The invention relates to a sandwich composite component (1) for the interior of a passenger aircraft. One problem to be solved by the invention is that of proposing a cost-effectively produced sandwich composite component which is suitable for the interior of a passenger aircraft and fulfils current fire protection requirements. The layer structure of the sandwich composite component (1) according to the invention comprises: a core layer (10) made of polymer foam; a reinforcing layer (20) comprising fiber composite material; and in addition at least one functional layer (50); wherein said layers of the layer structure are integrally bonded to each other, in particular by an adhesive bond. The fiber composite material of the reinforcing layer (20) comprises a woven or laid fabric made of reinforcing fibers and a polymer matrix, which has a higher density than the polymer foam of the core layer (10). Furthermore, the at least one functional layer (50) comprises a metal foil, in particular an aluminium foil, which has a thinner layer thickness than the reinforcing layer (20).

A method for manufacturing an integrated hull by using 3D structure type fiber clothes and 3D vacuum infusion process includes: sequentially stacking at least one first fiber cloth, at least one core material and at least one second fiber cloth on a mold; deploying structural materials on the second fiber cloth; stacking the third fiber clothes to cover the structure materials and a part of the second fiber cloth, whereby the first fiber cloth, the core material, the second fiber cloth and the third fiber clothes are formed to a lamination; determining a pipe arrangement of vacuum pipes and first and second resin pipes; deploying a vacuum bag on the lamination and covering the first and second resin pipes and the vacuum pipe; executing the 3D vacuum infusion process; curing the resin; and executing a mold release process to complete an integrated hull.

A fiber-reinforced composite blank for a fiber-reinforced composite component, in particular for a fiber-reinforced composite component of a wind turbine, comprising a layered construction with a form core consisting of or comprising a form core material, and a fiber layer adjoining the form core, said fiber layer consisting of or comprising a fiber layer material, and a plurality of reinforcing rods introduced into the form core and consisting of or comprising a reinforcing material, wherein the reinforcing material has a higher stiffness than the form core material. In this arrangement, the plurality of reinforcing rods is introduced into the form core at an angle to a form core plane. Furthermore, at least one reinforcing rod of the plurality of reinforcing rods is introduced into the form core at an angle to a direction orthogonal to the form core plane.

A deformable auxetic structure for absorbing energy of an impact that comprises a plurality of interconnected adjoining tridimensional auxetic cells where each tridimensional auxetic cell comprises at least one surface element and a plurality of legs extending from the surface, the plurality of legs and the surface element being configured such that the sectional cut of the structure in at least two planes perpendicular to the surface element follows an auxetic pattern.

A composite laminate structure includes a cellular core and a first laminate layer coupled to the cellular core. The first laminate layer includes a first thermoplastic layer and a first fiber-reinforced polymer layer, where a first surface of the first fiber-reinforced polymer layer is thermally consolidated to a second surface of the first thermoplastic layer. A first surface of the first thermoplastic layer is directly in contact with and bound to a first surface of the cellular core by temperature reduction of the first thermoplastic layer below a glass transition temperature of the first thermoplastic layer while the cellular core is pressed against the first thermoplastic layer when the first thermoplastic layer is above the glass transition temperature of the first thermoplastic layer and the cellular core is below a temperature where materials of the cellular core flow or degrade.

A co-curable thermoset acoustic liner and method of forming the same includes a sound attenuating core having a plurality of core cells. An inner face sheet having a plurality of face sheet apertures is coupled to the core by an inner thermoset adhesive sheet, which has a plurality of adhesive sheet apertures. Each of the plurality of adhesive sheet apertures is aligned within a corresponding one of the plurality of face sheet apertures so that the plurality of core cells are placed in fluid communication with airflow over the inner face sheet to create a Single Degree of Freedom (SDOF) acoustic liner.

A system and method for primarily erecting curvilinear buildings using a plurality of interconnected structural tubes/sandwich panels is provided. Fabricating structural tubing comprises: connecting a fibrous and flexible lining to an inner surface of a flexible outer membrane, wherein the lining is saturated in a curable material that forms into a solid foam material when cured; and curing the curable material. Fabricating a sandwich panel comprises: connecting a first fibrous and flexible lining to an inner surface of a first flexible outer membrane, wherein the first lining is saturated in a curable material that forms into a solid foam when cured; connecting a second fibrous and flexible lining to an inner surface of a second flexible outer membrane, wherein the second lining is saturated in a curable material that forms into a solid foam when cured; and curing the curable material of the first lining and second linings.

A method of fabricating a panel includes laying up a first laminate on a tooling surface, laying a first layer of thermoplastic on an inner surface of the first laminate, laying a large cell carbon core on the first layer of thermoplastic, laying a second layer of thermoplastic across the large cell carbon core, laying a second laminate on the second layer of thermoplastic, creating a sealed core pocket by bonding the edges of the first and second layers of the thermoplastic surrounding a perimeter of the core, increasing pressure within the core pocket, increasing pressure on the outer surface of the second laminate, heating the panel to a desired curing temperature, and maintaining the increased pressures and temperature for a desired curing duration.

A panel includes a corrugated base with base corrugations configured from first base segments and second base segments. A first of the base corrugations includes a first of the first base segments and a first of the second base segments that is non-parallel to the first of the first base segments. The first of the base corrugations forms a first channel that extends laterally between and longitudinally along the first of the first base segments and the first of the second base segments. A corrugated stringer includes a plurality of stringer corrugations arranged longitudinally along and within the first channel. The stringer corrugations are configured from first stringer segments and second stringer segments. A first of the stringer corrugations includes a first of the first stringer segments and a first of the second stringer segments that is non-parallel to the first of the first stringer segments.

Radius fillers for composite structures, composite structures that include the radius fillers, and systems and methods of forming the radius fillers. The systems and methods may be configured to create a pre-form that may be utilized to form a radius filler and/or to create a radius filler from the pre-form. The systems may include an apparatus configured to form the pre-form for the radius filler. This apparatus includes a composite tape source, a pre-forming structure, and a drive mechanism. The systems also may include an apparatus configured to form the radius filler. This apparatus includes a pre-form supply, a first radius filler die, a second radius filler die, and a die selection structure.