35 results about "Cross ply" patented technology

The present invention relates to polyethylene material that has a plurality of unidirectionally oriented polyethylene monolayers cross-plied and compressed at an angle to one another, each polyethylene monolayer composed of ultra high molecular weight polyethylene and essentially devoid of resins. The present invention further relates to ballistic resistant articles that include or incorporate the inventive polyethylene material and to methods of preparing the material and articles incorporating same.

A two-ply flooring plank is disclosed having two layers or “plies” with a bottom layer having a grain that runs generally transverse to a top layer (i.e., “cross-ply”) to provide dimensional stability to the plank. The bottom layer includes a number of strips secured to the bottom of the top layer. The bottom layer strips are also placed with gaps between the individual strips of the second layer to allow flexibility of the flooring plank, which allows the flooring to more easily conform to irregularities in a subfloor upon which the flooring plank is mounted.

Flexible ballistic resistant composite material that has improved resistance to pick-up of water and other liquids, the composite material comprising a plurality of non-woven fibrous layers. The fibrous layers are formed from a network of high tenacity fibers (aramid fibers, extended chain polyethylene fibers and/or rigid rod fibers). The fibers are embedded in a matrix of a thermoplastic polyurethane resin. Preferably, at least two adjacent fiber layers are oriented in a cross-ply arrangement with respect to each other. Flexible armor, such as body vests, are provided which are formed at least in part from the flexible composite material.

A low CTE metal-ceramic composite material featuring carbon fibers reinforcing a matrix featuring silicon metal or silicon alloy. The fibers have a low coefficient of thermal expansion (CTE) in the axial direction, and preferably negative. The principles of making Si/SiC composites can be adapted to produce the instant Si matrix composites. The CTE of the composite body depends not only upon the relative CTE's of the fibers and matrix, and their relative amounts (e.g., loadings), but also upon the relative elastic moduli of the fibers and matrix. Thus, Si/SiC matrices produced by a reaction-bonding process inherently possess low CTE, but the instant inventors prefer to make such composites having relatively large fractions of unreacted silicon, thereby driving composite CTE lower still. Here, the carbon fibers are protected from reaction with the silicon infiltrant with one or more materials disposed between the fibers and the infiltrant. Providing at least a degree of toughness or impact resistance can also be realized in these composites. Laminates produce Isotropic or quasi-isotropic properties in the composite body can be realized by, for example, providing the fibers in the form of cross-plied laminates featuring the fibers in parallel or woven arrays.

A ballistic-resistant molded article having a sandwich-type structure including two outer portions of a first high modulus material surrounding an inner portion of a second high modulus material. The outer portions are comprised of a plurality of interleaved layers of adhesive coated cross-plied non-fibrous ultra high molecular weight polyethylene tape. The inner portion is comprised of a plurality of interleaved layers of high modulus cross-plied fibers embedded in resin. The stack of interleaved layers is compressed at high temperature and pressure to form a hybrid sandwich ballistic-resistant molded article that includes a mix of high modulus materials. It has been found that ballistic resistance is higher for the hybrid structure than for a monolithic structure of comparable areal density.

A structure comprising a plurality of plies of fibre-reinforced composite material, each ply having a ply orientation defined by a principal stiffness direction of the ply. The structure has a first region and a second region, each region comprising N1 primary plies, N4 cross plies with a ply orientation substantially perpendicular to the primary plies, N2 positive-angled bias plies with a ply orientation at a positive acute angle to the primary plies, and N3 negative-angled bias plies with a ply orientation substantially perpendicular to the positive-angled bias plies. The ply orientation of the primary plies in each region is more closely aligned with a primary axis of the structure than the cross plies or the bias plies. N1=N4 in the first region but not in the second N region, and N2=N3 in the second region but not in the first region. In each of the two regions, one ply set is balanced and the other ply set is un-balanced. This provides a compromise between the advantages of using un-balanced ply sets, for instance to provide bending torsion coupling, and the disadvantage that un-balanced ply sets can introduce thermally induced distortion during manufacture.

This technology relates materials that are stab, spike and ballistic resistant and to stab, spike and ballistic resistant composite articles incorporating uniaxially oriented, non-woven fabrics. A fabric layer having a non-uniform areal density is formed having thick areas and thin areas, the thick areas having a greater filament/tape concentration compared to the thin areas. In said thick areas, agglomerated tapes/filaments will protrude from the fabric layer surface. Additional layers are then adjoined with the non-uniform layer to form a panel that has stab, spike and ballistic resistance, with protrusions at least partially spacing the additional layers from full, direct contact with the surface of the non-uniform fabric layer to thereby enhance flexibility and stab, spike and ballistic resistance of the whole.

