An airframe assembly for an aircraft. The airframe assembly includes a first airframe member having a first skin, a second skin, a large cell core joined between the first and second skins and a solid insert having a side surface. The solid insert is joined between the first and second skins such that at least a portion of the side surface is adjacent to the large cell core. The first skin has a first surface disposed opposite the solid insert. The airframe assembly also includes a second airframe member having a second surface. An adhesive joint is disposed between the first and second surfaces structurally bonding the first airframe member to the second airframe member such that the second airframe member is positioned opposite the solid insert.

A core stiffened panel includes first and second skins having a large cell core and a solid insert joined therebetween. The solid insert has a side surface at least a portion of which is adjacent to the large cell core and may be joined to the large cell core. The first skin, the second skin and the solid insert may be formed from composite materials such as carbon composite materials and preferably have generally matching coefficients of thermal expansion.

An airframe assembly for an aircraft includes a first airframe member having first and second skins with a large cell core and a solid insert joined therebetween. The solid insert has a side surface at least a portion of which is adjacent to the large cell core. The first airframe member has a first set of openings extending through the first skin, the solid insert and the second skin. The airframe assembly also includes a second airframe member having a second set of openings operable to be aligned with the first set of openings of the first airframe member. Each of a plurality of fasteners extends through one of the openings of the first set of openings and one of the openings of the second set of openings securably coupling the first airframe member to the second airframe member.

A method and apparatus for applying a force to an assembly comprising a layup mandrel and a composite part. The apparatus comprises a first gripper and a second gripper. The second gripper is spaced apart from the first gripper so as to define a space between the first and second grippers, the space configured to receive the assembly. An actuation system is positioned between the first and second grippers adjacent the space, the actuation system configured to separate the layup mandrel from the composite part by applying force.

A method and apparatus for applying a force to an assembly comprising a layup mandrel and a composite part. The apparatus comprises a first gripper and a second gripper. The second gripper is spaced apart from the first gripper so as to define a space between the first and second grippers, the space configured to receive the assembly. An actuation system is positioned between the first and second grippers adjacent the space, the actuation system configured to separate the layup mandrel from the composite part by applying force.

Provided herein are polymer matrix composites, articles including the polymer matrix composites, and methods of forming the polymer matrix composites. The polymer matrix composite includes a stitched composite and a hybrid barrier layer incorporated within the stitched composite, the hybrid barrier layer including a thin ply and a nanographene dispersed resin. The article includes a high-pressure composite cryogenic tank including the polymer matrix composite. The method includes positioning a dry thin ply between composite plies, stitching the composite plies to form a stitched preform, dispersing nanographene into the resin, and infusing the stitched preform with the modified resin.

A process for producing a component for an aircraft for the frame, e.g. formers and stringers. Aircraft are being increasingly constructed of polymeric fiber composite to reduce weight. Here, fiber composites were originally composed of thermoset polymer and carbon fibers. Thermoplastic fiber composites are increasingly a research focus. An example is poly(ether ether ketone). However, production of components of thermoplastic fiber composites is complex. An improved process for producing such components includes producing a sheet-like object with a thermoplastic fiber composite having a thermoplastic polymer material and reinforcing fibers embedded therein, forming the sheet-like object for a semifinished part, and solidification of the semifinished part to give the component. Components obtainable by this process are also disclosed.

An object of the present invention is to provide a prepreg and a laminate for producing a laminate suitable as a structural material, which have excellent joining strength and can be firmly integrated with another structural member by welding. The present invention provides a prepreg including the following structural components: [A] reinforcing fibers, [B] a thermosetting resin, and [C] a thermoplastic resin, wherein [A] has a surface free energy, measured by a Wilhelmy method, of 10 to 50 mJ/m.sup.2, [C] is present on a surface of the prepreg, and the reinforcing fibers [A] are present, which are included in a resin area including [B] and a resin area including [C] across an interface between the two resin areas.

A conveyor module, small fragments of which are detectable by X-ray and/or magnetic sensors, is formed from a compounded mixture of a polyketone resin, a ferrous metal powder, and, optionally, a barium sulfate powder. The ferrous metal powder is preferably 400 series stainless steel powder, or alternatively, a 300 series stainless steel powder, iron powder, or other iron alloy powder.

A protective braided sleeve and method of construction thereof is provided. The sleeve includes a seamless, circumferentially continuous, tubular braided wall having a cavity extending lengthwise along a central longitudinal axis between opposite ends. The wall includes a plurality of yarns braided with one another, with at least one or more of the yarns including a bicomponent yarn including a core and an outer adhesive sheath adapted to be selectively melted to bond the wall to an elongate member extending through the cavity.