A joined article includes a first component having a laser-treated surface portion and a second component having a laser-treated surface portion. An adhesive joins the first component to the second component at the treated surface portion. A method of making a joined article form components and a system for making joined articles are also disclosed.

A method for producing a composite material. The method includes the steps of producing an initial dry preform, formed from unidirectional continuous dry fibers, applying non-woven filaments to a first main face of the dry preform, and needling the filaments with a needling device. The needling device includes a plurality of needles, each provided with at least one notch, so that filaments are driven by the needles and arranged in a direction substantially perpendicular to the continuous fibers of the dry perform. The method includes the further step of impregnating the dry preform with an impregnation polymer, the impregnation polymer constituting the matrix of the composite material part.

A method of producing a partially separated fiber bundle wherein, while a fiber bundle includes a plurality of single fibers travels along a lengthwise direction of the fiber bundle, a separator provided with a plurality of projected parts is penetrated into the fiber bundle to create a separation-processed part, and entangled parts, where the single fibers are interlaced, are formed at contact parts with the projected parts in at least one separation-processed part, thereafter the separator is removed from the fiber bundle, and after passing through an entanglement accumulation part including the entangled parts, the separator is penetrated again into the fiber bundle, characterized in that a separation processing time t1 during being penetrated with the separator and a time t2 from being removed with the separator to being penetrated again into the fiber bundle satisfy Equation (1): 0.03≤t2/(t1+t2)≤0.5.

A method is described for producing a prepreg formed by applying a matrix resin to a reinforcing fiber sheet, wherein the method can effect continuous running without clogging due to generated fuzz even at a high running speed and effect efficient impregnation of the reinforcing fiber sheet with a matrix resin. A method of producing a prepreg includes allowing a reinforcing fiber sheet to pass substantially vertically downward through the inside of a coating section storing a matrix resin to obtain a matrix resin-impregnated reinforcing fiber sheet in which the matrix resin is applied to the reinforcing fiber sheet and at least heating the matrix resin-impregnated reinforcing fiber sheet, wherein the coating section includes a liquid pool and a narrowed section which are in communication with each other, wherein the liquid pool has a portion whose cross-sectional area decreases continuously along a running direction of the reinforcing fiber sheet.

A bulk moulding compound comprising one or more cyanate ester, a catalyst, a filler and reinforcement fibres is provide, whereby the one or more cyanate ester is independently selected from a difunctional cyanate ester compound and/or a polyfunctional cyanate ester and mixtures of these cyanate esters. Furthermore, the catalyst is independently selected from the group consisting of 4,4′ methylene-bis(2,6-diethylaniline) (M-DEA), 4,4′-methylene-bis(3-chloro-2,6-diethyl¬aniline) (M-CDEA), aluminum(III)acetylacetonate, and mixtures thereof.

Forming features in the surface of a bicycle component involves depositing a substance onto a substrate in a geometric pattern to form a transfer medium. Forming features may also involve positioning the transfer medium relative to an unformed bicycle component, and forming a negative of the geometric pattern in the bicycle component through the application of heat and/or pressure to the transfer medium and the unformed bicycle component. The transfer medium may be configured for use in the molding of carbon fiber reinforced plastic (“CFRP”) bicycle components and may include a substrate formed of a flexible material, and a geometric pattern formed of a hard material, the hard material different than the flexible material.

Aircraft stringers having carbon fiber reinforced plastic (CFRP) material reinforced flanges are disclosed. An example stringer to be coupled to a skin of an aircraft comprises a flange. The flange includes a first portion of a first stiffening segment. The flange further includes a first portion of a second stiffening segment coupled to the first portion of the first stiffening segment. The flange further includes a CFRP reinforcement segment coupled to the first portion of the first stiffening segment and to the first portion of the second stiffening segment. The CFRP reinforcement segment strengthens the first portion of the first stiffening segment and the first portion of the second stiffening segment.

Aircraft stringers having carbon fiber reinforced plastic (CFRP) material reinforced flanges are disclosed. An example stringer to be coupled to a skin of an aircraft comprises a flange. The flange includes a first portion of a first stiffening segment. The flange further includes a first portion of a second stiffening segment coupled to the first portion of the first stiffening segment. The flange further includes a CFRP reinforcement segment coupled to the first portion of the first stiffening segment and to the first portion of the second stiffening segment. The CFRP reinforcement segment strengthens the first portion of the first stiffening segment and the first portion of the second stiffening segment.

A door for a thrust reversal system, an aircraft with such a door, and a method for manufacturing a door of a thrust reversal system. The door comprises a wall formed from long fibers embedded in a thermoplastic resin matrix and a network of ribs overmolded on one of the faces of the wall. A propulsion assembly of an aircraft comprises a thrust reversal system having a plurality of such doors.

Provided is an improvement in a method for manufacturing a slit carbon fiber bundle. The method for manufacturing a slit carbon fiber bundle of the present invention is a method including a step of forming a resin film on one surface of a flat carbon fiber bundle to obtain a single-sided coated carbon fiber bundle, and a step of partially slitting the single-sided coated carbon fiber bundle using a slitter roll to obtain a slit carbon fiber bundle, which has been split into sub-bundles, wherein in the step of slitting, the single-sided coated carbon fiber bundle contacts a circumferential surface of the slitter roll on a surface where the resin film has been formed.