An unconsolidated impact and penetration resistant laminate comprises a plurality of cross-plied sheets, each cross-plied sheet further comprising (i) first and second layers of fibrous or non-fibrous ultra-high molecular weight polyethylene and (ii) first and second layers of thermoplastic adhesive, each adhesive layer having a basis weight of no greater than 5 gsm, wherein

• • (a) the layers of polyethylene and thermoplastic adhesive alternate within the sheet,
  • (b) at least 50 percent of the polyethylene layers are arranged such that the orientation of the first polyethylene layer is offset with respect to the orientation of the second polyethylene layer, and
  • (c) the plurality of cross-plied sheets form a stack that, when subjected to compaction at a pressure of 255 bar and a temperature of 132 degrees C., will not suffer a pressure loss greater than 8 bar within the first two minutes as measured by Test Method B.

The invention discloses a method for positioning transverse cracks of a carbon fiber composite material by using a chirp grating, which comprises the following steps of: (1) manufacturing a carbon fiber composite material cross-ply laminate with the stacking sequence of [0-degree 2/90-degree 4/0-degree 2], and embedding a chirp grating sensor into a 0-degree layer the carbon fiber composite material cross-ply laminate, wherein the chirp grating sensor is adjacent to a 90-degree layer; (2) under a condition with a constant temperature, using an optical fiber sensing analyzer to monitor a chirp grating reflection spectrum of a carbon fiber composite material test piece in a quasistatic tensile test; and (3) adjusting the length of the chirp grating to be accordant with a bandwidth phase of the chirp grating reflection spectrum before embedding in a coordinate system to ensure that a wavelength position corresponding to a point with decreased light intensity and a grating position corresponding to the wavelength in the chirp grating reflection spectrum are the positions where the transverse cracks are generated in the 90-degre layer of the composite material at that time. The method is simple, has a low cost, and can detect the transverse cracks in the carbon fiber composite material in real time.

The invention relates to a method for reducing deformation of a U-shaped composite part. The method comprises the following steps: a, making a continuous fiber sample part according to the layer lay-up design of a target part, and measuring the U-shaped opening dimension K1 of the continuous fiber sample part; b, making a satin fabric sample part after completely replacing the cross-ply layers in the layer lay-up design with satin fabric, and measuring the U-shaped opening dimension K2 of the satin fabric sample part; c, calculating the layer number Q of the satin fabric after correction; and d, making a U-shaped part after correction according to the rules that the number of the cross-ply layers of the satin fabric is Q and the number of the continuous fiber cross-ply layers is N-Q. According to the method for reducing deformation of the U-shaped composite part, the die surface can be obtained without long-time complicated and difficult calculation, making a new die after carrying out additional finite element calculation is not needed, and meanwhile repeated die repairing is also not needed.

A system for fabrication of an aerospace structure incorporates a mold having a surface and at least one unidirectional SFL head adapted to lay down a plurality of collimated tows in a predetermined laminated pattern on the mold surface to produce a fuselage skin. At least one cross plied laminate SFL head is adapted to lay down a cross plied laminate base interface on the fuselage skin to establish a lattice rib shape for each of a plurality of lattice ribs. The cross plied laminate SFL head has a band placement head steerable to avoid structural design features and to maintain spacing from adjacent steered lattice ribs. The unidirectional SFL head is further adapted to lay down a plurality of collimated tows on the base interface of each of the plurality of lattice ribs for a first plurality of unidirectional tow plies in each lattice rib. The unidirectional SFL head has a fiber placement head steerable to match the lattice rib shape to avoid structural design features and to maintain spacing from adjacent steered lattice ribs.

A ceramic matrix composite (CMC) component and method of fabrication including a plurality of counterflow elongated functional features. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies forming a densified body and a plurality of elongated functional features formed therein the densified body. Each of the plurality of functional features is configured longitudinally extending and in alignment with the plurality of ceramic matrix composite plies. Each of the plurality of elongated functional features includes an inlet configured in cross-ply configuration. The plurality of elongated functional features are configured to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The plurality of functional features are configured in alternating flow configuration.