Abstract: A method for fabricating a tower or component thereof for use with a wind turbine is disclosed. The method comprises weaving a fibrous tow in a shape corresponding to the shape of the tower or component to form a flexible textile preform; and laminating the flexible textile preform to form a composite shell. Also disclosed is a wind turbine assembly comprising a composite wind turbine tower and a wind turbine coupled to the tower.

Abstract: A first insert (15) forming a ring is placed inside and in contact with a core (10) in degradable material. On the outer face of the core a plurality of inserts (20) is arranged each comprising a platform (21) applied against the outer face of the core and at least one blade (22) extending substantially radially outwards. A fibrous structure (56) is wound around the core passing over the platforms (21) and over the inner surface of the ring-shaped insert (15). Molding of the fibrous structure, impregnated with a composition containing a resin, is performed before polymerization of the resin and removal of the core.

Abstract: To fabricate a composite item, a first end effector is selected from a plurality of end effectors to apply tows to a form. The first end effector includes an integrated creel configured to store spools of the tow on an assembly of spindles. The assembly of spindles is substantially parallel to a longitudinal axis of the first integrated creel. The first end effector is secured to a positioning device. The tows are applied to the form and the tows are compacted on the form with a compaction device. The assembly of spindles are disposed circumferentially about the compaction device.

Abstract: A method is described for making a composite laminate formed by curing a stacked structure comprising at least two layers of strips of fibrous material impregnated with resin, wherein the strips in adjacent layers have different directional orientations. An apparatus is provided for simultaneously separating a band of fibrous material impregnated with resin into strips and depositing the strips between adjacent pin rows of a pinmat to form the stacked structure.

Abstract: A method of manufacturing a blade is provided. The method includes providing a plurality of first plies, each of the first plies sized to extend substantially the length of a span of the blade and providing a plurality of second plies, each of the second plies sized to extend only partially the length of the span of the blade. The method also includes layering the plurality of first plies and the plurality of second plies in a mold such that the plurality of second plies is interspersed throughout the plurality of first plies to spread apart the plurality of first plies to facilitate increasing a cross-sectional area of the blade and bonding the plurality of first plies to the plurality of second plies to facilitate forming a structural core of the blade.

Abstract: A technique facilitates construction of high temperature fiber reinforced polymer oilfield tubulars. The technique comprises a method of combining a fiber material and a high temperature thermoset resin to create a high performance composite material. The composite material is formed into an oilfield tubular that can be used in a variety of downhole applications. The method of combining the high performance materials with low modulus, high temperature coating materials during the manufacturing process produces composite tubular products that can survive prolonged exposure to deleterious well fluids in high temperature and high pressure downhole environments.

Abstract: A composite ring gear (10) with a metallic gear insert (30) has at least one filament (34) wound about the gear insert and an eyelet (32) a plurality of times. The filament is adapted to withstand a portion of a tensile load transmitted between the insert and the eyelet. The insert, eyelet and filament are then embedded in a composite material.

Abstract: A method and apparatus for forming an elongate tubular from a composite material. The composite material includes fibers and epoxy resin that are disposed around an elongated mandrel. The fibers are wound around the outer circumference of the mandrel and the epoxy resin may be applied to the fibers, before, during, or after, being wound onto the mandrel. A trough is provided that supports the mandrel between ends of the mandrel. An example trough includes a flexible membrane supported on its lateral ends to resemble a catenary.

Abstract: A filament winding apparatus includes a control unit, a rotation mechanism that rotates a mandrel, a hoop winding head that performs hoop-winding, and a helical winding head that performs helical-winding. The hoop winding head includes bobbins that feed fiber bundles to the mandrel and a circulation mechanism that circulates the bobbins around the mandrel. The control unit controls the rotation and circulation mechanisms such that the mandrel is rotated and the bobbins are circulated in the same direction during helical-winding. It is not necessary to cut fiber bundles after hoop-winding, and wasted fiber is not fed during helical-winding, thereby increasing economy and productivity.

Abstract: To treat a surface of an optical fiber cable structure, substantially an entire length of the optical fiber cable structure is moved through an inline plasma treatment system. As the optical fiber cable structure is moved through the inline plasma treatment system, the surface of the optical fiber cable structure is continually exposed to plasma. Exposing the surface of the optical fiber cable structure to plasma modifies a characteristic of the surface of the optical cable structure to improve an ability of the surface of the optical fiber cable structure to adhere to a target material.

