| Hexcel Corporation Patent applications |
| Patent application number | Title | Published |
|---|
| 20120088864 | SOLVENT RESISTANCE OF EPOXY RESINS TOUGHENED WITH POLYETHERSULFONE - The solvent resistance of epoxy resins toughened with polyethersulfone is improved by using low molecular weight polyethersulfone. The resulting thermoplastic toughened epoxy resins are useful for making prepreg for aerospace applications. | 04-12-2012 |
| 20120088863 | SOLVENT RESISTANT THERMOPLASTIC TOUGHENED EPOXY - Thermoplastic toughened epoxy resin for use in making prepreg for aerospace applications. The resin includes an epoxy resin component comprising a tri functional epoxy resin and/or tetra functional epoxy, a thermoplastic component and 4,4′-Bis(p-aminophenoxy)biphenyl (BAPB) as the curing agent. The use of BAPB as a curative was found to increase the resistance of the cured resin to attack by solvents. | 04-12-2012 |
| 20120055006 | AEROSPACE ARTICLES MADE FROM QUASI-ISOTROPIC CHOPPED PREPREG - Quasi-isotropic chopped prepreg is used to make parts found in aerospace vehicles. Exemplary aerospace parts that are made using quasi-isotropic chopped prepreg include aircraft window frames, wing fairing supports, flange supports, frame gussets, rudder actuator brackets, shear ties, seat pedestals, cargo floor flange supports, storage bin fittings, antenna supports, torque tube pans, handle boxes, side guide fittings, wing box covers and intercostals. | 03-08-2012 |
| 20120040169 | MACHINABLE COMPOSITE MATERIAL - An assembly that includes a first part composed of a fibrous structure that includes fibers and a cured resin matrix. The fibrous structure has at least one surface and a layer that is located on the surface. The layer includes a discontinuous fiber composite that is composed of randomly oriented short fibers and a cured resin matrix wherein the layer has been machined to provide a machined surface. The assembly also includes a second part that is attached to the first part. The second part includes at least one surface that fits against the machined surface on the first part. | 02-16-2012 |
| 20120037449 | ACOUSTIC HONEYCOMB WITH PERFORATED SEPTUM CAPS - An acoustic structure that includes a honeycomb having cells in which septum caps are located. The septum caps are formed from sheets of flexible material that may be perforated before or after the material is inserted into the honeycomb. The flexible material is sufficiently flexible to allow folding into the shape of a septum cap. The flexible material is also sufficiently stiff to provide frictional engagement and locking of the septum cap to the honeycomb cell when the cap is inserted into the honeycomb during fabrication of the acoustic structure. An adhesive is applied to the septum caps after the caps have been inserted into the honeycomb cells to provide a permanent bond. | 02-16-2012 |
| 20120034090 | Helicopter Blade Mandrel With Roller Assembly - Methods and apparatus are provided for making a rotor blade spar from composite material wherein a multi-component mandrel is used to form the composite spar. The mandrel is made using a number of components that are assembled and held in place using a roller assembly. The roller assembly is removed after pre-cure lay up and compaction of the composite material. Once the roller assembly is removed, the remaining mandrel components can be separated from each other and easily removed from the spar. The mandrel components, including the roller assembly, can then be re-assembled and re-used to form additional composite spars. | 02-09-2012 |
| 20110262630 | Composite Materials With Improved Performance - A composite material comprising at least one polymeric resin and optionally at least one fibrous reinforcement where the polymeric resin comprises at least one difunctional epoxy resin and at least one epoxy resin with a functionality greater than two having at least one meta-substituted phenyl ring in its backbone. | 10-27-2011 |
| 20110259514 | Composite Material For Structural Applications - Composite material that contain epoxy resin which is toughened and strengthened with thermoplastic materials and a blend insoluble particles. The uncured matrix resins include an epoxy resin component, a soluble thermoplastic component, a curing agent and an insoluble particulate component composed of elastic particles and rigid particles. The uncured resin matrix is combined with a fibrous reinforcement and cured/molded to form composite materials that may be used for structural applications, such as primary structures in aircraft. | 10-27-2011 |
| 20110227249 | MOLD FOR USE IN MAKING COMPOSITE STRUCTURES - Machinable composite molds for use in molding composite structures. The mold includes a mold body having a tool surface that is shaped to provide the molded surface of the composite structure. The mold body is made up of at least one mold layer composed of a quasi-isotropic material composed of a plurality of randomly oriented fiber bundles or chips impregnated with a resin. The use of randomly oriented fiber chips allows post-cure machining of the mold body. | 09-22-2011 |
| 20110212292 | Thermoplastic-Toughened Cyanate Ester Resin Composites With Low Heat Release Properties - Composite materials that contain thermoplastic-toughened cyanate ester resins as the resin matrix. The composite materials exhibit low levels of heat release when burned. The matrix resins are composed of from 50 to 80 weight percent of a cyanate ester resin component. The matrix resin composition also includes from 10 to 40 weight percent of a thermoplastic blend that is composed of polyetherimide and polyamideimide. The epoxy resin composition further includes from 1 to 10 weight percent of a curative agent. The composite materials may be used for primary structures in aircraft and other load-bearing structures. | 09-01-2011 |
