This relates to a composite structural element, in particular a rib or a spar, specifically for use in a torsion box of an aircraft structure such as a vertical tailplane, wherein the structural element defines a coordinate system with a first axis “a” wherein the structural element comprises a substantially planar main section defining a coordinate system with a first axis “a” extending along the longitudinal axis “L” of the structural element and a second axis “b” extending perpendicular to said longitudinal axis “L” within the planar main section and defining an angle of +90° with the first axis “a”, wherein the structural element contains a lay-up of single plies consisting of a fiber-reinforced composite material with a substantially unidirectional fiber orientation.

A structure for use in industrial fabrics such as paper machine clothing and engineered fabrics. The structure is a bicomponent extruded elastomeric netting or mesh having a high degree of both compressibility under an applied normal load and excellent recovery (resiliency or spring back) upon removal of that load.

A structure for use in industrial fabrics such as paper machine clothing and engineered fabrics. The structure is a bicomponent extruded elastomeric netting or mesh having a high degree of both compressibility under an applied normal load and excellent recovery (resiliency or spring back) upon removal of that load.

In a composite material structure, which is configured as a fiber-reinforced plastic composite material extending in one direction and having a plurality of holes defined at intervals in a row in the one direction and which is subjected to a tensile load and/or a compressive load in the one direction, a peripheral region around the holes comprises a first area obtained by bending composite material, which is reinforced using continuous fibers that have been made even in a longitudinal direction, so that a center line of a width of the composite material weaves between adjacent holes and zigzags in the one direction. A tensile rigidity and/or a compressive rigidity in the one direction of the peripheral region around the holes is lower than a tensile rigidity and/or a compressive rigidity in the one direction of other regions that surround the peripheral region.

A hybrid carbon/fiberglass structural component or beam for an aircraft is constructed with layers of strips of glass fibers interspersed with layers of strips of unidirectional carbon fibers where the carbon fibers are oriented only in alignment with or along the longitudinal direction of the length of the beam thereby adding strength and stiffness to the beam while reducing weight and manufacturing costs.

A hybrid carbon/fiberglass structural component or beam for an aircraft is constructed with layers of strips of glass fibers interspersed with layers of strips of unidirectional carbon fibers where the carbon fibers are oriented only in alignment with or along the longitudinal direction of the length of the beam thereby adding strength and stiffness to the beam while reducing weight and manufacturing costs.

A structure for use in industrial fabrics such as paper machine clothing and engineered fabrics. The structure is a bicomponent extruded elastomeric netting or mesh having a high degree of both compressibility under an applied normal load and excellent recovery (resiliency or spring back) upon removal of that load.

The invention relates to a multilayered material sheet comprising a consolidated stack of unidirectional monolayers of drawn polymer. The draw direction of two subsequent monolayers in the stack differs. Moreover the strength to thickness ratio of at least one monolayer is larger than 4.5.10.sup.13 N/m.sup.3. The invention also relates to a ballistic resistant article comprising the multilayered material sheet and to a process for the preparation of the ballistic resistant article.

The invention relates to a multilayered material sheet comprising a consolidated stack of unidirection monolayers of drawn ultra high molecular weight polyolefine. The draw direction of two subsequent monolayers in the stack differs. Moreover the thickness of at least one monolayer does not exceed 50 m, and the strength of at least one monolayer is comprised between 1.2 GPa and 3 GPa. The invention also relates to a ballistic resistant article comprising the multilayered material sheet and to a process for the preparation of the ballistic resistant article.

A composite material made of multiple filament bands is disclosed. The filament bands are wound to create a composite material. The filament bands may be impregnated with a solid or semi-solid resin. The filament bands are wound in multiple orientations to form a sheet of composite material. Additionally, the composite material may be made to have a varying number of layer and fiber orientations throughout the sheet of composite material. In another embodiment, a composite component requiring multiple layers and fiber orientations may be substantially manufactured during a filament winding process.