Abstract: The invention relates to a method of making a casing-and-diverging-portion unit, the method comprising the following steps: forming fiber reinforcement from a first fiber preform made with a first type of fiber and a second fiber preform made with a second type of fiber different from the first type of fiber, said second preform being placed on the first preform; maintaining the fiber reinforcement in tooling so that it has a shape identical to the shape of the casing-and-diverging-portion unit that is to be made; and impregnating said fiber reinforcement with a thermosetting resin and impregnating the resin.

Abstract: A method of forming a fibre reinforced thermoplastic composite tube (P) in which reinforcing fibres (10) and thermoplastic resin matrix material (12) are placed around a mandrel (M) to provide a composite tubular pre-form (20) on the mandrel (M) which is then passed through a heated die (30) to compact and reduce the diameter of the pre-form (20) and change the state of matrix, the mandrel (M) with the formed tube (P) thereon exiting the die and the now formed tube (P) is removed from the mandrel, the composite tubular pre-form (20) being produced by winding reinforcement fiber (10) and thermoplastic fiber (11) onto the mandrel, the thermoplastic matrix being caused to flow and then solidify on cooling.

Abstract: Embodiments of the invention relate to a fiber application method and a fiber application machine for producing parts in composite material, such as for the application of a band of fibers on convex surfaces and/or with edges. The machine comprises a fiber application head and a moving system for moving the application head. The application head comprises a compacting system including a compacting roller intended to come in contact against the application surface to apply the band, and a compacting member placed downstream from the compacting roller and exhibiting a substantially planar contact surface, said compacting member being capable of being pressed by its contact surface, against an application surface, substantially on the entire width of a band, by at least one contact line.

Abstract: An apparatus for winding a fiber strand onto a bobbin having a longitudinal axis has a support holding the bobbin for rotation about the axis, a supply for feeding the fiber strand in a travel direction generally radially or tangentially to the bobbin, and a drive for rotating the bobbin about the longitudinal axis and for, when a fiber strand is engaged with the bobbin, winding the fiber strand onto the bobbin. A handling device is rotatable about the axis adjacent the bobbin and carries a strand layer for at a start of a winding operation moving into a predetermined angular position and pressing a leading end of the fiber strand against the bobbin. The handler also carries a cutter on the handling device for at an end of a winding operation cutting the fiber strand and thereby forming a trailing end attached to the bobbin and a new leading end.

Abstract: A fiber placement tool comprising a plurality of tool segments, each tool segment having an outer surface defining a predetermined profile, each tool segment being removably mounted on at least one elongate shaft.

Abstract: A composite panel and method of manufacture includes a support structure and a tape skin wound about the support structure. A mandrel assembly with extractable longitudinal mandrels facilitates winding of the tape skin onto the support structure. The composite panel is suitable for use in an aircraft floor system.

Abstract: There is described a method for making a vehicle (2), including a body comprising carbon fibres, preferably a military vehicle. The method consists of the body being wound up over a mandrel with threads (28) wetted in glue. The threads (28) contain carbon fibres. The threads (28) wound around the mandrel (22) are subsequently cured. After the curing, the body is drawn off the mandrel (22), and the ends of the body are cut off at appropriate angles. Then the front end and rear end of the body are closed with closure elements, preferably closure elements containing carbon fibres and armouring materials. During the winding process, one or more layers of lightweight ceramic and/or other armouring materials (26) are laid in, which thereby become integrated in the basic body.

Abstract: A method and apparatus for applying a pre-cured composite strip to a composite component. A pre-cured composite strip having a thermoset resin may be placed on a surface of a portion of the composite component where a caul plate seam may be expected. Caul plates may be placed on the composite component after placing the pre-cured composite strip to form the caul plate seam. The composite component may be cured after placing the caul plates on the composite component.

Abstract: An apparatus for producing tubes formed from fiber reinforced composite material, the apparatus including: an elongate hollow mandrel (3) having an internal mandrel cavity (5), the mandrel having an external surface (7) upon which reinforcing fiber material (9) can be wrapped to provide a composite lay-up (10) supported thereon; and fluid flow means (11) for enabling heat transfer fluid of different temperatures to be circulated through the mandrel cavity (5), such that when fluid at an elevated temperature is circulated, heat is transferred from the fluid, through the mandrel (3) to the composite lay-up (10) for curing or forming said lay-up.