| 20110147670 | COMPOSITE MATERIALS WITH BLEND OF THERMOPLASTIC PARTICLES - Pre-impregnated composite material (prepreg) is provided that can be cured to form composite parts that have high levels of damage tolerance. The matrix resin includes a thermoplastic particle component that is a blend of particles that have a melting point above the curing temperature and particles that have a melting point at or below the curing temperature. | 06-23-2011 |
| 20110118386 | Prepreg Containing Epoxy Resin With Improved Flexural Properties - Prepreg that contains epoxy resin compositions that include an epoxy resin component and a curative powder comprising particles of 4,4′-diaminobenzanilide (DABA) wherein the size of the DABA particles is less than 100 microns and wherein the median particle size is below 20 microns. | 05-19-2011 |
| 20110073407 | ACOUSTIC SEPTUM CAP HONEYCOMB - An acoustic structure that includes a honeycomb having cells in which septum caps are located. The septum caps are formed from sheets of acoustic material and include a resonator portion and a flange portion. The flange portion has an anchoring surface that provides frictional engagement of the septum caps to the honeycomb cells when the caps are inserted into the honeycomb during fabrication of the acoustic structure. An adhesive is applied to the anchoring surface of the septum caps after the caps have been inserted into the honeycomb cells to provide a permanent bond. | 03-31-2011 |
| 20110064908 | METHOD OF MOLDING COMPLEX COMPOSITE PARTS USING PRE-PLIED MULTI-DIRECTIONAL CONTINUOUS FIBER LAMINATE - Layers of unidirectional (UD) fiber prepreg are formed into a pre-plied, multi-directional, continuous fiber laminate that is used as a molding compound to form three dimensional structures. Cut-outs from the laminate are slotted and folded along fold lines to provide near-net-shaped preforms that may be compression molded to form fiber-reinforced composite structures having complex shapes. | 03-17-2011 |
| 20110011975 | Aerospace articles made from quasi-isotropic chopped prepreg - Quasi-isotropic chopped prepreg is used to make parts found in aerospace vehicles. Exemplary aerospace parts that are made using quasi-isotropic chopped prepreg include aircraft window frames, wing fairing supports, flange supports, frame gussets, rudder actuator brackets, shear ties, seat pedestals, cargo floor flange supports, storage bin fittings, antenna supports, torque tube pans, handle boxes, side guide fittings, wing box covers and intercostals. | 01-20-2011 |
| 20100298468 | EPOXY RESINS WITH IMPROVED FLEXURAL PROPERTIES - Epoxy resin compositions that include an epoxy resin component and a curative powder comprising particles of 4,4′-diaminobenzanilide (DABA) wherein the size of the DABA particles is less than 100 microns and wherein the median particle size is below 20 microns. | 11-25-2010 |
| 20100276055 | Resin Compositions With High Thermoplastic Loading - Uncured thermosetting resins are loaded with relatively high amounts of solid thermoplastic resin particles to form a resin precursor. The resin precursor is heat treated so as to produce an uncured resin composition wherein the thermoplastic resin particles become substantially dissolved in the thermosetting resin without causing cure of the resin mixture. Heat treatment of highly loaded thermosetting resins in accordance with the present invention provides uncured resin compositions that are well suited for use in fabricating composite structures and particularly prepreg for use in lightning protection surface coatings. | 11-04-2010 |
| 20100239755 | COMPOSITE MATERIALS WITH BLEND OF THERMOPLASTIC PARTICLES - Pre-impregnated composite material (prepreg) is provided that can be cured to form composite parts that have high levels of damage tolerance. The matrix resin includes a thermoplastic particle component that is a blend of particles that have a melting point above the curing temperature and particles that have a melting point at or below the curing temperature. | 09-23-2010 |
| 20100232973 | HELICOPTER BLADE MANDREL - Methods and apparatus are provided for making a rotor blade spar from composite material wherein a multi-component mandrel is used to form the composite spar. The mandrel is made using a number of components, which are assembled to provide a structure that is sufficiently strong to maintain the spar shape during pre-cure lay up, compaction and curing of the composite material. The multiple components used to form the mandrel can be separated from each other and easily removed from the spar either before or after curing of the composite material. The mandrel components can then be re-assembled and re-used to form additional composite spars. | 09-16-2010 |
| 20100189988 | Prepreg With Integrated Multi-Dimensional Gas Venting Network - Composite prepreg including a gas venting network that allows multi-dimensional escape of gas from the prepreg during the curing process. Penetrable barriers are also provided between the matrix precursor elements to promote long- term storability of the prepreg at ambient temperatures. All or a portion of the gas venting network may be integrated with the penetrable barriers. | 07-29-2010 |
