Hexcel Corporation Patent applications |
Patent application number | Title | Published |
20150375481 | MULTI-COMPONENT COMPOSITE STRUCTURES - A composite assembly that can be cured to form a multi-component composite structure which does not have micro cracks along the boundaries between the various components. The composite assembly includes a structural component and a moldable component wherein the coefficients of thermal expansion of the structural component and the moldable component at the interface or boundary between the two components are such that micro cracks do not form along the interface when the composite assembly is cured to form the multi-component composite structure. | 12-31-2015 |
20150355111 | TRACERS FOR USE IN COMPRESSION MOLDING OF UNIDIRECTIONAL DISCONTINUOUS FIBER COMPOSITE MOLDING COMPOUND - Tracking or tracing of both the global and local movements of unidirectional discontinuous fiber composite (UD-DFC) chips during compression molding of UD-DFC molding compound. The tracking capability is provided by including tracer chips in the UD-DFC molding compound. The tracer chips include a resin matrix and at least one unidirectional carbon tow which is made up of a plurality of carbon filaments. The tracer chip further includes a unidirectional tracer yarn which is made up of a plurality of unidirectional filaments that are detectable by x-ray or other radiation-based scanning technique. | 12-10-2015 |
20150252182 | EXTENDED ROOM TEMPERATURE STORAGE OF EPOXY RESINS - Uncured epoxy resin for use in making prepreg for aerospace applications. The resin includes an epoxy resin component comprising difunctional epoxy resin, trifunctional epoxy resin and/or tetrafuctional epoxy resin and a sufficient amount of [3-(4-aminobenzoyl)oxyphenyl]4-aminobenzoate (3-ABOAB, as a curing agent, such that the uncured resin can be stored at room temperature of at least 6 weeks and wherein the uncured resin can be fully cured in no more than 2 hours at a temperature of between 175° C. and 185° C. | 09-10-2015 |
20150041248 | MULTI-SECTIONAL ACOUSTIC SEPTUM - A multi-sectional acoustic septum that includes sections which have different acoustic resistance properties. The multi-sectional acoustic septums extend vertically with the acoustic cell and are capable of increasing the effective acoustical length of the acoustic cell. The multiple acoustic properties provided by the multiple acoustic sections also make it possible to target specific frequency ranges within the overall frequency range of the acoustic cell. | 02-12-2015 |
20150041247 | SOUND WAVE GUIDE FOR USE IN ACOUSTIC STRUCTURES - The bandwidth or acoustical range of an acoustic structure is increased by locating a sound wave guide within the acoustic cell. The wave guide divides the cell into two acoustical chambers. The two chambers provide an effective increase in resonator length of the cell. | 02-12-2015 |
20140220339 | Carbon Fibers Having Improved Strength And Modulus And An Associated Method And Apparatus For Preparing Same - The invention is directed to carbon fibers having high tensile strength and modulus of elasticity. The invention also provides a method and apparatus for making the carbon fibers. The method comprises advancing a precursor fiber through an oxidation oven wherein the fiber is subjected to controlled stretching in an oxidizing atmosphere in which tension loads are distributed amongst a plurality of passes through the oxidation oven, which permits higher cumulative stretches to be achieved. The method also includes subjecting the fiber to controlled stretching in two or more of the passes that is sufficient to cause the fiber to undergo one or more transitions in each of the two or more passes. The invention is also directed to an oxidation oven having a plurality of cooperating drive rolls in series that can be driven independently of each other so that the amount of stretch applied to the oven in each of the plurality of passes can be independently controlled. | 08-07-2014 |
20140217332 | COMPOSITE MATERIALS - A prepreg comprising a fibre reinforced curable resin, the curable resin being composed of 25 to 35 weight percent tetrafunctional epoxy resin based on the total weight of the curable resin; 18 to 28 weight percent difunctional epoxy resin; 4 to 18 weight percent polyether sulfone; 2 to 10 weight percent polyamide 12 particles; 2 to 10 weight percent polyamide 11 particles; 1 to 8 weight percent potato shaped graphite particles; and 17.4 to 27.4 weight percent of a curing agent for said curable resin. | 08-07-2014 |
20140163139 | COMPOSITE MATERIAL WITH POLYAMIDE PARTICLE MIXTURES - Pre-impregnated composite material (prepreg) is provided that can be cured/molded to form composite parts having high damage tolerance and interlaminar fracture toughness. The matrix resin includes a thermoplastic particle component that includes a mixture of polyamide 12 particles and polyamide 11 particles. | 06-12-2014 |
20140133964 | ACOUSTIC STRUCTURE WITH INTERNAL THERMAL REGULATORS - Thermally insulating septums are located internally within the cells of an acoustic honeycomb to regulate heat flow into the acoustic structure. The internally located insulating septums protect the honeycomb and acoustic septums located within the honeycomb cells from heat damage that might otherwise be caused by a heat source, such as the hot section of a jet engine. The internal thermal regulators are useful in combination with heat blankets or other thermal insulating structures to provide a reduction in size and/or weight of the insulating structure while still providing the same overall degree of thermal insulation for the acoustic honeycomb. | 05-15-2014 |
20140131136 | ACOUSTIC STRUCTURE WITH INCREASED BANDWIDTH SUPPRESSION - The bandwidth or acoustical range of a nacelle or other type of acoustic structure is increased by acoustically coupling honeycomb cells together to form pairs of acoustic cells that have an effective acoustic or resonator length that is up to twice that of either acoustic cell taken alone. | 05-15-2014 |
20140110188 | ANCHORING OF SEPTUMS IN ACOUSTIC HONEYCOMB - A honeycomb structure dial includes cells in which septums are located to provide acoustic dampening. The cells are formed by at least our walls wherein at least two of the walls are substantially parallel to each other. The septums include warp fibers and weft fibers that are substantially perpendicular to each other. The septums are oriented in the honeycomb cells such that the weft fibers and/or warp fibers are substantially perpendicular to the parallel walls. | 04-24-2014 |