Abstract: Processes for making fiber-on-end materials are provided. The materials can be used to make a variety of finished articles.

Abstract: By completing curing in a short period of time even at low temperatures and using an epoxy resin composition as a matrix resin of a prepreg, it is possible to obtain a fiber-reinforced composite plastic product such as a fiber-reinforced tubular composite with excellent mechanical properties and, more particularly, excellent impact resistance. The epoxy resin composition includes A component, B component, C component, D component and E component, where the content rate of sulfur atoms is equal to or more than 0.2 wt % and equal to or less than 7 wt %, and the content rate of the C component is equal to or more than 1 wt % and equal to or less than 15 wt %. A component: epoxy resins, B component: reactive products of the epoxy resins and an amine compounds including the sulfur atom in a molecule (the unreacted epoxy resins and/or the amine compounds may be included), C component: polyamide compounds soluble in the A component, D component: urea compounds, and E component: dicyandiamide.

Abstract: A non-compliant medical balloon, where the non-compliant medical balloon may be changed from a deflated state to an inflated state by increasing pressure within the balloon, is made with a first fiber layer, a second fiber layer over said first fiber layer such that the fibers of the first fiber layer and the fibers of the second fiber layer form an angle and a binding layer coating the first fiber layer and said second fiber layer. The interior surface area of the non-compliant medical balloon remains unchanged when the balloon changes from a deflated state to an inflated state.

Abstract: A modular composite utility pole has a plurality of sections, each with a tapered hollow tube having a plurality of plies, wherein a first end has a larger diameter than a second end, wherein each section is adapted to join at least one adjoining section at a joint wherein the first end of an upper section overlaps the second end of a lower section, the lower section having a ledge proximate to the second end of the lower section, with a fastener passing through the joint via apertures in the sections, and wherein, when the modular composite utility pole is erected, the joint is self-located by the joint features, and wherein substantially all vertical load is transferred between sections via the a surface of the second end of the upper section resting upon the ledge of the lower section. Also disclosed are individual sections and methods of making them.

Abstract: A pipe is wrapped with a composite to form a pre-stressed interface to facilitate load sharing between the materials. Prior to being wrapped, the pipe is placed in tension via hydraulic devices or the like. Alternatively, a combination of cured and uncured composite wraps is used in proximity to each other to apply compressive stress to the pipe. In addition, the pipe may be subjected to cold temperatures to change its dimensions prior to being wrapped with a composite material.

Abstract: A fiber optic faceplate fabricated using a series of stacked ribbon structures. Each ribbon structure comprises optical fiber segments that run from an input edge to an output edge with fixed input and output fiber-to-fiber spacing. Input and output edge spacers may be used to provide spacing between stacked ribbon structures. Ribbon structures may be provided individually or as one or more sheets of ribbon structures.

Abstract: A process of constructing a large diameter tank is provided. The process includes the step of providing a tank wall mandrel that has at least one drive wheel and at least one curved panel. Glass fibers are applied from a vertical winder to the curved panel in order to form a segment of a tank wall shell. Additional glass fibers are also applied to the curved panel at a location above the segment of the tank wall shell in order to form a unitary tank shell.

Abstract: Embodiments include an infusion-occlusion system having a delivery catheter, a guide catheter adapted to receive the delivery catheter, and a guidewire with an occlusion device adapted to be received within the guide catheter. The guide catheter of the catheter kit may be provided with an occlusion device at the distal end of the guide catheter. The delivery catheter may have an accessory lumen, coaxial or co-linear lumen, a supporting mandrel, or an occlusion device at its distal end. Moreover, according to some embodiments, occlusion devices may be a single material or a composite balloon having an inner liner and an outer layer of different materials, a high compliance low pressure balloon, or a filter device that restricts particles from passing through but does not restrict fluid, such as blood. An inflation device with a large volume and low volume syringe can be used to inflate the balloon.

Abstract: A method for manufacturing a solenoidal magnet having one or more coils wound onto a cylindrical former, and an annular end coil (20), mounted onto an end of the former such that no part of the former is present on the radially inner (A1) or axially outer (B2) sides of the end coil.

