recubrimiento protector de UV duro. Las composiciones pulidoras y lustradoras pueden incluir partículas abrasivas aglomeradas dispersadas en un portador líquido o de gel que progresivamente se desintegran en tamaño cuando se exponen al oxígeno y la presurización mecánica durante el pulido o lustrado.

Method for repairing fuel tanks

A method for repairing fuel tanks having detected leaks comprises (1) filling the detected leaks by applying an adhesive over the detected leaks and allowing the adhesive to cure to seal the detected leaks or (2) providing a fuel tank having a surface with detected leaks, providing a patch having a surface to be attached to the fuel tank surface having detected leaks, coating one or both surfaces with an adhesive, applying the patch over the detected leak(s) such that the adhesive is interposed between the patch surface and the tank surface, pressing the patch against the tank and allowing the adhesive to cure to bond the two surfaces together.

Method for repairing fuel tanks

A method for repairing fuel tanks having detected leaks comprises (1) filling the detected leaks by applying an adhesive over the detected leaks and allowing the adhesive to cure to seal the detected leaks or (2) providing a fuel tank having a surface with detected leaks, providing a patch having a surface to be attached to the fuel tank surface having detected leaks, coating one or both surfaces with an adhesive, applying the patch over the detected leak(s) such that the adhesive is interposed between the patch surface and the tank surface, pressing the patch against the tank and allowing the adhesive to cure to bond the two surfaces together.

Method for repairing carbon fiber reinforced plastic member

Disclosed is a method for repairing a carbon fiber reinforced plastic member. In one embodiment, the method for repairing the carbon fiber reinforced plastic member comprises the following steps of: primarily polishing a surface of a carbon fiber reinforced plastic (CFRP) member by using a sandpaper; coating a curable putty composition to the surface of the CFRP member, and curing the same to form a coating layer; and heat-treating the CFRP member on which the coating layer is formed at more than 80°C and less than 100°C, wherein the curable putty composition contains a transparent resin, a curing agent, and a solvent.

Method of overhauling composite structure with three linings and two inner layers

FIELD: process engineering. SUBSTANCE: invention relates to overhauling dual multilayer composite structures. Proposed method consists in overhauling composite material structure comprising first outer lining, first cellular inner layer, mid lining, second cellular inner layer and second outer lining. Note here that said method comprises replacement of sections of outer linings, mid lining and inner layers by new sections. Then, stiff pressure plate is placed on new section of the first outer lining and around it. Then, said plate is pressed against composite material structure. Then, new said sections of outer linings and mid lining are solidified. Prior to solidifying, mid lining is punctured to let air contained in first layer and second of inner part out. EFFECT: reduced overhaul time with no deterioration in repair quality. 4 cl, 3 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 412 816 (13) C2 (51) МПК B29C 73/04 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2008116811/05, 27.09.2006 (24) Дата начала отсчета срока действия патента: 27.09.2006 (73) Патентообладатель(и): ЭРБЮС ФРАНС (FR) R U Приоритет(ы): (30) Конвенционный приоритет: 29.09.2005 FR 05/52952 (72) Автор(ы): БЕРНЮС Кристоф (FR), МАРТИ Жан-Клод (FR), ФУРНЬЕ Жак (FR) (43) Дата публикации заявки: 10.11.2009 Бюл. № 31 2 4 1 2 8 1 6 (45) Опубликовано: 27.02.2011 Бюл. № 6 (56) Список документов, цитированных в отчете о поиске: US 4668317 А, 26.05.1987. FR 2773645 A1, 16.07.1999. RU 2039655 C1, 20.07.1995. US 5882756 A, 16.03.1999. RU 2224655 C2, 27.02.2004. 2 4 1 2 8 1 6 R U (86) Заявка PCT: EP 2006/066811 (27.09.2006) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 29.04.2008 (87) Публикация заявки РСТ: WO 2007/036545 (05.04.2007) Адрес для переписки: 103735, Москва, ул. Ильинка, 5/2, ООО "Союзпатент", пат.пов. С.Б.Фелицыной, рег. № 303 (54) СПОСОБ КАПИТАЛЬНОГО РЕМОНТА КОМПОЗИТНОЙ КОНСТРУКЦИИ ...

Process and apparatus for producing a glazing equippede based on polymer

본 발명은 압출 성형 프로파일 또는 프로파일에 연결된 부품의 포팅을 위한 장치에 관한 것으로, 압출 성형에 의해 제조된 여러 가지 프로파일을 상호 교제하거나 또는 상기 프로파일에 다양한 부품을 첨가 또는 고정시키는 것과 같은 새로운 방법이 기술되어 있다.

METHOD FOR CAPITAL REPAIR OF COMPOSITE CONSTRUCTION WITH THREE COVERINGS AND TWO INNER LAYERS

1. Способ капитального ремонта конструкции из композитного материала, содержащий последовательно первую внешнюю обшивку (2), первый ячеистый внутренний слой (16), среднюю обшивку (17), второй ячеистый внутренний слой (19), вторую внешнюю обшивку (2), включающий замену участков упомянутых внешних обшивок, упомянутой средней обшивки и упомянутых внутренних слоев новыми участками (6, 20, 21, 22, 23); наложение жесткой прижимной формы (8) на новый участок первой внешней обшивки (6) и вокруг него, прижатие прижимной формой к конструкции из композитного материала отверждение новых участков внешних обшивок и средней обшивки (6, 21, 23), отличающийся тем, что перед отверждением выполняют прокол (24) на новом участке средней обшивки (21) для дренажа воздуха, содержащегося в первом слое и втором слое (20, 22) внутренней части. ! 2. Способ капитального ремонта конструкции из композитного материала по п.1, отличающийся тем, что перед отверждением и дренажом выполняют прокол (25) нового участка первой внешней обшивки (6). ! 3. Способ капитального ремонта конструкции из композитного материала по п.1, отличающийся тем, что отверждение выполняют только в два этапа, причем первый из этих этапов относится к новым участкам первой внешней обшивки и средней обшивки (6, 21), а второй из этих этапов относится к новому участку второй внутренней обшивки (23), при этом новые участки второго внутреннего слоя (22) и второй внешней обшивки (23) устанавливают между обоими этапами. ! 4. Способ капитального ремонта конструкции из композитного материала по п.2, отличающийся тем, что отверждение осуществляют в единственном этапе. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2008 116 811 (13) A (51) МПК B29C 73/04 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21), (22) Заявка: 2008116811/12, 27.09.2006 (71) Заявитель(и): ЭРБЮС ФРАНС (FR) (30) Конвенционный приоритет: 29.09.2005 FR 05/52952 (87) Публикация PCT: WO 2007/036545 (05.04.2007) R ...

