Abstract: A process for manufacturing a three-dimensional object from a powder by selective sintering the powder using electromagnetic radiation. The powder includes recycled PAEK. In one embodiment, the powder includes recycled PEKK. In one embodiment, the powder includes first recycle PEKK and second recycle PEKK. In one embodiment, the powder consists essentially of recycled PEKK. The process may include the step of maintaining a bed of a selective laser sintering machine at approximately 300 degrees Celsius and applying a layer of the powder to the bed. The average in-plane tensile strength of the three-dimensional object is greater than that of a three-dimension object manufactured by selective sintering using a powder including an unused PEKK powder.

Abstract: Provided is a composition for the treatment of fibers, such as PAN precursor fibers. The finish composition includes a polysiloxane; an emulsifier; water; and a dicarboxylic acid having a pKa from 1 to 4, and boiling point from 200 to 400° C. The dicarboxylic acid may have the following formula: where R1 is absent or a saturated or unsaturated, linear or branched, aromatic substituted or unsubstituted, hydrocarbon group; Y1 and Y2 are independently hydrogen, nitrogen, oxygen, sulfur, phosphorus, C1-C6 alkyl group, or an alkoxy group; and X1 and X2 are independently one or more hydrogen atoms, a metal, a quaternary amine, or a hydrocarbon group having up to 6 carbon atoms, the hydrocarbon group being an alkyl group, an alkylene group, or an aromatic group, which may be branched or linear, and may optionally have one or more heteroatoms selected from the group consisting of nitrogen, oxygen, sulfur and phosphorus.

Abstract: A thermal panel having a high temperature side located nearest a source of heat and a low temperature side. The thermal panel includes a corrugated composite material core having hot side ridges and cold side ridges. A hot side skin is attached to the hot side ridges to form a plurality of first cells. A cold side skin is attached to the cold side ridges to form a plurality of second cells. The first cells and second cells are substantially filled with an insulating material that has a thermal conductivity which is lower than the thermal conductivity of the composite material.

Abstract: A semipreg that can be cured/molded to form aerospace composite parts including rocket booster casings. The semipreg includes a fibrous layer and a resin layer located on one side of the fibrous layer. The resin layer includes an epoxy component that is a combination of a hydrocarbon epoxy novolac resin and a trifunctional epoxy resin and optionally a tetrafunctional epoxy resin. The resin matrix includes polyethersulfone as a toughening agent and a thermoplastic particle component.

Abstract: Pre-impregnated composite material (prepreg) that can be cured/molded to form aerospace composite parts that are designed to tolerate hot and wet conditions. The prepreg includes fibers and an uncured resin. The uncured resin includes an epoxy component that is a combination of a trifunctional epoxy resin, a tetrafunctional epoxy resin and a solid epoxy resin. The resin further includes polyethersulfone as a toughening agent and a curing agent.

Abstract: Pre-impregnated composite material (prepreg) that can be cured/molded to form aerospace composite parts. The prepreg includes carbon reinforcing fibers and an uncured resin matrix. The resin matrix includes an epoxy component that is a combination of a hydrocarbon epoxy novolac resin and a trifunctional epoxy resin and optionally a tetrafunctional epoxy resin. The resin matrix includes polyethersulfone as a toughening agent and a thermoplastic particle component.

Abstract: Light weight fibrous veils are incorporated into the uncured composite face sheets of a honeycomb sandwich structure in order to reduce the lateral crushing of the honeycomb (core crush) that occurs during curing of the uncured structure in an autoclave or vacuum bag system. The light weight fibrous veils act as friction-promoting layers to reduce the relative movement of the uncured face sheets that leads to core crush during the curing process.

Abstract: An alternate resin-coated paper material for use in making honeycomb. The alternate resin-coated paper material is made from a paper that contains from 30 to 50 weight percent aramid fibers and from 50 to 70 weight percent of non-aramid fibers. A fire retarded phenolic resin is incorporated into the paper to make it self-extinguishing in less than 10 seconds with a self-extinguishing burn length of less than 12 inches when exposed to a 12-second vertical flame in accordance with the vertical burn test requirements set forth in 14 C.F.R. Part 25.583. The fire retarded phenolic resin includes a phenol formaldehyde resin and a phosphorous-containing fire retardant.

Abstract: 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.

Abstract: Pre-impregnated composite material (prepreg) that can be cured/molded to form aerospace composite parts. The prepreg includes carbon reinforcing fibers and an uncured resin matrix. The resin matrix includes an epoxy component that is a combination of a hydrocarbon epoxy novolac resin and a trifunctional epoxy resin and a tetrafunctional epoxy resin. The resin matrix includes polyethersulfone as a toughening agent and a thermoplastic particle component that includes a mixture of polyamide particles and polyimide particles.