Abstract: A method of assembling a vehicle includes providing a mandrel that approximates the shape of a fuselage to be formed, winding a fiber around the mandrel by rotating the mandrel with a driver, heating the fiber to form the fuselage having a structural, hardened shell, removing the mandrel from the fuselage, and mounting the fuselage onto a frame rail of the vehicle.

Abstract: Methods for making a structure having an integral mounting flange involving providing a primary composite structure having a circumference, applying at least one circumferentially oriented core fiber about the circumference of the primary composite structure, applying at least one layer of attachment fibers to operably connect the core fiber to the primary composite structure about the circumference to obtain an integral mounting flange preform, and curing the mounting flange preform to obtain an integral mounting flange.

Abstract: A method for fabricating a grid-stiffened structure from fiber-reinforced composite materials. Ribs are formed on a smooth hard base tool. Expansion blocks are placed in the shallow cavities formed by the ribs and the base tool, and held in place by one of several means while a skin is placed over the ribs, expansion blocks, and base tool. The assembly is then placed in a vacuum bag and autoclave cured. After cooling, the formed structure is separated from the base tool and the expansion blocks are removed from the cavities. This abstract is provided to comply with the rules requiring an abstract, and is intended to allow a searcher or other reader to quickly ascertain the subject matter of the technical disclosure. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims.

Abstract: A steerable kink resistant access device is provided having an elongated body and a steerable portion. The access sheath has an outside diameter sufficiently small so that it may be inserted into a body cavity or conduit. The access sheath typically has two internal lumen, a first lumen sized and configured as an access to a surgical site and a second lumen sized and configured to contain a tensioning device that, when acted upon, will deflect the steerable portion. The tensioning device may be directly or remotely attached to an actuation device that operates to control the tensioning and loosening of the tensioning device.

Abstract: For use in the manufacture of reinforcement layers for flexible pipes which are capable of absorbing compressive or tensile forces, and which are used for the transport of oil and gas, a thermoplastic material is applied to a strength-imparting layer. The strength-imparting layers are reeled on reels, and following unreeling they are laminated by application of heat and in direct continuation applied to the flexible pipe. The strength-imparting layer expediently consists of a polymer which is reinforced with at least 20% by volume of fibres. The thermoplastic material is of a reversible type, i.e. it may change from being relatively soft, but non-sticky by changes in temperature. The use of the method according to the invention allows manufacture of very strong reinforcements for flexible pipes which cannot be manufactured using a solid material, such as steel, since high performing bending forces are required in the shaping.

Abstract: A pressure vessel and method for producing a pressure vessel is disclosed. The pressure vessel comprises a liner shell fabricated from composite material applied to a soluble mandrel having a body shaped to pattern an interior of the pressure vessel, the liner shell having an opening, a boss having an aperture therethrough, the boss sealingly bonded to the liner shell with the aperture adjacent the opening, and an outer shell fabricated from plies of composite material filament impregnated with matrix material wound over the liner shell and the boss, but not over the aperture.

Abstract: The present invention relates to a method for manufacturing a composite container with different opening sizes, which is accomplished by winding with fibers impregnated with resin. First, fibers impregnated with resin are wound on a first substrate for winding a first container, wherein first openings are positioned at both ends of the first container. Then, cut the first container into two shells with a first opening each, and slip one of the shells on a second substrate. Next, fibers impregnated with resin is used for winding the second substrate and the shell such that the fibers impregnated with resin wound on the second substrate and the shell are combined to form a second container, where both ends of the second container are the first opening and a second opening with different opening sizes. Thereby, filament winding can be applied for manufacturing containers with different opening sizes on both ends, and the technique of manufacturing and performance of containers are enhanced.

Abstract: The present invention provides a pressure shell formed by winding reinforcement fibers with resin material for hardening on an outer surface of a hollow tank base body, a high-pressure tank having the pressure shell, a manufacturing method of the high-pressure tank, and an apparatus for manufacturing the high-pressure tank. The pressure shell adopts the laminated structure in which a large number of fiber layers each formed by winding the reinforcement fibers around the tank base body are laminated. In a state the inside of the high-pressure tank is emptied, a compressive stress is applied to a lower fiber layer and a tensile stress is applied to an upper fiber layer. Particularly, in winding the reinforcement fibers around the tank base body, the reinforcement fibers are wound while filling fluid for pressure regulation in the tank base body, regulating a pressure applied to the fluid for pressure regulation, and adjusting a tension applied to the reinforcement fibers.