Repair of a damaged composite structure

本发明公开了一种修复由复合材料制成的飞行器机翼的蒙皮中的缺损的方法。该机翼具有附接至蒙皮内表面的纵梁，并且该方法包括以下步骤：从所述蒙皮切除纵梁的在所述缺损附近的部段；在所述缺损的上方将修复板定位在所述内表面上，使得所述修复板在所述纵梁的两相对的切削端部之间延伸；将纵梁修复部定位在所述修复板上，所述纵梁修复部具有足以与所述纵梁的每个切削端部都重叠的长度；将所述修复板附接至所述蒙皮；以及在每个切削端部处的重叠区域中将所述纵梁修复部附接至所述纵梁。本发明还公开了一种用于修复机翼的装置。

Repair or resumption of manufacture of a composite material part with three-dimensional woven fiber reinforcement

Réparation ou reprise de fabrication d’une pièce en matériau composite à renfort fibreux tissé tridimensionnel Un procédé de réparation d'une pièce en matériau composite (10) comprenant : - la réalisation d’une portion évidée (30) par retrait du matériau composite au niveau d’une zone endommagée (20), - la réalisation de rainures (110, 120) s’étendant sur les deux faces (11, 12) de la pièce (10) à partir des bords (32, 34) de la portion évidée, - la réalisation d’une pluralité d’orifices (130) dans l’épaisseur de la pièce débouchant dans les rainures, - le tissage tridimensionnel de préforme fibreuses de pièce de comblement (40, 50) comprenant une portion centrale (41, 51) ayant une forme correspondant à la forme de la portion évidée et une pluralité de faisceaux fibreux (420, 450) s’étendant depuis la portion centrale (41, 51), - le placement des préformes de comblement (40, 50) respectivement sur l’une et l’autre face de la pièce (10) avec les faisceaux fibreux présents dans les rainures présentes sur les faces de la pièce et dans les orifices de la pluralité d’orifices (130) de manière à ce que les faisceaux fibreux débouchent dans les rainures présentes sur la face opposé de la pièce, - l’imprégnation des préformes fibreuses de comblement (40, 50) avec une résine précurseur d’une matrice, - la transformation de la résine en matrice afin d’obtenir une pièce de comblement en matériau composite (60) comprenant un renfort fibreux densifié par une matrice. Figure pour l’abrégé : Fig. 7B. Repair or resumption of manufacture of a part made of composite material with three-dimensional woven fibrous reinforcement A method of repairing a part made of composite material (10) comprising: - the production of a recessed portion (30) by removing the composite material at the level of a damaged area (20), - the production of grooves (110, 120) extending on the two faces (11, 12) of the part (10) from the edges (32, 34) of the portion hollow, - the production of a plurality ...

Flexible composite pipe defect repairing method and structure

本发明公开了一种柔性复合管缺陷修复方法及结构，热塑性塑料管位于柔性复合管的缺陷段移除区域，热塑性塑料管两端与柔性复合管中移除缺陷段部位的两端内衬层连接，热塑性塑料管外缠绕有纤维增强带，纤维增强带缠绕厚度大于柔性复合管增强层和外保护层厚度之和。1.将柔性复合管中的缺陷段进行移除，移除缺陷段两端增强层和外保护层，将内衬层裸露在外2.将热塑性塑料管两端连接在柔性复合管中移除缺陷段部位的两端；3.使用纤维增强带在热塑性塑料管外及内衬层外进行缠绕，纤维增强带缠绕厚度大于柔性复合管增强层和外保护层厚度之和。降低了管材修复成本，保证修复处在再次承压时的可靠性。

System and method for in situ repair of gas turbine engine casing clearance

The present disclosure is directed to a system and method for repairing an abradable material coated on a casing of a gas turbine engine. The system includes an articulating guide configured to fit into an access port of the gas turbine engine. Further, the articulating guide has a proximal end and a distal end. The system also includes a repair tool configured at a distal end of the articulating guide. The repair tool includes a body having a proximal end and a shaped distal end, with the shaped distal end extending away from the body. Thus, the shaped distal body is configured to trench out an area of the abradable material comprising a defect. The system also includes a filler material for filling the trenched out area.

Device and methods for supporting of tire side strip

FIELD: motor car construction. SUBSTANCE: tire is taken that has side strip coupled with appropriate bead. Initiated is the limitation of lateral displacement for one of side strips and bead relative to the other side strips and beads. Side strip is engaged by means of the inclined element. One of side strips and bead are displaced in crosswise direction from other side strips and beads to get a crosswise side strip strain till crosswise strained configuration. Claimed device comprises area to accommodate the tire, limiting element, inclined element and drive gear. EFFECT: simplified repair of the tire. 21 cl, 6 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 566 592 C1 (51) МПК B29C 35/00 (2006.01) B29D 30/06 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2014117789/11, 30.09.2011 (24) Дата начала отсчета срока действия патента: 30.09.2011 (45) Опубликовано: 27.10.2015 Бюл. № 30 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 30.04.2014 (86) Заявка PCT: US 2011/054370 (30.09.2011) (87) Публикация заявки PCT: 2 5 6 6 5 9 2 (56) Список документов, цитированных в отчете о поиске: US 3038203 A, 12.06.1962;. DE 9407662 U1, 14.07.1994;. SU 1212840 A, 23.02.1986;. SU 414133 A1, 05.11.1974 (73) Патентообладатель(и): МИШЛЕН РЕШЕРШ Э ТЕКНИК С.А. (CH), КОМПАНИ ЖЕНЕРАЛЬ ДЕЗ ЭТАБЛИССМАН МИШЛЕН (FR) R U Приоритет(ы): (22) Дата подачи заявки: 30.09.2011 (72) Автор(ы): ИКОНОМОВ Методи Л. (US), ЧЕБЛИ Адиб Тони (US), ЗАРАК Сезар Э. (US), КОЛБИ Э. Брюс (US) 2 5 6 6 5 9 2 R U Адрес для переписки: 129090, Москва, ул. Б. Спасская, 25, строение 3, ООО "Юридическая фирма Городисский и Партнеры" (54) СПОСОБЫ И УСТРОЙСТВО ДЛЯ ОТКЛОНЕНИЯ И ПОДДЕРЖИВАНИЯ БОКОВИНЫ ШИНЫ (57) Реферат: Группа изобретений относится к способу и перемещение по меньшей мере одного из устройству для деформации боковины шины. боковины и борта в поперечном направлении от Способ заключается в том, что берут шину, других боковины и борта до ...