| 20100186878 | Method For Molding Composite Structures - Method for making, modifying and using machinable composite molds for use in molding composite structures. The mold includes a mold body having a tool surface that is shaped to provide the molded surface of the composite structure. The mold body is made up of at least one mold layer composed of a quasi-isotropic material composed of a plurality of randomly oriented fiber bundles or chips impregnated with a resin. The use of randomly oriented fiber chips allows post-cure machining of the mold body. | 07-29-2010 |
| 20100154982 | CORROSION RESISTANT HONEYCOMB - Corrosion resistant metallic honeycomb composed of a plurality of honeycomb cells having cell walls that include cell edges that form the edge of the honeycomb. A corrosion resistant coating that contains polyamideimide is used to cover the cell walls and cell edges. The corrosion resistant coating is preferably applied after the honeycomb structure has been formed. | 06-24-2010 |
| 20100108812 | AEROSPACE ARTICLES MADE FROM QUASI-ISOTROPIC CHOPPED PREPREG - Quasi-isotropic chopped prepreg is used to make parts found in aerospace vehicles. Exemplary aerospace parts that are made using quasi-isotropic chopped prepreg include aircraft window frames, wing fairing supports, flange supports, frame gussets, rudder actuator brackets, shear ties, seat pedestals, cargo floor flange supports, storage bin fittings, antenna supports, torque tube pans, handle boxes, side guide fittings, wing box covers and intercostals. | 05-06-2010 |
| 20100087587 | Composite Materials With Improved Burn Properties - Epoxy resins and composite materials that generate reduced levels of sulfur dioxide and which unexpectedly have reduced self-extinguishing times. The epoxy resins are composed of from 50 to 70 weight percent of an epoxy resin component. The epoxy resin composition also includes from 20 to 35 weight percent of a thermoplastic blend that is composed of polyetherimide and polyamideimide. The epoxy resin composition further includes from 5 to 25 weight percent of a curative agent. The composite materials may be used for primary structures in aircraft and other load-bearing structures. | 04-08-2010 |
| 20100087582 | Epoxy resins with improved burn properties - Epoxy resin compositions that generate reduced levels of sulfur dioxide and which unexpectedly have reduced self-extinguishing times. The epoxy resins are composed of from 50 to 70 weight percent of an epoxy resin component. The epoxy resin composition also includes from 15 to 35 weight percent of a thermoplastic blend that is composed of polyetherimide and polyamideimide. The epoxy resin composition further includes from 5 to 25 weight percent of a curative agent. | 04-08-2010 |
| 20090189325 | Helicopter blade mandrel with roller assembly - Methods and apparatus are provided for making a rotor blade spar from composite material wherein a multi-component mandrel is used to form the composite spar. The mandrel is made using a number of components that are assembled and held in place using a roller assembly. The roller assembly is removed after pre-cure lay up and compaction of the composite material. Once the roller assembly is removed, the remaining mandrel components can be separated from each other and easily removed from the spar. The mandrel components, including the roller assembly, can then be re-assembled and re-used to form additional composite spars. | 07-30-2009 |
| 20090165931 | Method For Molding Composite Structures - Method for making, modifying and using machinable composite molds for use in molding composite structures. The mold includes a mold body having a tool surface that is shaped to provide the molded surface of the composite structure. The mold body is made up of at least one mold layer composed of a quasi-isotropic material composed of a plurality of randomly oriented fiber bundles or chips impregnated with a resin. The use of randomly oriented fiber chips allows post-cure machining of the mold body. | 07-02-2009 |
| 20090072086 | Aircraft floor and interior panels using edge coated honeycomb - Aircraft floor and interior panels where core-skin bonding is improved between honeycomb and composite face sheets (skins) by applying a polyamide and/or rubber-containing adhesive to the edge of the honeycomb prior to bonding. Edge coating of the honeycomb allows one to reduce panel weight without reducing the performance parameters that are required for different types of aircraft floor and interior panels. | 03-19-2009 |
| 20080286578 | Composite materials with blend of thermoplastic particles - Pre-impregnated composite material (prepreg) is provided that can be cured to form composite parts that have high levels of damage tolerance. The matrix resin includes a thermoplastic particle component that is a blend of particles that have a melting point above the curing temperature and particles that have a melting point at or below the curing temperature. | 11-20-2008 |
| 20080251315 | Acoustic septum cap honeycomb - An acoustic structure that includes a honeycomb having cells in which septum caps are located. The septum caps are formed from sheets of acoustic material and include a resonator portion and a flange portion. The flange portion has an anchoring surface that provides frictional engagement of the septum caps to the honeycomb cells when the caps are inserted into the honeycomb during fabrication of the acoustic structure. An adhesive is applied to the anchoring surface of the septum caps after the caps have been inserted into the honeycomb cells to provide a permanent bond. | 10-16-2008 |
