The invention relates to a method for producing a fiber-plastic composite reference body for simulating delamination for the nondestructive testing of FPC components, in particular aircraft components, comprising the following steps: i. producing a first insert by a. arranging a first FPC layer; b. forming a recess in the first FPC layer; c. procuring the first FPC layer, in order to obtain the first insert; ii. producing a second insert by a. arranging a second FPC layer; b. pre-curing the second FPC layer, in order to obtain the second insert; iii. providing at least one first FPC layer and at least one second FPC layer with a first clearance and a second clearance; iv. inserting the first insert and the second insert into the respective clearance of the corresponding FPC layer; v. curing the arrangement, a delamination being simulated at the recess of the first insert.

In a metal-fiber reinforced plastic (FRP) composite, the FRP and the metal member are bonded together, so internal stress (thermal stress) is generated due to the misfit of coefficients of thermal expansion of the metal member and the FRP. Not only does the binder layer peel off and the mechanical properties of the FRP cannot be obtained, but also defects in appearance (surface strain) occur. Therefore, the technical problem is to secure the mechanical properties as a composite while easing the internal stress and keeping surface strain from being generated. The metal-fiber reinforced plastic (FRP) composite according to the present invention solves the technical problem by sandwiching an FRP between two metal members and not having at least one of the metal members joined (bonded) with the FRP. Further, it is possible to arrange an intermediate member between the other metal member and the FRP and sandwich the FRP between the two metal members through the intermediate member.

Stiffened skin panels comprise alternating truss core portions and solid laminate portions sandwiched between inner and outer facesheets, all formed from a fiber reinforced thermoplastic. The components of the panels are co-consolidated using induction heating. The panels are stiffened with spars fastened to the solid laminate portions.

In a first aspect, the disclosure provides; a composite laminate. The laminate is made of: a first exterior layer comprising a biocompatible material; a second exterior layer comprising a biocompatible material; and a first inner layer comprising biocompatible threads running parallel to each other and oriented at zero degrees. The layers are laminated together. The disclosure further provides; a method for creating a biocompatible composite laminate. The method includes laying biocompatible threads parallel to one another to create a first middle thread layer on a first biocompatible material exterior layer, and placing a second biocompatible exterior material layer over the parallel biocompatible threads. The laminate is heated and compressed to bond the layers together.

A composite wheel assembly and method of fabricating the same is provided. The wheel assembly includes a composite wheel rim, a wheel center, and a plurality of attachment fasteners for attaching the wheel center to the wheel rim. The wheel rim includes a plurality of attachment inserts that are configured to selectively engage with respective attachment fasteners. Each attachment insert is encapsulated by a plurality of composite layers of the wheel rim or is otherwise secured to the wheel rim. The attachment inserts extend from and/or are positioned within a drop well region of the wheel rim. The method of fabricating the wheel assembly includes forming first and second preforms and positioning the same onto a mold assembly. The method further includes positioning the attachment inserts between the first and second preforms such that the attachment inserts are secured therebetween.

A composite wheel assembly and method of fabricating the same is provided. The wheel assembly includes a composite wheel rim, a wheel center, and a plurality of attachment fasteners for attaching the wheel center to the wheel rim. The wheel rim includes a plurality of attachment inserts that are configured to selectively engage with respective attachment fasteners. Each attachment insert is encapsulated by a plurality of composite layers of the wheel rim or is otherwise secured to the wheel rim. The attachment inserts extend from and/or are positioned within a drop well region of the wheel rim. The method of fabricating the wheel assembly includes forming first and second preforms and positioning the same onto a mold assembly. The method further includes positioning the attachment inserts between the first and second preforms such that the attachment inserts are secured therebetween.

A composite sandwich panel comprises a first composite skin, a second composite skin, a hollow cell core between the first composite skin and the second composite skin, and a first over-crush edge region with a first edge. The first edge has a first thickness at least 40% less than a nominal thickness of the composite sandwich panel. The first over-crush edge region has a length of at least 0.25 inches over which a thickness of the composite sandwich panel decreases.

The present invention relates to the use of a single layer fluoropolymer film selected from ethylene tetrafluoroethylene film and polytetrafluoroethylene film as release film in a method for shaping a composite material.

A method for manufacturing a quadrangular shell having five faces and non-developable trihedral connectors between the faces. Plies having continuous fibers are cut to cover the five faces of the shell outside of the trihedral connector zones. Four connector components consolidated in the shape of the trihedral connectors are obtained. Each of the components includes an integration zone between the plies. Plies are positioned and laid up. The four consolidated components are inserted in the trihedral connection zones by inserting the integration zones between two plies to form an assembly obtain a preform. The preform is placed in a tool and the consolidation of the stack of fibrous plies is performed by subjecting the assembly to a predetermined pressure/temperature cycle.

A method of forming a cored composite laminate, the method including forming a first recess in a first coupling surface of a first layer of the cored composite laminate, forming a second recess in a second coupling surface of a second layer of the cored composite laminate so that when the first layer of the cored composite laminate and the second layer of the cored composite laminate are coupled, the first recess and the second recess form a cavity through the cored composite laminate, and disposing a shape memory alloy member in die cavity, so that the shape memory alloy member supports the cored composite laminate during curing of the cored composite laminate.