Flexible guide for repair of tire

FIELD: transport. SUBSTANCE: template has the orifice extending between tire inner and outer surfaces. Said template comprises long case in length equal to half the tire patch selected to be applied nearby the hole and in width extending between two opposed guide side edges extending along the casing, depth and means for template fastening to the tire, The latter allows the template fastening via the hole and extends from long case outer surface along and sideways of long case. Said fastener comprises rod and clamping mechanism for mounting along said rod. EFFECT: higher patch adherence. 21 cl, 13 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК B29C 73/12 (13) 2 536 977 C1 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2013124818/05, 29.10.2010 (24) Дата начала отсчета срока действия патента: 29.10.2010 (45) Опубликовано: 27.12.2014 Бюл. № 36 (56) Список документов, цитированных в отчете о поиске: US 2937576 А,24.05.1960. US 5788414 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 29.05.2013 (86) Заявка PCT: US 2010/054789 (29.10.2010) (87) Публикация заявки PCT: 2 5 3 6 9 7 7 А, 04.08.1998. SU 1659223 A1, 30.06.1991; . RU 10634 U1, 16.08.1999. (73) Патентообладатель(и): МИШЛЕН РЕШЕРШ Э ТЕКНИК С.А. (CH), КОМПАНИ ЖЕНЕРАЛЬ ДЕЗ ЭТАБЛИССМАН МИШЛЕН (FR) R U Приоритет(ы): (22) Дата подачи заявки: 29.10.2010 (72) Автор(ы): ИКОНОМОВ, Методи, Лубенов (US), ЗАРАК, Сезар, Энрике (US), ПАННИНГ, Натан, Джоэл (US), ВИДМАЙЕР, Майкл, Эдвард (US) 2 5 3 6 9 7 7 R U Адрес для переписки: 129090, Москва, ул. Б. Спасская, 25, строение 3, ООО "Юридическая фирма Городисский и Партнеры" (54) ГИБКАЯ НАПРАВЛЯЮЩАЯ ДЛЯ РЕМОНТА ШИНЫ (57) Реферат: Изобретение относится к шаблону для средство для крепления шаблона к шине. ремонта части шины и к способу подготовки Средство для крепления выполнено с части шины к ремонту. Шаблон имеет отверстие, возможностью прикрепления шаблона к шине проходящее между внутренней ...

COMPOSITIONS AND METHODS FOR RESTORING PLASTIC CAPS AND LENSES

1. Комплект принадлежностей для восстановления свойств оптической прозрачности и светопропускания пластмассовой поверхности, поврежденной нанесением царапин и/или окислением, включающий:по меньшей мере, один полировочный состав, имеющий полировочный абразив с зернистостью в интервале приблизительно от 50 микрон до 400 микрон, диспергированный в жидком или гелеобразном носителе;по меньшей мере, один состав для глянцевания, имеющий абразив для глянцевания с зернистостью в интервале приблизительно от 10 микрон до 60 микрон, диспергированный в жидком или гелеобразном носителе; ипо меньшей мере, один УФ защитный состав для нанесения в качестве УФ защитного покрытия на пластмассовую поверхность, обработанную полировочным составом и составом для глянцевания.2. Комплект принадлежностей по п.1, в котором полировочный абразив имеет зернистость в интервале приблизительно от 60 микрон до 300 микрон, и абразив для глянцевания имеет зернистость в интервале приблизительно от 15 микрон до 50 микрон.3. Комплект принадлежностей по п.1, в котором полировочный абразив имеет зернистость в интервале приблизительно от 70 микрон до 200 микрон, и абразив для глянцевания имеет зернистость в интервале приблизительно от 20 микрон до 45 микрон.4. Комплект принадлежностей по п.1, в котором полировочный абразив имеет зернистость в интервале приблизительно от 75 микрон до 150 микрон, и абразив для глянцевания имеет зернистость в интервале приблизительно от 25 микрон до 40 микрон.5. Комплект принадлежностей по п.1, в котором полировочный абразив включает агломераты, которые при механическом и окислительном воздействии в процессе полировки разрушаются до РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК B24B 29/00 (13) 2011 135 969 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2011135969/02, 30.01.2009 (71) Заявитель(и): ПиСиДабл-ю ХОЛДИНГЗ, ЭлЭлСи (US) Приоритет(ы): (22) Дата подачи заявки: 30.01.2009 (43) Дата публикации заявки: 10.03.2013 ...

Production and repair of composite armour plate and set for its production and repair

FIELD: process engineering. SUBSTANCE: set of inventions relates to armour plates intended for ballistic protection of personnel, light and heavy vehicles and machines and to set for production or repair of composite panel. Production of composite armour panel consists in making of horizontal frame, arranging of ceramic units, applying of cured binder on cavity being filled, creating the conditions for curing of said binder and removing of said horizontal frame. Said set comprises at least one cured binder and cylindrical ceramic units. Proposed repair process consists in the replacement of at least one ceramic unit, application of binder and creation of conditions for curing of said binder. EFFECT: better reparability, decreased weight. 30 cl, 12 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК F41H 5/04 (13) 2 564 302 C2 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2011103159/11, 28.01.2011 (24) Дата начала отсчета срока действия патента: 28.01.2011 (72) Автор(ы): КОЭН Майкл (IL) (73) Патентообладатель(и): КОЭН Майкл (IL) Приоритет(ы): (30) Конвенционный приоритет: (43) Дата публикации заявки: 10.08.2012 Бюл. № 22 R U 09.01.2011 IL 210,526 (45) Опубликовано: 27.09.2015 Бюл. № 27 C 2 2 5 6 4 3 0 2 R U (54) СПОСОБ ПОЛУЧЕНИЯ И РЕМОНТА КОМПОЗИТНОЙ БРОНЕВОЙ ПАНЕЛИ, И НАБОР ДЛЯ ЕЕ ИЗГОТОВЛЕНИЯ И РЕМОНТА (57) Реферат: Группа изобретений относится к броневым плоскость, создании условий для отверждения пластинам, обеспечивающим баллистическую связующего материала и удалении защиту личного состава, легкой и тяжелой горизонтальной рамы. Набор содержит по подвижной техники и транспортных средств, а меньшей мере один отверждаемый связующий именно к способу получения композитной материал, цилиндрические керамические блоки. броневой панели, набору для приготовления или Способ ремонта заключается в замене по ремонта композитной панели и способу ремонта меньшей мере одного из керамических блоков, композитной ...

Method and apparatus for reworking structures using resin infusion of fiber preforms

An area of a structure is reworked using resin infusion of a fiber preform. A resin flow hole is formed through the structure from a first side of the structure to a second side of the structure. The fiber preform is placed on the first side of the structure and substantially saturated with resin by flowing resin into the preform and out through the resin flow hole to the second side of the structure.

Aircraft radome repair technique

The repair surface is split into a number of steps each several millimetres thick, of decreasing diameter towards the outside, and the shape is formed with an external moulding, thus providing a good tolerance fit.

PIECE AND METHOD FOR REPAIRING A DAMAGED STRUCTURE, ESPECIALLY AIRCRAFT SKIN, AND A REPAIR KIT FOR IMPLEMENTING THE SAME

The part comprises a double internal/external extended plate adapted to be fixed to internal and external faces of a damaged structure, and a central core connecting the internal and external plates so as to form a groove between the plates. The part consists of a single block made of composite material. The plates have dimension and thickness that are determined by damaged location. A glass fold draped on the groove is placed between the plates and the structure. The core is traversed by an opening for passing links through the structure. The internal plate has folds to cover. The part comprises a double internal/external extended plate adapted to be fixed to internal and external faces of a damaged structure, and a central core connecting the internal and external plates so as to form a groove between the plates. The part consists of a single block made of composite material. The plates have dimension and thickness that are determined by damaged location. A glass fold draped on the groove is placed between the plates and the structure. The core is traversed by an opening for passing links through the structure. The internal plate has folds to cover, and is adapted to be fixed to the elements located in a close environment. Independent claims are included for: (1) a process for repairing a damaged structure; and (2) a kit for repairing a damaged structure.