Abstract: A method of making a cylindrical pressure vessel (11) with a large diameter port in its sidewall includes the step of providing a mandrel (23) of desired diameter and filament winding upon the same. After winding one overall innermost layer, an annular reinforcement belt (16) is helically wound atop a defined region using a band (60) of resin impregnated parallel strands (39) under tension. The annular belt (16) is then itself helically overwound with the resin impregnated parallel strands of filamentary material under tension to provide two complete outer layers. After curing and removal from the mandrel (23) at least one aperture (71) is cut in the sidewall within the reinforcement belt (16) and a side port fitting (75) is installed in the aperture (71).

Abstract: An apparatus comprising a fiber placement head assembly and an infrared heating assembly is provided. The fiber placement head assembly includes a compaction roller assembly and a feeder assembly. An infrared heating assembly, a cooling mechanism, temperature sensors, and a controller are operably coupled to the fiber placement head assembly. The infrared heating assembly includes an infrared heater that generates a heating profile. The heating profile defines a heating zone on either a tool or previously laid tows. If the burn point of either the tool or previously laid tows within the heating zone is approached, the controller, which receives temperature readings from the temperature sensors, simultaneously disables the infrared heater and activates the cooling mechanism. As such, the tool and the previously laid tows are protected from being ruined due to an over temperature condition.

Abstract: A method and device for manufacturing a body, a device for implementing the method, and products obtained by the method. In the method, at least a first heated composite strip is introduced into at least one die, and at the same time, at least one molten material is introduced into the die in contact with the first composite strip, to obtain at least one second composite strip, and the second composite strip is wound around a support rotating about its axis.

Abstract: An assembly and method for manufacturing a composite reinforcement for unitizing a structure are provided. According to one embodiment, the assembly includes a base having a plurality of pins extending outwardly therefrom to define a structure about which a composite fiber is wound to define a composite reinforcement preform. The assembly also includes a plurality of mandrels positioned adjacent to the base and at least a portion of the composite reinforcement preform, and a cap that is positioned over at least a portion of the plurality of mandrels. The cap is configured to engage each of the mandrels to support the mandrels and the composite reinforcement preform during a curing process to form the composite reinforcement.

Abstract: A “PROCESS FOR OBTAINING PIPES AND JOINTS FROM A POLYMER COMPOSITE” comprising an inner pipe (1), 3.0 to 8.0 mm thick, made of fiber glass with an epoxy resin matrix for resisting the corrosion of the produced fluids and the abrasion of the solid suspended particles. They are made in a metal polished mold through the “filament winding” process with roving thread at a winding angle of 52° to 55°, impregnated with epoxy resin and catalyzed with an aromatic amine, anhydride and aliphatic amine-based cold cure agent, in order to stand chemical attacks and temperature, with the ends being made from molds with a molded thread made of an epoxy resin and carbon fiber compound, wherein the outer face suffers a sanding down process which decreases brightness and adherence in order to accommodate a second layer of “filament winding”, with roving thread at a winding angle between 80° and 85°, 5.0 mm and 8.

Abstract: A 360° tool for making a one-piece composite tubular structure, such as a skin of an acoustic liner, is adjustable between a molding position and a non-molding position. The tool includes a base, a fixed segment mounted to the base, first and second doors hingedly connected on either side of the fixed sector, and third door hingedly connected to the second door. The third door has a circumferential extent that is less than one-fourth that of either the first or second door. Sealing members are provided between the doors. Collectively, the fixed sector, and the first, second and third doors have a predetermined shaped surface that corresponds to a portion of the contour of the tubular structure to be formed. After composite material is applied on the outer surfaces of the fixed sector and the doors, a vacuum bag is formed to surround the composite material and also the joint areas on the inner surface of the tool. The entire tool may be placed in an autoclave for curing.

Abstract: An apparatus and method are provided for replacing a creel in a fiber placement machine, by sequentially moving replaceable creels into place on the fiber placement machine, via tracks and/or guide rails, as one or more spools in a previously operating creel are exhausted, and removing the creel having the one or more exhausted spools, to thereby allow fiber placement to continue from the replacement creel while the creel having one or more exhausted spools of material is replenished. An auto-splice apparatus and method are incorporated into the replaceable creel and fiber placement machine, for assisting in the exchange of replaceable creels.

