A process for producing a thermoplastic composite pipe, where the process includes: a) providing a tubular liner having a wall containing a thermoplastic polymer A in the region of the outer surface; b) providing a tape containing reinforcing fibres in a matrix containing a thermoplastic polymer B, where polymer A and polymer B are different; c) applying a film or a composite which is produced in d) and is composed of a film and a tape provided in step b) to the tubular liner, with melting of the outer surface of the liner and of the contact surface of the film either beforehand, simultaneously or thereafter, d) applying the tape provided in b) to the outer surface of the film, with melting of the outer surface of the film applied and of the contact surface of the tape either beforehand, simultaneously or thereafter,
where the surface of the film which is brought into contact with the liner contains a moulding compound containing polymer A to an extent of at least 30% by weight, and the opposite surface of the film contains a moulding compound containing polymer B to an extent of at least 30% by weight.

A composite product substantially reduced the impact force imposed by hard impactor which travelled at the speed in the range of 400 m/s to 1400 m/s simultaneously damping the vibrations and shocks appeared therein is disclosed. At the same time it is light weight with the weight lower than that of 22 to 38 kg/m2 and is flexible to adopt the shape suitable for the end applications. A method of manufacturing the composite product of the invention is also disclosed.

The present invention provides: a surface-coated film which is for being integrally formed with a fiber impregnation resin; a surface-coated fiber-reinforced resin molded product; and a manufacturing method thereof. The surface-coated film has a base film B and an easily adhesive layer A provided on the base film B, wherein the base film B has a flat layer b2 and an easily molded layer b1 adjacent to the easily adhesive layer A, the thickness of the easily adhesive layer A is 30-250 nm, the thickness of the base film B is 50-500 μm, the easily molded layer b1 and the flat layer b2 satisfy both expression 1 of 3≤ratio (EHb2/EHb1) of storage elastic modulus EHb2 of flat layer b2 at 150° C. to storage elastic modulus EHb1 of easily molded layer b1 at 150° C., and expression 2 of 1,000 MPa≤storage elastic modulus ELb1 of easily molded layer b1 at 23° C.

A gasket is disclosed for use as an environmental seal between a first aircraft part having planer surface and a second aircraft part having a planer surface, the two planer parts spread apart and engaged with fasteners. The gasket, in some embodiments, is compressible between the planer surfaces. The gasket, in some embodiments, comprises a first tabular portion having tabular portion properties and having a first tabular thickness and a length and a width, the length and width much greater than the first tabular thickness; and a second tabular portion having tabular portion properties having a second tabular thickness, a length and width, the length and width much greater than the second tabular thickness; and a tabular skeleton. The first and second tabular portions and the skeleton are positioned parallel to one another. The skeleton is at least partly contacting one of the tabular portions. The first tabular portion and the second tabular portion differ in at least one tabular portion property.

A lightweight, flame-retardant, multilayered composite structure having at least the following components: a thermoplastic foam core having two opposing surfaces; a thermoplastic adhesive film on at least one of the opposing surfaces of the foam core, one or more composite layer(s) on each adhesive film. The composite layer(s) is/are composed of reinforcement fibers embedded in a thermoplastic polymer or thermoset resin matrix. Adhesive bonding is effectuated by the interleaving thermoplastic adhesive film interposed between the thermoplastic foam core and the adjacent composite layer. The thermoplastic adhesive film is formed of a thermoplastic polymer composition having a T.sub.g of at least 20° C. lower than the T.sub.g of the foam core material.

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.

A composite panel manufacturing process with interlocking connections. The method includes laying out the first sheet of pre-preg epoxy carbon fiber, upon a polished and released aluminum tool. A second sheet of epoxy fiberglass is laid out over the top side of the first sheet. Rigid structural foam is laid on top of the second sheet of epoxy fiberglass. A third sheet of pre-preg epoxy fiberglass is laid on top of the rigid structural foam. A fourth sheet of pre-preg epoxy carbon is laid on top of the third sheet of pre-preg epoxy fiberglass with heavy resin/top side out to form a plurality of panels. The plurality of panels are cured to form a multilayer panel. Core material is removed along one edge of a first multilayer panel to make a U-shaped channel having a base and parallel flanges. A grooved slot is cut along one edge of the next multilayer panel. The panels are joined at the corner using an adhesive.

A gasket is disclosed for use as an environmental seal between a first aircraft part having planer surface and a second aircraft part having a planer surface, the two planer parts spread apart and engaged with fasteners. The gasket, in some embodiments, is compressible between the planer surfaces. The gasket, in some embodiments, comprises a first tabular portion having tabular portion properties and having a first tabular thickness and a length and a width, the length and width much greater than the first tabular thickness; and a second tabular portion having tabular portion properties having a second tabular thickness, a length and width, the length and width much greater than the second tabular thickness; and a tabular skeleton. The first and second tabular portions and the skeleton are positioned parallel to one another. The skeleton is at least partly contacting one of the tabular portions. The first tabular portion and the second tabular portion differ in at least one tabular portion property.

A composite material body (10) includes a first material layer (20) and a second material layer (30) overlapping the first material layer (20). The first material layer (20) and the second material layer (30) are wound to form a flexible and circular rod. Impact absorption is effectively improved and impact resisting strength is enhanced because energy-absorber or damping material or its composition is attached into the composite material body (10). Technical characteristics, effects and objects of this invention are achieved thereby.

A turbomachine blade including a blade body made of fiber-reinforced organic matrix composite material, the blade body having a pressure side and a head provided with an apex; an erosion protection film which is made of a thermoplastic polymer and adhered to the blade body; a reinforcement layer which is made of a thermosetting polymer and positioned on the erosion protection film on the head of the blade.