PROCESS FOR REPAIRING EXTERNAL SKIN OF COMPOSITE STRUCTURE

Method for repairing thermoplastic plastics.

PROCESS FOR REPAIRING A COMPOSITE PANEL

La présente invention se rapporte à un procédé de réparation d'un panneau composite comprenant un ensemble de plis superposés disposés à l'intérieur d'une matrice, comprenant les étapes visant à : - Retirer les plis et la matrice au niveau d'une zone de réparation. - Mettre en place un ensemble de plis de réparation, lesdits plis de réparation étant disposés de manière à venir en chevauchement avec des plis du panneau à réparer, - Procéder au durcissement d'un matériau destiné à former une matrice autour des plis de réparations, caractérisé en ce que les plis de réparation sont disposés de manière à venir en chevauchement des plis du panneau de part et d'autre de la zone de réparation par rapport à un plan neutre du panneau à réparer.

PROCESS FOR THE REPAIR OF RADOMES AND RADOMES THUS REPAIRED

Repair or resumption of manufacture of a composite material part with three-dimensional woven fiber reinforcement

Réparation ou reprise de fabrication d’une pièce en matériau composite à renfort fibreux tissé tridimensionnel Un procédé de réparation d'une pièce en matériau composite (10) comprenant : - la réalisation d’une portion évidée (30) par retrait du matériau composite au niveau d’une zone endommagée (20), - la réalisation de rainures (110, 120) s’étendant sur les deux faces (11, 12) de la pièce (10) à partir des bords (32, 34) de la portion évidée, - la réalisation d’une pluralité d’orifices (130) dans l’épaisseur de la pièce débouchant dans les rainures, - le tissage tridimensionnel de préforme fibreuses de pièce de comblement (40, 50) comprenant une portion centrale (41, 51) ayant une forme correspondant à la forme de la portion évidée et une pluralité de faisceaux fibreux (420, 450) s’étendant depuis la portion centrale (41, 51), - le placement des préformes de comblement (40, 50) respectivement sur l’une et l’autre face de la pièce (10) avec les faisceaux fibreux présents dans les rainures présentes sur les faces de la pièce et dans les orifices de la pluralité d’orifices (130) de manière à ce que les faisceaux fibreux débouchent dans les rainures présentes sur la face opposé de la pièce, - l’imprégnation des préformes fibreuses de comblement (40, 50) avec une résine précurseur d’une matrice, - la transformation de la résine en matrice afin d’obtenir une pièce de comblement en matériau composite (60) comprenant un renfort fibreux densifié par une matrice. Figure pour l’abrégé : Fig. 7B. Repair or resumption of manufacture of a part made of composite material with three-dimensional woven fiber reinforcement A method of repairing a part made of composite material (10) comprising: - the production of a recessed portion (30) by removing the composite material at level of a damaged area (20), - the production of grooves (110, 120) extending on both sides (11, 12) of the part (10) from the edges (32, 34) of the portion hollow, - the production of a plurality of ...

Repair of a composite material part

Réparation d’une pièce en matériau composite Procédé de réparation d’une pièce en matériau composite (1) comprenant un renfort fibreux présentant un tissage tridimensionnel caractérisé en ce qu’il comprend : - l’identification d’au moins une zone endommagée (20) à la surface de l’aube (11), - la réalisation d’une portion évidée (40) par retrait du matériau composite au niveau de la zone endommagée (20), - le tissage tridimensionnel d’une préforme fibreuse de comblement ayant une forme correspondant à la forme de la portion évidée (40), - l’imprégnation de la préforme fibreuse de la pièce de comblement avec une résine précurseur d’une matrice, - la polymérisation de la résine en matrice afin d’obtenir une pièce de comblement (4) en matériau composite comprenant une préforme fibreuse tissée 3D, - le collage de la pièce de comblement (4) dans la portion évidée (40), ladite pièce de comblement occupant le volume défini par la portion évidée. Figure pour l’abrégé : Fig. 7 Repairing a part made of composite material Method for repairing a part made of composite material (1) comprising a fibrous reinforcement having a three-dimensional weave, characterized in that it comprises: - the identification of at least one damaged zone (20 ) on the surface of the blade (11), - the production of a recessed portion (40) by removing the composite material at the level of the damaged zone (20), - the three-dimensional weaving of a fibrous filler preform having a shape corresponding to the shape of the recessed portion (40), - the impregnation of the fibrous preform of the filler piece with a resin precursor of a matrix, - the polymerization of the resin in matrix in order to obtain a piece filler (4) made of composite material comprising a 3D woven fiber preform, - gluing the filler (4) in the recessed portion (40), said filler occupying the volume defined by the recessed portion. Figure for abstract: Fig. 7

Repair process for thermal protection of a nacelle structure

Procédé de réparation d’une protection thermique d’une structure de nacelle La présente invention se rapporte à un procédé de réparation d’une protection thermique endommagée recouvrant une structure de nacelle de turboréacteur d’aéronef en rapportant un matelas d’isolation thermique de réparation ainsi qu’une feuille de réparation sur la partie endommagée. Figure pour l’abrégé : Fig. 11. The present invention relates to a method of repairing damaged thermal protection covering an aircraft turbojet nacelle structure by adding a repair thermal insulation blanket. as well as a repair sheet on the damaged part. Figure for the abstract: Fig. 11.

Composite material structure repairing method for e.g. rail equipment, involves replacing portion of one of external shell by new portion, supporting key form, and piercing other shell till draining of air in inner core before hardening

The method involves replacing a portion of one of external shell by a new portion (6). A rigid key form (8) is set on a new portion and around the new portion. The key form is supported on the structure in composite material and the new portion is hardened. Other shell (3) is pierced till an inner core (1) and air contained in the core is drained before hardening.

Repairing thermoplastic unit or article by multistage application of compsns., - grinding and painting, restoring original appearance and strength, e.g. in vehicle repairs

In repairing a thermoplastic unit or article, to restore its original visual and solid state, the article is welded, glued or reshaped, and ground, followed by (a) application and drying of a prod. (A), (b) application, hardening and grinding of a prod. (B), (c) application of a prod. (C) onto the ground scratches, and drying, (d) application, hardening and grinding of a prod. (D, (e) application of prod. (C) to (part of) the article, and drying, and (f) painting. Pref. after welding, gluing or reshaping the article, a modified thermoplastic single component acrylic varnish, drying in 0.5-15 h (6 h) is applied. Application of prod. (A) is followed by application of a modified thermoplastic polyester coating, drying in 1 min.-3 h(15 mins.) before being ground with an abrasive of grain size 20-600 (100). USE/ADVANTAGE - Application is in industry, e.g. in vehicle repairs. Imperfections are completely covered.