Abstract: An apparatus and invention are provided for accelerating an added tow to match the lay-down speed of other tows exiting a compaction roller of a fiber placement head, by driving the added tow with an add roller operatively coupled to be driven at the same peripheral speed as a feed roller having a peripheral speed matching the peripheral speed of the compaction roller.

Abstract: The present invention relates to a tubular-shaped component (19) for an aeronautical fuselage made of composite materials comprising an outer skin (1) without joints having a cylindrical or cylindrical-conical shape, a plurality of stiffeners or stringers (2) longitudinally arranged in said outer skin (1) and a plurality of anchoring elements (3) for anchoring other elements to subsequently be incorporated transversally arranged between said stiffeners or stringers (2). The invention also comprises a jig (18) comprising a support body (12) and a plurality of panels (9) that can shift between an extended position (10) and a retracted position (10?) in both directions and a process for manufacturing said component (19) in the last step of which once the tubular component (19) is formed and cured, it is separated from the jig (18) by means of a longitudinal movement after the shifting of those elements of the jig (18) preventing it, and particularly the panels (9) that can be shifted.

Abstract: The invention describes the production and utilization of a multi-layer composite material, a polyester resin and/or vinyl-ester resin based adhesive with special composition, applied on the surface or between the layer of the enforced object, which is made of unsaturated polyester resin and/or vinyl-ester resin based, glass-fiber reinforced, pre-made band shaped prepreg material, which can be used on surface of cylindrically symmetric objects like piers, pipes, pillars, etc. to strengthen their stability, endurance and resistance. This material can also be used to repair certain small irregularities on the enforced objects surface. Initiators and substances are added to the prepreg's matrix material, such as poly-?-caprolacton; acetyl-acetone and alkyl-(acrylate)-methacrylate type monomers to result in networking of the resins. Peroxides decompose due to activator compounds coming from diffusion on the surface of the adhesive substance.

Abstract: A method for manufacturing a pressure vessel includes the steps of obtaining a metal liner and applying a first layer of adhesive to an outer surface of the metal liner. The metal liner is then placed into a vacuum bag and a vacuum is applied, thus securing the adhesive to the outer surface of the metal liner. After curing of the adhesive, a filamentary material is wound around the liner, where the filamentary material adheres to the first layer of adhesive forming an overwrap layer on the outer surface of the metal liner, forming the pressure vessel.

Abstract: A process of constructing a large diameter tank is provided. The process includes the step of providing a tank wall mandrel that has at least one drive wheel and at least one curved panel. Glass fibers are applied from a vertical winder to the curved panel in order to form a segment of a tank wall shell. Additional glass fibers are also applied to the curved panel at a location above the segment of the tank wall shell in order to form a unitary tank shell.

Abstract: A cylindrical casing (12) is disclosed which is of glass reinforced plastic and has an end cap at each end thereof. In the drawing the illustrated end cap is designated 42.2. Each end cap has at least one opening (52) therein through which water can flow. The illustrated end cap 42.2 is held in place by a mounting ring (28) embedded in the wall of the casing and encircling the casing internally. An internal groove (32) extends circumferentially of the mounting ring (28). A first locking ring (34) having a peripherally extending external rib (36) is within the ring 28. The rib (36) is in the groove (32). A second locking ring (38) fits into the locking ring (34) to expand it outwardly and press the rib (36) into the groove (32). Stud holes (40) in the end cap (42.2) and in the locking ring (38), receive studs (44) which secure the locking ring (38) to the end cap (42.2).

Abstract: A method for fabricating a grid-stiffened structure from fiber-reinforced composite materials. Ribs are formed on a smooth hard base tool. Expansion blocks are placed in the shallow cavities formed by the ribs and the base tool, and held in place by a synthetic elastomer-based adhesive while a skin is placed over the ribs, expansion blocks, and base tool. The assembly is then placed in a vacuum bag and autoclave cured. After cooling, the expansion blocks are removed and the formed structure is removed from the hard base tool. This abstract is provided to comply with the rules requiring an abstract, and is intended to allow a searcher or other reader to quickly ascertain the subject matter of the technical disclosure. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims.