A composite stiffener for a stiffener reinforced panel is disclosed. The stiffener has a longitudinal direction and a run-out region which terminates at an end of the stiffener. The stiffener also has a constant section region inboard of the run-out region in the longitudinal direction and having a constant cross section transverse to the longitudinal direction with a crown between adjacent foot portions. The run-out region has a changing cross section transverse to the longitudinal direction with a crown between adjacent foot portions and the crown reduces in height towards the end of the stiffener forming a ramp. The composite stiffener includes a number of blankets of non-crimp fabric layers.

Provided is a method for producing a fiber-reinforced plastic having high mechanical properties and high productivity during molding of a complicated shape. A method for producing a fiber-reinforced plastic using a sheet substrate A is provided, the sheet substrate A being a substrate including one or more sheets of incised prepreg a, the incised prepreg a being a prepreg including unidirectionally oriented reinforcing fibers and a resin and having a plurality of incisions dividing the reinforcing fibers formed in the prepreg, wherein the method for producing a fiber-reinforced plastic includes a placement step (A) of placing a plurality of sheet substrates A in a mold such that each of the sheet substrates A forms an overlapping portion in which the sheet substrate A overlaps one or more other sheet substrates A and a non-overlapping portion in which the sheet substrate A does not overlap any other sheet substrates A, and a molding step of heating and pressing the plurality of sheet substrates A, and the total area of the overlapping portion and the non-overlapping portion is 50 to 100% relative to the area of a mold surface.

A fiber-reinforced member includes: a base member having a tubular region with an outer circumferential surface extending along and substantially in parallel with an axial direction; and a fiber-reinforced resin layer constituted of a tow prepreg wound in an overlapping manner to cover the outer circumferential surface of the base member along a predetermined direction crossing the axial direction when viewed in a radial direction of the base member, the tow prepreg serving as a widened tape-like member. The tape-like member constituting the fiber-reinforced resin layer has a portion having a fiber line extending along a direction crossing the predetermined direction. A size of a width of the tape-like member constituting the fiber-reinforced resin layer is not less than 100 times and not more than 400 times as large as a size of a thickness of the tape-like member constituting the fiber-reinforced resin layer in the radial direction.

A device for producing textile planar structures formed of a plurality of portions deposited beside one another of fiber rovings. A supply device provides a fiber rovings at a transfer installation. A plurality of path guiding rails are disposed beside one another and above the depositing face. A gripper unit and a cutting unit are disposed on each path guiding rail. Each gripper unit and each cutting unit is movable and positionable along the path guiding rail independently of the gripper units and cutting units of the other path guiding rails. The gripper units grab the fiber roving from the transfer installation and move their free end to a desired terminal position. The cutting units severs the rovings at a cutting position. The gripper units and the cutting units have a downholder for pressing the fiber roving against the depositing face.

A composite structure having at least one radially extending part is provided. The composite structure is formed with ply layers. At least one of the ply layers used to form the radially extending part has fibers oriented at an angle offset from an edge of the at least one ply layer.

An airfoil member can have a root end, a tip end, a leading edge, and a trailing edge. The airfoil member can include an upper skin, a lower skin, and a composite core member having a plurality of cells, an upper surface network of the cells can be bonded to the upper skin, a lower surface network of the cells can be bonded to the lower skin. The composite core can have a septum layer embedded in the cells that form the composite core, the septum layer being configured to provide tailored characteristics of the airfoil member.

A method of manufacturing a gas tank comprises: a step (a) of preparing a liner having a hollow cylindrical shape; a step (b) of forming a first layer by winding a first fiber bundle impregnated with resin around the liner; a step (c) of forming a second layer by winding a second fiber bundle impregnated with resin around the liner with the wound first fiber bundle in such a manner that portions of the second fiber bundle overlap each other in a direction parallel to a center axis of the liner; a step (d) of causing a section where the portions of the second fiber bundle overlap each other to get into the first layer; and a step (e) of curing the resin.

The invention relates to a method for manufacturing a hoisting rope, comprising the steps of providing a plurality of elongated composite members, which composite members are made of composite material comprising reinforcing fibers in polymer matrix; and arranging the composite members to form an elongated row of parallel composite members, which row has a longitudingal direction, a thickness direction and a width direction, and in which row the composite members are positioned side by side such that they are parallel to each other, and spaced apart from each other in width direction of the row; and directing plasma treatment on the outer surface of the composite members; and embedding the composite members in fluid polymer material; and solidifying the polymer material wherein the composite members are embedded. The invention relates also to a hoisting rope obtained with the method and an elevator comprising the hoisting rope.

A structural component has a main body formed of a fibre composite material, a plurality of first reinforcement parts and a plurality of second reinforcement parts, wherein the main body is formed as a domed body having a peripheral edge and a vertex, wherein the first reinforcement parts are connected to the main body and in each case have a concave curvature course in relation to a first plane, and wherein the second reinforcement parts are connected to the main body and also have a concave curvature course in each case in relation to a second plane.

A method for forming fiber-reinforced composite parts via compression molding, particularly useful for forming parts that include off-axis, out-of-plane, or small, intricate features. In accordance with the method, non-flowing continuous fiber bundles and flowing continuous fiber bundles are placed in a mold, wherein the flowing continuous fiber bundles are disposed proximal to a minor feature. The non-flowing bundle has a length about equal to the length of a major feature of the mold. The flowing bundle has a length that is somewhat longer than the length of the minor feature. Under heat and pressure, resin softens and fibers from the flowing continuous fiber bundles flow into the minor feature.