Repair of parts made of organic matrix composite material

Réparation de pièc es en matériau composite à matrice organique Un procédé de réparation d'une pièce (11) en matériau composite à matrice organique (100) recouverte d’au moins une couche de peinture (102) comprend les étapes suivantes :a) le retrait de la peinture au niveau d’une zone endommagée de la pièce (11),b) le retrait du matériau composite (100) au niveau de la zone endommagée de manière à former une portion évidée,c) le dépôt d’une résine de réparation dans la portion évidée,d) la réticulation de la résine de réparation,e) l’application d’au moins une couche de peinture (102) sur la zone de réparation.Procédé dans lequel la résine de réparation est chargée avec des particules aptes à être détectées magnétiquement (41). Figure pour l’abrégé : Fig. 6.

Automated surface preparations for the inner surface of a tire

Automated treatment operations for preparing the inner surface of a tire for patch application is provided. One exemplary method includes the steps of locating the tire on a tire support, identifying a target area for preparing that is located on the inner surface of the tire, scanning the target area so as to acquire data regarding the inner surface of the tire at the target area, determining a treatment path using the data regarding the inner surface of the tire, treating the inside of the tire by removing material using a treatment tool, and positioning the treatment tool along the treatment path during the treating step.

METHOD AND SYSTEM FOR FOLDING PLI A PIECE OF COMPOSITE MATERIAL BY POWER SUPPLY

PROCESS FOR REPAIRING A COMPOSITE PANEL

Repair process for a stiffened isogrid-type panel and a stiffened isogrid-type panel thus repaired

Procédé de réparation d’un panneau raidi de type isogrid et panneau raidi de type isogrid ainsi réparé L'invention a pour objet un procédé de réparation d’un panneau raidi (10) de type isogrid endommagé, caractérisé en ce que le procédé de réparation comprend une étape de retrait de matière visant à retirer au moins une nervure endommagée ainsi que des étapes de pose d’au moins un renfort structurel (34, 34’, 34’’) reliant au moins deux nœuds positionnés autour de la zone endommagée et d’au moins un renfort de paroi (42.1, 42.2, 60, 80) reliant la paroi (12) du panneau raidi (10) et le renfort structurel (34, 34’, 34’’). L’invention a également pour objet le panneau raidi ainsi réparé. Figure 15 A method for repairing a stiffened isogrid-type panel and a stiffened isogrid-type panel thus repaired The invention relates to a method for repairing a damaged stiffened isogrid-type panel (10), characterized in that the repair method includes a material removal step to remove at least one damaged rib as well as steps of installing at least one structural reinforcement (34, 34 ', 34' ') connecting at least two nodes positioned around the damaged area and at least one wall reinforcement (42.1, 42.2, 60, 80) connecting the wall (12) of the stiffened panel (10) and the structural reinforcement (34, 34 ', 34' '). The invention also relates to the stiffened panel thus repaired. Figure 15

METHOD FOR REPAIRING A WALL CONSISTING OF MULTIPLE LAYERS

Method for repairing a damaged area of a composite fibre component with integrated fibre optics, together with a device

The invention relates to a method that is particularly suitable for the repair of damaged composite fibre components 1 with integrated fibre optics on aircraft. The method involves: a) pre-treating damaged area 2. in particular by mechanical removal of material, at least in certain areas; b) disclosing fibre optic 3 in an edge area 6 of damaged area 2, in particular by a chemical etching process, c) splicing in a bridging fibre optic 18 for restoring the optical connection; and d) gluing in and/or over a repair patch 20. The invention also relates to a device, in particular a repair stick 7, with two containers 8, 9 connected by a valve 10, and a contact body 11 connected by a flexible pipe 12 to second container 9. The container 9 contains an acid for carrying out the actual etching process, and second container 8 is filled with a lye for neutralising the acid after completion of the etching process. The method and the device are particularly suitable for the so-called "in field" repair and/or in the production of composite fibre components with fibre optics.

A kind of glass fiber reinforced plastics product method for repairing and mending

本发明公开了一种玻璃钢制品修补方法，包括以下步骤：A、修补前对玻璃钢制品需要修补的部位进行缺损接口的查看、并且对缺损部位进行清理、脱脂、干燥等处理；B、接着清洗修补面，晾干后注入粘结剂，使填补粉末和强力粘结剂的混合物满溢出缺损处的部分；C、将接补位置清理干净、凉干；D、修整玻璃钢制品的粘结处，对修补部位的表面进行抛光打磨，使得玻璃钢制品的外部轮廓符合修补前的模样；E、然后在修补表面贴补玻璃钢补强层或者热焊补接的方法将其复原，本发明具有修补方便，在修补过程中不需要特殊的修补环境，也不需要采用特殊的修补工具进行修补，大大降低修补的成本。

Method and system for the ply-by-ply machining of a component made of composite material, by applying energy

The invention relates to machine a component made of composite material in order to eliminate singularities, defects or damage to the component using a method that is repeatable and adaptable. To do this, it is proposed that the defects and their type be identified by image processing of the surface of the component and that the local machining rates at which the plies are machined be regulated at the function of this identification. According to one embodiment, a system ( 10 ) for the ply-by-ply machining of defects of a component made of composite material includes a numerical data processing unit ( 1 ) combined with a sweep control ( 2 ) that commands the sweep of a high-pressure water jet machine ( 20 ), and an image formation assembly ( 3 ) including an image capturing device ( 30, 31 ) connected with the numerical processing unit ( 1 ). The processing unit ( 1 ) includes regulating devices ( 11, 13 ) indexing local sweep rates, by convergence of brightness levels (NB) from the successive sweeps, these being formed by the image capturing assembly ( 3 ) toward making the brightness uniform according to a model (Mr) correlating brightness to ply state typology identification (BT) that can be supplied by a library ( 4 ). The correlation data (BT) and brightness levels (NB) are stored in memory modules ( 12, 14 ) of the processing unit ( 1 ).

Method for repairing fuel tanks

修补带有检出漏缝的油箱的方法，包括(1)在该检出漏缝上使用一种粘合剂以填补该漏缝，并让该粘合剂固化从而将检出漏缝密封，或(2)提供一种表面有检出漏缝的油箱，提供一块补片其表面将要贴在油箱表面上，将一个或两个表面都涂上粘合剂，将补片盖在检出漏缝上，以使粘合剂置于油箱表面和补片表面之间，将补片压在油箱上，让粘合剂固化从而将两个表面粘合在一起。

Method of repairing a fibre composite solid member

The present invention relates to a method of repairing a fiber composite solid member having a locally deteriorated surface area, such as having cracks or creases. The solid member may e.g. be a mold for the manufacturing of wind turbine blades or such blades. The method comprises machining a surface section comprising the locally deteriorated surface area in order to obtain a recess having a predefined depth and circumferential shape, placing a repair patch having a predefined thickness and circumferential shape matching the recess in the recess, and fastening the repair patch to the solid member by use of a binder material. At least some of the elastic and thermal properties of the repair patch and the binder material are so that after fastening, the repair patch and the binder material in combination have elastic and thermal properties which are substantially the same as the corresponding properties of the surface section before machining.

