Compaction systems and methods of compacting components are provided. In one aspect, a laminate of a component can be laid up on a tool of a compaction system. The laminate defines a cavity. A noodle is positioned relative to or in the cavity. A noodle ring is then positioned relative to the noodle. For instance, the noodle ring can be placed over the noodle. A cross section of the noodle ring can be shaped complementary to a cross section of the noodle. A plunger of the compaction system is moved so that it engages the noodle ring. Particularly, the plunger is moved in such a way that a force is applied on the noodle ring so that the noodle ring compacts the noodle into the cavity.

Aspects of the present disclosure include a pickleball paddle that is formed using a plastic or composite molded material. A composite material is wrapped around a center and placed in a mold to form a paddle frame or arranged around a paddle frame. In some embodiments, additional composite material is wrapped at specific positions to tune the balance point and rebound characteristics of the finished paddle The mold is heated to cure the composite material within the mold cavity. Face shells are then added to complete the paddle.

The present invention relates to a method of manufacturing a blade shell member for a wind turbine blade. The method comprising providing a blade mould for the blade shell member and arranging a number of fibre-reinforced layers on a blade moulding surface of the blade mould. A first primer layer is applied on top of the fibre-reinforced layers, at a pre-determined spar cap region. Furthermore, a pre-manufactured spar cap having an upper surface, a lower surface, a first side surface, a second side surface, a first end surface and a second end surface is arranged in the pre-manufactured spar cap on the spar cap region, such that the lower surface of the pre-manufactured spar cap contacts the first primer layer arranged on the spar cap region. A second primer layer is also applied to the upper surface of the pre-manufactured spar cap before the step of infusing the blade moulding cavity with resin and curing it. The present invention further relates to a method of manufacturing a wind turbine blade, comprising the steps of manufacturing a pressure side shell half and a suction side shell half over substantially the entire length of the wind turbine blade and subsequently closing and joining the shell halves for obtaining a closed shell.

A mold assembly for manufacturing a composite part with a stiffener, the mold assembly includes a bottom mold configured to form a first surface of the composite part, wherein the bottom mold has at least one elongated recess configured to form a stiffener in the composite part; a feeder unit having a shape corresponding to the at least one elongated recess, wherein the feeder unit is configured to fit at least partially into the at least one elongated recess; and a top mold configured to form a second surface of the composite part opposite to the first surface. Also a method of manufacturing a composite part using such a mold assembly, which includes draping a flat laminate over the bottom mold and pushing portions of the laminate into the at least one elongated recess.

A reinforcing structure for a wind turbine blade is in the form of an elongate stack of layers of pultruded fibrous composite strips supported within a U-shaped channel. The length of each layer is slightly different to create a taper at the ends of the stack; the centre of the stack has five layers, and each end has a single layer. The ends of each layer are chamfered, and the stack is coated with a thin flexible pultruded fibrous composite strip extending the full length of the stack. The reinforcing structure extends along a curved path within the outer shell of the blade. The regions of the outer shell of the blade on either side of the reinforcing structure are filled with structural foam, and the reinforcing structure and the foam are both sandwiched between an inner skin and an outer skin.

A method of manufacturing a composite (e.g. fibre-reinforced polymer) connector for a fluid transfer conduit includes: providing a tubular mandrel which extends substantially parallel to a central axis C; providing a former on the tubular mandrel which extends substantially perpendicular to the central axis C; and winding continuous fibre reinforcement, impregnated with a thermosetting polymer, around the mandrel to form a tubular hub portion which extends substantially parallel to the central axis C and over the former to form a flange portion 308 which extends from the hub portion at an angle to the central axis C. Winding the continuous fibre reinforcement over the former includes passing the continuous fibre reinforcement across a first surface of the former that is substantially perpendicular to the central axis C and across a second surface of the former such that the former is encapsulated as a core for the flange portion.

A shaped preform component (200) for a face portion (104) of a composite wheel (100), the shaped preform (200) having a hub (206) that extends around a central axis (Y), the shaped preform component (200) being formed from a cured composite fibre material having a compressibility of <2% volumetric under moulding conditions of 50 bar hydrostatic pressure and a temperature of 60 to 200° C.

A cover for a cushion includes a first panel, a second panel, and a primary receptacle defined between the first panel and the second panel. The primary receptacle may receive a primary cushioning element, such as a pillow, a pillow insert, or a fill material. At least one of the first panel and the second panel includes a secondary cushioning element. The secondary cushioning element may be defined from a compressible, resilient elastomeric material that defines a plurality of thin interconnected walls that in turn define an array of open cells or columns. Each cell or column may have a hexagonal shape, imparting the array of open cells or columns with a honeycomb appearance. Methods for assembling a primary cushioning element with such a cover are also disclosed.

A propeller blade comprises a fibre reinforced blade structure spar having a blade retention section formed at one end thereof, and at least one metallic formation spray deposited onto said blade retention section.

A method for manufacturing an overhead storage compartment for an aircraft cabin, including providing a shell part extending between a first end and a second end, wherein the shell part has a first edge at the first end and a second edge at the second end. A first end wall and a second end wall are provided. The shell part and the first and second end walls are assembled, wherein the first edge is attached to the first end wall and the second edge is attached to the second end wall, such that the shell part, the first end wall and the second end wall together surround an interior space. An object, to provide a simple and fast method for manufacturing an overhead storage compartment, wherein possibly little handwork is required, is achieved in that the first end wall and/or the second end wall include an undirected long fiber reinforced plastic material.