Abstract:
A transportable system and method for the in situ eccentric manufacturing of reinforced thermoplastic pipelines in continuous lengths up to 10 miles and from 8 to 60 inches in diameter having a rotating frame assembly with a eccentric spools for application of reinforcing tapes and other components to a polyolefin core pipe, and further having a forming machine for cross sectional shape reduction of the reinforced thermoplastic pipelines to facilitate pulling the reinforced thermoplastic pipelines inside a host pipeline. Also provided are continuous monitoring and marking with application of tape in the hoop stress direction and the axial stress direction as well as saturated tape feeding stations for impregnation of the reinforcing tape for in situ curing.
Abstract:
A method of forming a homogenous composite pipe of unspecified length from strips of fiber reinforced thermoplastic material is disclosed. A mandrel is arranged stationary in a process direction to extend freely from a first supported end to a second end. A slip-sheath is applied about the mandrel. The thermoplastic material strips are wound about the slip-sheath. A section of the thermoplastic material strip winding is consolidated. The slip-sheath is formed from tape material which is applied longitudinally onto the mandrel surface. The slip-sheath is connected to a puller arranged downstream of the mandrel in the process direction. Consolidated pipe sections are pulled off from the second end of the mandrel in synchronization with the winding and consolidation. An assembly for carrying out the method.
Abstract:
A winding apparatus for and method of manufacturing structures (116) includes a rotating faceplate (74) upon which are mounted a forming station for forming a supply of strip material before it is wound into a desired structure and a plurality of inner supports in the form of rollers (110) mounted for rotation about an axis and with said faceplate and a plurality of outer driven rollers (92) provided on an outer faceplate (118). The inner rollers (110) are mounted for radial movement relative to the inner faceplate (74). In operation, the inner rollers (110) act to support an inner portion S1 of strip material wound thereon whilst allowing it to be supplied from an inner diameter thereof to said forming station and the outer rollers (92) act to support an outer portion S2 of said strip. Said outer rollers are driven as and when necessary to transfer material to the inner portion S1 and the radial position of the inner rollers increases as strip material is consumed from an inner diameter, thereby to maintain support of the strip supply regardless of the amount that has been consumed.
Abstract:
According to one aspect, the present invention relates to a method of manufacturing at least one non-uniform thickness composite spar component. The method comprises braiding a plurality of fibers over a non-cylindrical mandrel to form a variable thickness shaped fiber preform, flattening the shaped fiber preform and cutting the flattened shaped fiber preform to obtain the at least one non-uniform thickness composite spar component. Spars made according to various embodiments of the present invention are faster and less expensive to manufacture than conventional composite spar components.
Abstract:
An apparatus (50) for and method of manufacturing structures (116) includes coaxial rotating faceplates (74, 89, 97), capable of rotation at different angular speeds. A plurality of forming rollers (76) and diameter defining rollers (78) are mounted on the inner faceplate (74, 89), which, in operation, cause a strip material (80) to be plastically deformed into a helical winding which may be lain down in abutting or self-overlapping relationship to form said tubular structure (116). A plurality of support rollers are mounted in a circle on the inner faceplate (74, 89) at a distance from the axis exceeding that of the outermost forming roller and serve to support the stock of strip material.
Abstract:
A spool winding assembly for winding a composite strip onto a spool having a hub is disclosed. The strip includes an elongate plastic strip having a flat base portion and a plurality of laterally spaced apart lengthwise extending rib portions upstanding from the base portion; and a plurality of elongate reinforcing members extending lengthwise within respective rib portions, the rib portions and the reinforcing members forming composite ribs. The assembly includes: a main frame, a spool holder for rotatably supporting the spool relative to the main frame, a spool drive unit for driving the spool with respect to the main frame, a carriage mounted for lateral movement with respect to the spool, a bender mounted to the carriage for receiving the strip as it is fed towards the hub of the spool and for deforming the strip to give it a curved base portion, and a bender drive unit operably connected to the bender for driving the strip through the bender.
Abstract:
A breathing circuit component includes an inlet, an outlet and an enclosing wall. The enclosing wall defines a gases passageway between the inlet and the outlet. At least a region of the enclosing wall is formed from a breathable material that allows the passage of water vapour without allowing the passage of liquid water or respiratory gases. The breathing circuit component is the expiratory limb of a breathing circuit.
Abstract:
A method is provided for making a composite laminate aircraft skin for a fuselage in multiple composite panels. A resin-impregnated composite tape is placed on a lay-up surface of a mandrel tool to form the composite laminate aircraft skin as a barrel that is substantially the shape of a fuselage section. The barrel is cut into a plurality of panels on the mandrel tool, and at least one panel of the plurality of panels is transferred, individually and independently of all other of the plurality of panels, from the lay-up surface of the mandrel tool to a first cure tool of a plurality of cure tools having an aero surface tooled to an outer mold line. The at least one of the panels is cured on the first cure tool to form a cured composite panel. The first cure tool defines and controls the outer mold line of the at least one panel. The cured composite panel is removed from the first cure tool.
Abstract:
Armouring tape (102) for wrapping around a hose (300) during its fabrication by a hose-wrapping machine (200; 400). The tape (102) is coiled into a roll (100) having a hollow core (109) from which the tape (102) is unwound to be wrapped onto the hose (300). Th hose-wrapping machine (200; 400) rotatably mounts the roll (100) with the hose (300) passing through the roll core (109), the roll axis (108) being skewed to the hose axis (304) by the helix angle at which the tape (102) is to be wrapped onto and along the hose (300). The hose (300) is moved longitudinally through the longitudinally static roll (100) and at the same time, the roll (100) is rotated around the longitudinal axis (304) of the non-rotating hose (300). The armouring tape (102) unwinds from the inside (109) of the roll onto and along the hose (300) so as to wrap the hose (300) with a uniform helix of armouring tape (102). The use of a tape (102) containing an elastomer-enbedded array of armouring cables (104) enables armouring wires and elastomer layers to be applied without a stabilising layer of fabric, and greatly simplifies setting-up of machinery for hose fabrication. The use of a tape roll (100) which can be unwound from its inside (109) enables hoses to be wrapped without having to orbit rolls that are very large and heavy.
Abstract:
An apparatus, and method for laying up structural filaments. The apparatus includes an openable race providing a circular path for a carrier bearing a filament source. The carrier moves circumferentially within the race and may be formed as a centerless wheel. The carrier may be formed in sections to facilitate opening of the race to insert a workpiece.