20140058013 | COMPOSITE MATERIAL WITH POLYAMIDE PARTICLES - Pre-impregnated composite material (prepreg) is provided that can be cured/molded to form composite parts having high compression strength under hot and wet conditions, as well as, high damage tolerance and interlaminar fracture toughness. The matrix resin includes a thermoplastic particle component that includes polyamide particles which are composed of the polymeric condensation product of a methyl derivative of bis(4-aminocyclohexyl)methane and an aliphatic dicarboxylic acid. | 02-27-2014 |
20140034417 | SPLICING OF CURVED ACOUSTIC HONEYCOMB - Honeycomb sections are bonded together with seams made up of an adhesive that is carried by a linked-segment seam support. The seams are particularly useful for splicing together curved honeycomb sections that contain acoustic septum. The curved acoustic honeycomb sections are spliced or seamed together to form engine nacelles and other acoustic damping structures. | 02-06-2014 |
20140013601 | METHOD FOR MAKING ACOUSTIC HONEYCOMB - A method for making 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. | 01-16-2014 |
20130341119 | STRUCTURE WITH ACTIVE ACOUSTIC OPENINGS - An acoustic structure that includes a septum having an acoustic opening which defines an open area that varies in response to changes in the velocity of noise-containing media passing through the acoustic opening. The septum includes a fixed portion and one or more movable flapper portions wherein the fixed portion and/or the flapper portion(s) include surfaces that define an acoustic opening through the septum. The acoustic opening has an open area which varies due to movement of the movable flapper(s) in response to changes in velocity of the noise-containing media that passes through the acoustic opening. The resulting septum has a relatively low non-linearity factor (NLF). | 12-26-2013 |
20130330551 | Carbon Fibers Having Improved Strength and Modulus and an Associated Method and Apparatus For Preparing Same - The invention is directed to carbon fibers having high tensile strength and modulus of elasticity. The invention also provides a method and apparatus for making the carbon fibers. The method comprises advancing a precursor fiber through an oxidation oven wherein the fiber is subjected to controlled stretching in an oxidizing atmosphere in which tension loads are distributed amongst a plurality of passes through the oxidation oven, which permits higher cumulative stretches to be achieved. The method also includes subjecting the fiber to controlled stretching in two or more of the passes that is sufficient to cause the fiber to undergo one or more transitions in each of the two or more passes. The invention is also directed to an oxidation oven having a plurality of cooperating drive rolls in series that can be driven independently of each other so that the amount of stretch applied to the oven in each of the plurality of passes can be independently controlled. | 12-12-2013 |
20130309435 | OVER-MOLDING OF LOAD-BEARING COMPOSITE STRUCTURES - A load-bearing composite structure for connection to a support body or structure. The load-bearing structure includes a load-bearing element that is made up of continuous reinforcing fibers and a resin matrix. The load-bearing element has an attachment portion for connection to the support body. The load-bearing composite structure further includes a connection element that is formed using a molding material which is composed of discontinuous fibers and a resin matrix. The molding material is molded over the surface of the attachment portion of the load-bearing element. | 11-21-2013 |
20130299274 | ACOUSTIC STRUCTURE WITH INCREASED BANDWIDTH SUPPRESSION - The bandwidth or acoustical range of a nacelle or other type of acoustic structure is increased by acoustically coupling honeycomb cells together to form pairs of acoustic cells that have an effective acoustic or resonator length that is up to twice that of either acoustic cell taken alone. | 11-14-2013 |
20130285284 | MODULE FOR HOLDING AT LEAST ONE BUSHING | 10-31-2013 |
20130260022 | COMPOSITE MATERIAL FOR STRUCTURAL APPLICATIONS - Composite material that contain epoxy resin which is toughened and strengthened with thermoplastic materials and a blend of 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. | 10-03-2013 |
20130220731 | SPLICING OF CURVED ACOUSTIC HONEYCOMB - Honeycomb sections are bonded together with seams made up of an adhesive that is carried by a honeycomb seam support or a linked-segment seam support. The seams are particularly useful for splicing together curved honeycomb sections that contain acoustic septum. The curved acoustic honeycomb sections are spliced or seamed together to form engine nacelles and other acoustic dampening structures. | 08-29-2013 |
20130101406 | HIGH PRESSURE MOLDING OF COMPOSITE PARTS - Composite pre-forms are molded at high pressure to form composite parts that can be used in place of metal-based high performance parts, such as the outlet guide vanes found in turbofan jet engines. The composite pre-forms include two different fiber orientations that are co-molded in a resin matrix at high pressures to provide composite outlet guide vanes and other high performance parts. Chambers within the composite part are optionally formed during molding of the pre-form at high pressures. | 04-25-2013 |
20130062143 | ANCHORING OF SEPTUMS IN ACOUSTIC HONEYCOMB - A honeycomb structure that includes cells in which septums are located to provide acoustic dampening. The cells are formed by at least four walls wherein at least two of the walls are substantially parallel to each other. The septums include warp fibers and weft fibers that are substantially perpendicular to each other. The septums are oriented in the honeycomb cells such that the weft fibers and/or warp fibers are substantially perpendicular to the parallel walls. | 03-14-2013 |
20130005898 | 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. | 01-03-2013 |
20120308766 | 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. | 12-06-2012 |
20120223183 | 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. | 09-06-2012 |
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 |