Abstract: 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.

Abstract: 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 tetrafunctional 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.

Abstract: A method for determining a bed temperature setpoint for use with a powder in a selective laser sintering machine is disclosed. The method includes the step of providing a powder comprising a polymer for use in a selective laser sintering machine. The method further includes the step of determining a ratio of a liquid portion of the powder to a solid portion of the powder as a function of temperature within a temperature range. A bed temperature setpoint is selected in the temperature range corresponding to a desired ratio of the liquid portion of the powder to the solid portion of the powder. A temperature of a bed of a selective laser sintering machine is set to the selected bed temperature setpoint, and a part is built from the powder using the selective laser sintering machine.

Abstract: Pre-impregnated composite material (prepreg) that can be cured/molded to form aerospace composite parts. The prepreg includes carbon reinforcing fibers and an uncured resin matrix. The resin matrix includes an epoxy component that is a combination of a hydrocarbon epoxy novolac resin and a trifunctional epoxy resin and optionally a tetrafunctional epoxy resin. The resin matrix includes polyethersulfone as a toughening agent and a thermoplastic particle component.

Abstract: A process for manufacturing a three-dimensional object from a powder by selective sintering the powder using electromagnetic radiation. The powder includes recycled PAEK. In one embodiment, the powder includes recycled PEKK. In one embodiment, the powder includes first recycle PEKK and second recycle PEKK. In one embodiment, the powder consists essentially of recycled PEKK. The process may include the step of maintaining a bed of a selective laser sintering machine at approximately 300 degrees Celsius and applying a layer of the powder to the bed. The average in-plane tensile strength of the three-dimensional object is greater than that of a three-dimension object manufactured by selective sintering using a powder including an unused PEKK powder.

Abstract: Amino benzoates have been found to be useful curing agents for epoxy resins particularly para amino benzoates containing at least two primary amine groups and at least two carboxyl moieties, the amino benzoates are particularly useful as curatives in prepregs.

Abstract: A process for manufacturing a three-dimensional object from a powder by selective sintering the powder using electromagnetic radiation. The powder comprises recycled PAEK. In one embodiment, the powder comprises recycled PEKK. In one embodiment, the powder comprises first recycle PEKK and second recycle PEKK. In one embodiment, the powder consists essentially of recycled PEKK. The process may include the step of maintaining a bed of a selective laser sintering machine at approximately 300 degrees Celsius and applying a layer of the powder to the bed. The average in-plane tensile strength of the three-dimensional object is greater than that of a three-dimension object manufactured by selective sintering using a powder comprising an unused PEKK powder.

Abstract: Pre-impregnated composite material (prepreg) is provided that can be cured/molded to form composite parts having high levels of compressive strength under dry conditions at room temperature and which retain their compressive strength when subjected to hot and wet conditions. The pre-impregnated composite materials are composed of reinforcing fibers and an uncured resin matrix. The uncured resin matrix includes a resin component made up of one or more difunctional epoxy resins and multifunctional epoxy resins. The uncured resin matrix further includes a thermoplastic particle component, a thermoplastic toughening agent and a curing agent. The thermoplastic particle component is composed of a mixture of a first group of polyamide particles that do not contain crosslinked polyamide and a second group of polyamide particles that contain crosslinked polyamide.

Abstract: A method for determining a bed temperature setpoint for use with a powder in a selective laser sintering machine is disclosed. The method includes the step of providing a powder comprising a polymer for use in a selective laser sintering machine. The method further includes the step of determining a ratio of a liquid portion of the powder to a solid portion of the powder as a function of temperature within a temperature range. A bed temperature setpoint is selected in the temperature range corresponding to a desired ratio of the liquid portion of the powder to the solid portion of the powder. A temperature of a bed of a selective laser sintering machine is set to the selected bed temperature setpoint, and a part is built from the powder using the selective laser sintering machine.

Abstract: An existing acoustic honeycomb panel having a radius of curvature is cut into segments that have longitudinal and lateral sides that extend between the edges of the honeycomb. The segments are bonded together along their longitudinal or lateral sides to form a segmented acoustic honeycomb in which the radius of curvature is different from the radius of curvature of the original acoustic honeycomb panel. The shape of the longitudinal or lateral sides of the segments and the thickness of the adhesive bond can be controlled to provide segmented acoustic honeycomb panels that are tightly curved and which are suitable for use in demanding noise damping applications, such as jet engine nacelles.