A method of manufacturing a control cuff for a rotor blade of a hinge and bearingless rotor. The method comprises at least the steps of: manufacturing an outer shell, manufacturing a stiffener member by means of an automated process, inserting the stiffener member into the outer shell, and bonding the stiffener member to the outer shell.

An acoustic panel for an aircraft nacelle includes a cellular layer configured to trap noise, a backplate fixed to one surface of the cellular layer and a facesheet fixed to another, opposite, surface of the cellular layer. The facesheet includes a layer of a preimpregnated woven material containing weft yarns spaced apart from one another and warp yarns spaced apart from one another so that the facesheet exhibits openings between the yarns.

A carbon fiber prepreg is disclosed. The carbon fiber prepreg, exclusive of any additive scrims, comprises a multiple carbon fiber layers and resin layers in an integral form, characterized in that: for the carbon fiber prepreg at each standard unit of the carbon fiber prepreg (g/m.sup.2, indicating a weight percentage of the carbon fiber and the resin in the carbon fiber prepreg), the resin layers and the carbon fiber layers are both of multi-layer in a manner that each resin layer is impregnated with two adjacent carbon fiber layers so that the carbon fiber layers are able to be consolidated firmly for strengthening overall structure of the carbon fiber prepreg.

Laminar structures comprising a fiber reinforced layer bonded to an expandable filler containing layer to provide improved flexural stiffness to weight ratio at lower fiber loading; a process for the manufacture of the laminar structures in which the material are selected so that migration of the expandable filler into the fiber structure of the fiber reinforced layer as they expand is minimized or prevented.

A configuration and manufacturing method for a trailing edge of an aircraft airfoil, such as a control surface or a lifting surface is described. The trailing edge is formed and configured by upper and lower composite covers, which are stitched to each other with a metallic wire, such as the metallic wire is electrically in contact with upper and lower metallic meshes to provide electrical continuity between meshes. According to a method, upper and lower covers configuring the trailing edge, are stitched with the metallic wire before curing the covers, so that the metallic wire gets embedded within the composite material. A trailing edge for an aircraft airfoil, which is easy to manufacture and that at the same time fulfills aerodynamic, mechanical and electrical conductivity requirements is described.

A laminate blank includes at least one rigidifying layer and at least one comfort layer. The rigidifying layer includes a reinforcement preform and a resin. The layers are pressed to form the laminate blank.

Embodiments disclosed herein relate to polymer resins having a first thermoset and one or more additional components (e.g., a second thermoset and/or a thermoplastic), composite laminates including the same, methods of making and using the same, and composite laminate structures including the same.

One or more techniques and/or systems are disclosed for creating panels to simulate the real light tracing ability of wood fibers, and the light refractive properties of real wood figure. High light refractive man-made fibers can be molded into 3D figured panels which may then be filled with clear resin to magnify and to duplicate the light refractivity of wood figure. A protective backing material can be applied to the rear of the molded fiber panel, to provide a flat surface, and/or for adherence purposes. Rather, the 3D figured panels may also be machined into flat fiber panels to reveal a visual 3D surface that simulates the light refractivity of wood figure.

A thermoplastic bonded preform and method of manufacturing the preform are disclosed. The preform comprises a primary fiber comprising little or no sizing; a mechanical fiber; and a thermoplastic.

A yarn for reinforcing composite material includes carbon nanotubes. The yarn has also been treated to promote interaction with a resinous matrix.