Structural rework of honeycomb core panel

本发明涉及蜂窝芯材面板的结构重修。公开了用于重修结构的方法和重修蜂窝芯材面板、包括重修蜂窝芯材面板的重修结构以及用于重修蜂窝声学面板和重修蜂窝非声学面板的引导件和切割设备。

Automated surface preparations for the inner surface of a tire

Automated treatment operations for preparing the inner surface of a tire for patch application is provided. One exemplary method includes the steps of locating the tire on a tire support, identifying a target area for preparing that is located on the inner surface of the tire, scanning the target area so as to acquire data regarding the inner surface of the tire at the target area, determining a treatment path using the data regarding the inner surface of the tire, treating the inside of the tire by removing material using a treatment tool, and positioning the treatment tool along the treatment path during the treating step.

Method for repairing damaged composite articles

ABSTRACT OF THE DISCLOSURE Damaged composites are repaired by use of a rubber modified vinyl ester resin composition as either an adhesive for bonding metal or cured composite to the area surrounding the damaged area or by placing an uncured reinforcing material saturated with a rubber modified vinyl ester resin composition over the prepared damaged zone and curing in place.

METHOD FOR REALIZING A TREE COMPRISING A COMPLEX PROFILE

Un procédé de réalésage d'un arbre (35) à forer, ledit arbre (35) comportant une cavité (37) creuse s'étendant suivant un axe longitudinal, ledit procédé comprenant les étapes suivantes : • introduire un tube de maintien (32) dans la cavité creuse (37), le tube comportant un diamètre correspondant au diamètre souhaité de pré-calibrage de l'arbre (35) ; • injecter une résine (33) entre la paroi intérieure de la cavité (37) de l'arbre (35) et la surface extérieure du tube (32) ; • retirer le tube (32) après le durcissement de la résine (33), l'espace libéré (19) par le tube de maintien (32) assurant une fonction de guidage pour réalésage de l'arbre ; • réaliser un premier réalésage d'usinage de l'arbre (35) en poussant une tête de calibrage (20) introduite selon l'axe longitudinal de l'arbre (35) dans l'espace libéré (19); • réaliser un second réalésage de finition de l'arbre (35) en tirant une tête de finition (51) dans l'arbre (35) pour l'élaboration d'un usinage de l'espace libéré (19) selon un diamètre évolutif. A method of reboring a shaft (35) to be drilled, said shaft (35) having a hollow cavity (37) extending along a longitudinal axis, said method comprising the following steps: • introducing a holding tube (32) in the hollow cavity (37), the tube having a diameter corresponding to the desired pre-calibration diameter of the shaft (35); Injecting a resin (33) between the inner wall of the cavity (37) of the shaft (35) and the outer surface of the tube (32); • removing the tube (32) after curing the resin (33), the space released (19) by the holding tube (32) providing a guide function for reaming of the shaft; • perform a first machining bore of the shaft (35) by pushing a calibration head (20) introduced along the longitudinal axis of the shaft (35) in the released space (19); Performing a second finishing boring of the shaft (35) by pulling a finishing head (51) in the shaft (35) for producing a ...

Method for repairing fuel tanks

A method is provided for repairing fuel tanks. The method includes defuming the fuel tank, removing rust and tar from the surface of the tank, coating the exterior surface of the gas tank with a plastisol compound and heating the plastisol compound to cure the compound and bond the compound to the fuel tank. The method provides a fast and inexpensive procedure for repairing fuel tanks.

Patent DE3731038C2

METHOD FOR REPAIR OF EXTERNAL COVERING OF COMPOSITE CONSTRUCTION

1. Способ ремонта конструкции из композитного материала, содержащей ячеистый внутренний слой (1) между двумя противоположными внешними обшивками (2, 3), включающий ! замену участка одной из упомянутых внешних обшивок новым участком (6); ! наложение жесткой прижимной формы (8) на новый участок и вокруг него; ! прижатие прижимной формой к конструкции из композитного материала; ! отверждение нового участка, ! отличающийся тем, что ! перед отверждением выполняют прокол (14) на другой из упомянутых внешних обшивок (3) непосредственно над внутренним слоем для дренажа воздуха, содержащегося во внутреннем слое. ! 2. Способ ремонта конструкции из композитного материала, содержащей ячеистый внутренний слой между двумя противоположными внешними обшивками (2, 3) и внутреннюю обшивку (17), разделяющую внутренний слой на два слоя (15, 16), включающий ! замену участка одной из упомянутых внешних обшивок новым участком (6); ! накладку жесткой прижимной формы (8) на новый участок и вокруг него; ! прижатие прижимной формы к композитной конструкции; ! отверждение нового участка, ! отличающийся тем, что ! перед отверждением выполняют прокол (18) на другой из упомянутых внешних обшивок (3) одного из слоев (16) внутренней части и среднюю обшивку (17) непосредственно над другим слоем внутренней части для дренажа воздуха, содержащегося во внутреннем слое. ! 3. Способ ремонта конструкции из композитного материала по п.1, отличающийся тем, что внутренний слой представляет собой сотовую структуру с ячейками, проходящими между двумя из обшивок (2, 3; 2, 17; 17, 3). ! 4. Способ ремонта конструкции из композитного материала по п.1, отличающийся тем, что прижимная форма содержит пове� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2008 116 813 (13) A (51) МПК B29C 73/04 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21), (22) Заявка: 2008116813/12, 27.09.2006 (71) Заявитель(и): ЭРБЮС ФРАНС (FR) (30) Конвенционный приоритет: 29.09.2005 FR ...

Apparatus for repairing conveyor belt on site

(57)【要約】本公報は電子出願前の出願データであるた め要約のデータは記録されません。

Solid Rocket Motor Fiber Composite Material Shell internal insulation cold bonding method for repairing and mending

本发明公开了一种固体火箭发动机纤维缠绕壳体内绝热层冷粘修补方法，预处理‑制备修补用熟胶片‑绝热层缺陷处理‑修补用熟胶片处理‑配胶粘剂‑修补。通过采用常温固化的方式保证对固体发动机内绝热层表面缺陷进行修补，保证内绝热层缺陷的发动机可继续正常使用，解决了因内绝热层缺陷导致发动机无法正常使用或报废的问题；修补后的内绝热层厚度及粘接面强度满足固体火箭发动机纤维缠绕壳体内绝热层要求，同时保证修补后纤维缠绕壳体的气密性能及烧蚀性能，适用于缺陷深度小于5mm、缺陷面积小于5000mm 2 的修补。

Method of repairing, splicing, joining, machining, and stabilizing honeycomb core using pourable structural foam and a structure incorporating the same

A core stiffened structure including a first skin, a second skin, and a core member having an expanded foam disposed within cell members. An attachment member is attached to the core stiffened structure through the first skin, the second skin, and the core member. The structure may form an aerodynamic structure of an aircraft. The structure may include an upper core member, a lower core member, a forward foam member bonded to a forward portion of the upper and lower core members and an aft foam member bonded to an aft portion of the upper and lower core members. Also, the structure may include an upper core member and a lower core member, with the upper core member including a plurality of cell member filled with structural foam.

Method for repairing ceramic matrix composite and ceramic matrix composite member

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.

Method for repairing a wall consisting of a plurality of layers

The invention relates to a method for repairing a wall ( 1 ), including a plurality of layers ( 2 ), each layer including fibers ( 3 ) extending in a main direction ( 4 ), and having a damaged area ( 5 ) over a plurality layers ( 2 ). The repair method includes a material removal step comprising making a recessed area ( 6 ) encircling the damaged area ( 5 ) and comprising a peripheral area ( 7 ) including steps ( 8 ) and adapted such that each step defines an interface area ( 9 ) having a width ( 10 ), the dimension of which in the main direction of the fibers of the lower layer adjoining the interface area ( 9 ) is greater than the dimension of said width in directions other than the main direction ( 4 ), a step of producing a replacement part ( 12 ) suitable for obstructing the recessed area, and a step of assembling the replacement part ( 12 ) onto the wall.

Part and method for repairing a damaged structure, in particular of an aircraft skin, as well as a repair kit for implementing same

The part comprises a double internal/external extended plate adapted to be fixed to internal and external faces of a damaged structure, and a central core connecting the internal and external plates so as to form a groove between the plates. The part consists of a single block made of composite material. The plates have dimension and thickness that are determined by damaged location. A glass fold draped on the groove is placed between the plates and the structure. The core is traversed by an opening for passing links through the structure. The internal plate has folds to cover. The part comprises a double internal/external extended plate adapted to be fixed to internal and external faces of a damaged structure, and a central core connecting the internal and external plates so as to form a groove between the plates. The part consists of a single block made of composite material. The plates have dimension and thickness that are determined by damaged location. A glass fold draped on the groove is placed between the plates and the structure. The core is traversed by an opening for passing links through the structure. The internal plate has folds to cover, and is adapted to be fixed to the elements located in a close environment. Independent claims are included for: (1) a process for repairing a damaged structure; and (2) a kit for repairing a damaged structure.

Snowmobile track repair system, apparatus, method and product

A system, method and apparatus to repair a flexible endless track (1) of a track-driven vehicle such as a snowmobile increases the usable life of the track and avoids its disposal. In the preferred embodiment, a worn section of a snowmobile track (1) is first prepared for repair by cleaning, grinding and tack gluing. Next, suitable hot vulcanizing repair materials (81) are placed over the worn spot. Finally, a number of tools (21, 22, 41, 42, 51, 61-69, 86) according to the invention are used to press these materials (81) into place, and necessary heat (23) and pressure is applied for the necessary length of time to complete the repair process.

User-facilitated material removal in composite structures

Suture repair of a sandwich panel

Réparation par suture d’un panneau sandwich La présente demande se rapporte à un panneau sandwich (10) d'une nacelle de turboréacteur, le panneau sandwich (10) comportant une première peau (12) et une seconde peau (12, 14) (14) délimitant entre elles un espace dans lequel une âme (16) est logée, au moins l’une des peaux (12, 14) comportant une zone endommagée (19), caractérisé en ce qu’au moins un réseau (A, B) de trous traversants (22) de part en part la première peau (12) et la seconde peau (14) est formé autour et/ou dans la zone endommagée (19), et en ce qu’au moins un fil (11, 11’, 11’’, 11’’’, 11’’’’) enfilé dans ce réseau (A, B) de trous traversants (22) forme une suture contenant, dans la zone endommagée (19), l’au moins une dite peau (12, 14) contre l’âme alvéolaire (16). Figure pour l’abrégé : Fig. 2 Repair of a sandwich panel by suturing The present application relates to a sandwich panel (10) of a turbojet engine nacelle, the sandwich panel (10) comprising a first skin (12) and a second skin (12, 14) ( 14) delimiting between them a space in which a core (16) is housed, at least one of the skins (12, 14) comprising a damaged zone (19), characterized in that at least one network (A, B ) through holes (22) right through the first skin (12) and the second skin (14) is formed around and/or in the damaged zone (19), and in that at least one wire (11, 11', 11'', 11''', 11'''') threaded into this network (A, B) of through-holes (22) forms a suture containing, in the damaged zone (19), the at least a said skin (12, 14) against the cellular core (16). Figure for abstract: Fig. 2

Repair of wind turbine components

A method of repairing a subsurface defect (40) comprising a void in a composite wind turbine component (10) is described. The method comprises: forming an inlet passage (70a) extending between the surface (30) of the component and the void, the inlet passage defining an inlet at the surface; forming an outlet passage (70b) extending between the surface of the component and the void, the outlet passage defining an outlet at the surface; administering resin through the inlet; and causing the resin to flow from the inlet towards the outlet such that the resin substantially fills the void. The inlet and outlet passages are each formed as a respective groove that extends longitudinally between first (72) and second ends (74) defined at the surface of the component. Each groove has a first end portion (76) and a second end portion (78) defining the first and second ends respectively, and an intermediate portion (80) located between the first and second end portions and extending into the void. The first and second end portions of the respective grooves are chamfered such that the end portions have a depth relative to the surface of the component that increases progressively moving along the groove from the first and second ends towards the intermediate portion, in order to prevent cracks from forming in the wind turbine component as a result of the repair.

Tool and method for repairing tubular members

A rotatable tool for use in repairing composite hollow shafts, namely for sports equipment, for example, composite hockey stick shafts. The rotatable tool includes a plurality of aligned spaced-apart grinding surfaces and proximal and distal guide bearings coaxially arranged along a tool shaft. The rotatable tool is used to form grooves proximate the repair location so as to enhance mechanical bonding of a composite repair material which spans a region of abutment of hollow shaft segments.

Method for repairing a flight component and patch therefor

The invention relates to a method for repairing an aircraft component ( 10 ) of fiber reinforced plastic, with the steps of: cutting out a damage site ( 12 ) by creating a hole ( 14 ), which (i) has a first extent (A 1 ) in a first direction and (ii) has a second extent (A 2 ), which is greater than the first extent (A 1 ), in a second direction, extending transversely in relation to the first direction, and (iii) has a scarfed rim ( 16 ), guiding through the hole ( 14 ) an inner patch ( 36 ), which is formed so as to cover the hole ( 14 ) completely from an inner side of the aircraft component ( 10 ), closing the hole ( 14 ) with a middle patch ( 26 ), which has a scarfed rim, the rim of the patch complementing the rim ( 16 ) of the hole, and adhesively bonding the patches ( 26, 36 ) to the aircraft component ( 10 ).

METHOD FOR REALIZING A TREE COMPRISING A COMPLEX PROFILE

Window with frame printed from polymer and method of window manufacturing

Production of a glass plate with a polymer frame or frame section, includes extending a profiled polymer section, using a calibrated extruder nozzle, immediately onto the edge region of the glass plate, or onto an intermediate section consisting of a glass light opaque layer and/or one or more adhesion improving layers. At least one local profile section is mechanically removed and a guide hardening polymer is injected, which forms a permanent connection with the already hardened polymer.

Repair Apparatus for Green Case

본 발명은 그린케이스의 유니포미티를 측정한 후, 유니포미티가 불량한 그린케이스의 트레드를 수리하여 유니포미티 성능을 만족시키는 완제품 타이어를 제조할 수 있도록 하는 그린케이스 수리장치에 관한 것으로서, 그린케이스가 지지 고정되는 그린케이스지지대와, 베이스에 대해 수직으로 설치되며 그린케이스지지대의 일측 단부가 회전 가능하게 결합되는 지지대 고정부와, 그린케이스의 트레드를 수리하는 트레드 수리기와, 베이스에 대해 수직으로 설치되어 트레드 수리기를 지지하는 수리기 지지대를 포함하여 구성되는 것을 특징으로 한다.

Structural rework of cellular core panels

Methods for reworking structures and reworked cellular core panels, reworked structures comprising the reworked cellular core panels, and guides and cutting apparatuses for reworking cellular acoustic panels and reworking cellular non-acoustic panels are disclosed.

Process and apparatus for joining strips of belt along their lengthwise running side edges

Method for repairing components with embedded inserts

Die Erfindung betrifft einen Verbindungsadapter zum Herstellen einer Verbindungskontur am stirnseitigen Ende eines Hohlprofils zum Verbinden mit einem Reparaturprofil, wobei der Verbindungsadapter einen ersten Befestigungsabschnitt mit einer Befestigungsfläche zum Befestigen an der Innenseite eines Hohlprofils und einen zweiten Befestigungsabschnitt zum Befestigen eines Reparaturprofils, wobei wenigstens eine zur Befestigung bestimmte Fläche des zweiten Befestigungsabschnitt geschäftet ausgebildet ist. The invention relates to a connection adapter for producing a connection contour at the front end of a hollow profile for connection to a repair profile, wherein the connection adapter has a first attachment portion with a mounting surface for attachment to the inside of a hollow profile and a second attachment portion for securing a repair profile, wherein at least one for attachment certain surface of the second attachment portion is formed geschet.

Method for repairing damaged area of composite material of airplane

本发明属于飞机复合材料修复领域，公开了一种飞机复合材料损伤区域的修复方法，包括：往待修复区的蜂窝芳纶酯芯层表面填充碳纤维预浸布，接着往碳纤维预浸布的表面上依次叠放穿孔分离膜、固体分离膜、隔板、加热片、受热膨胀片材以及通气管材料层，然后抽真空，再开启加热片，待碳纤维预浸布固化完全后，停止加热并冷却，去除碳纤维预浸布表面的材料，受热膨胀片材为在一定温度范围下能够受热启动膨胀的热固性膨胀复合片材，所述抽真空之后体系的真空度为1‑100KPa，碳纤维预浸布的固化温度不低于受热膨胀片材的启动膨胀温度，加热片加热至的温度不仅能够使得受热膨胀片材受热膨胀，而且能够使得碳纤维预浸布受热固化。采用本发明提供的方法能够增强修复位置的材料层间结合力，产品良率非常高，极具工业应用前景。

Forming adhesive bond to a substrate - by contacting adhesive impregnated open-celled foam with substrate under pressure to immobilise adhesive

L'INVENTION CONCERNE UN PROCEDE ET UN NECESSAIRE POUR DES REPARATIONS PAR COLLAGE. ON IMPREGNE D'UN ADHESIF RESINEUX THERMODURCISSABLE UNE MOUSSE SYNTHETIQUE SOUPLE A CELLULES OUVERTES; ON APPLIQUE LA MOUSSE SUR UN SUBSTRAT A COLLER OU SUR UNE DECHIRURE DE CE SUBSTRAT, PUIS L'ON COMPRIME LA MOUSSE POUR Y IMMOBILISER L'ADHESIF. APPLICATION : REPARATIONS SOUS L'EAU DE DECHIRURES DANS DES COQUES DE BATEAUX OU DES PLATES-FORMES DE FORAGE.

Method and apparatus for repairing a hole in a structural wall of composite material

Abstract of the Disclosure A hole (12) in a panel (10) of composite material is cut by a router or the like to dress it into a rounded hole (12'). A cavity is routed or otherwise formed in the panel (10) to extend across the dressed hole (12') in the direction of maximum tension loads in the panel (10). An insert (16) is secured in the cavity (18). The insert (16) and the cavity (18) have matching plan forms and each has a relatively narrow central portion and enlarged end portions (42, 44). The end portions (42, 44) of the insert interlock with end portions of the cavity (18). such that tension loads will be carried by the insert (16) from a region of the wall (10) on one side of the hole (12') across the hole (12') to a region of the wall (10) on the opposite side of the hole (12').

Integrated reinforcement patch

Methods and a tire patch for repairing a damaged tire portion are provided. In one embodiment, such method includes the steps of: buffing an interior surface of the tire about a perimeter of the damaged tire portion to form a patch receiving surface, the interior surface being buffed to a depth sufficient to place a tire patch reinforcement of a tire patch a distance of approximately 3 millimeters or less from a damaged tire reinforcement; covering the damaged portion by applying a pre-assembled patch to the patch receiving surface along the interior surface of the tire, the tire patch sized to cover the damaged area, such patch including a reinforcement layer interposed between an air-impermeable layer and an adhesive layer, the adhesive layer being at least partially uncured for facilitating attachment of the repair patch to the tire; and, curing the patch to the tire.

GUIDED MANUAL TOOL FOR TIRE GRINDING

1. Способ шерохования поверхности шины, включающий этапы, на которых:крепят шину для предотвращения ее поворота,обеспечивают механизм, проходящий от основания, и имеющий конец, к которому прикреплен элемент для шерохования, причем указанный механизм ограничивает перемещение элемента для шерохования пределами только заданной плоскости шерохования для взаимодействия с поверхностью шины по меньшей мере частично при ручном управлении оператора, при этом указанная плоскость шерохования проходит приблизительно параллельно оси вращения шины или совпадает с ней,перемещают элемент для шерохования в пределах указанной плоскости шерохования для взаимодействия с необходимой поверхностью шины ивручную направляют элемент для шерохования в контакт с поверхностью шины для формирования обработанной шерохованием кривой линии в плоскости шерохования вдоль поверхности шины.2. Способ по п. 1, дополнительно включающий этап, на котором:приводят во вращение элемент для шерохования вокруг оси вращения, расположенной приблизительно параллельно плоскости шерохования или совпадающей с ней.3. Способ по п. 1, дополнительно включающий этапы, на которых:перемещают механизм вдоль основания в направлении, в целом перпендикулярном плоскости шерохования,направляют элемент для шерохования в контакт с поверхностью шины и обрабатывают шерохованием дополнительную кривую линию вдоль поверхности рядом с предыдущей обработанной шерохованием линией.4. Способ по п. 3, дополнительно включающий этапы, на которых:повторяют этап, на котором перемещают механизм и направляют элемент для шерохования в контакт с поверхностью шины по мере необх� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК B24B 27/04 (13) 2013 124 800 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2013124800/02, 29.10.2010 Приоритет(ы): (22) Дата подачи заявки: 29.10.2010 (43) Дата публикации заявки: 10.12.2014 Бюл. № 34 (71) Заявитель(и): КОМПАНИ ЖЕНЕРАЛЬ ДЕЗ ЭТАБЛИССМАН МИШЛЕН (FR), МИШЛЕН ...