Abstract: A method, apparatus, system, and computer program product for manufacturing an unconsolidated composite material. Sensor data is received from a sensor system for a composite material manufacturing system, wherein the sensor data is received during manufacturing of the unconsolidated composite material by the composite material manufacturing system. A set of predicted properties is determined for a number of portions of the unconsolidated composite material as completed from manufacturing by the composite material manufacturing system using the sensor data. A quality level for the number of portions of the unconsolidated composite material is identified based on the set of predicted properties for the number of portions of the unconsolidated composite material.

Abstract: A system, apparatus, computer program product, and a method for manufacturing an unconsolidated composite material. Sensor data is received from a sensor system for a composite material manufacturing system. The sensor data is received during manufacturing an unconsolidated composite material by the composite material manufacturing system. A set of predicted properties is determined for a number of portions of the unconsolidated composite material using the sensor data. The set of predicted properties is for the number of portions of the unconsolidated composite material as a completed product. A corrective action is performed based on a quality level for the number of portions of the unconsolidated composite material.

Abstract: Methods and apparatus to increase fire resistance and fracture toughness of composite structures are described. An example multi-ply composite structure has at least eleven plies including an innermost ply forming a first external surface of the multi-ply composite structure, and an outermost ply forming a second external surface of the multi-ply composite structure, with the second external surface being located opposite the first external surface. The at least eleven plies further include at least one and no more than three fire-resistant plies positioned between the innermost ply and the outermost ply within either an innermost 33% of the at least eleven plies or an outermost 33% of the at least eleven plies. Respective ones of the fire-resistant plies include an epoxy-based resin and a first additive mixed into the epoxy-based resin. The first additive increases a flammability resistance of the multi-ply composite structure.

Abstract: Methods and apparatus to increase fire resistance and fracture toughness of composite structures are described. An example multi-ply composite structure has at least eleven plies including an innermost ply forming a first external surface of the multi-ply composite structure, and an outermost ply forming a second external surface of the multi-ply composite structure, with the second external surface being located opposite the first external surface. The at least eleven plies further include at least one and no more than three fire-resistant plies positioned between the innermost ply and the outermost ply within either an innermost 33% of the at least eleven plies or an outermost 33% of the at least eleven plies. Respective ones of the fire-resistant plies include an epoxy-based resin and a first additive mixed into the epoxy-based resin. The first additive increases a flammability resistance of the multi-ply composite structure.

Abstract: Methods and apparatus to increase fire resistance and fracture toughness of a composite structure are described. An example apparatus includes a composite structure formed by an innermost ply and a fire-resistant ply including a first additive to increase a flammability resistance of the structure, where the fire-resistant ply is an inner ply of the composite structure.

Abstract: Methods and apparatus to increase fire resistance and fracture toughness of a composite structure are described. An example apparatus includes a composite structure formed by an innermost ply and a fire-resistant ply including a first additive to increase a flammability resistance of the structure, where the fire-resistant ply is an inner ply of the composite structure.

Abstract: A joining surface formed of a composite structure having at least one ply and a peel ply cured to an outer surface of the composite structure, the peel ply including a plurality of microcapsules each filled with a joining material, wherein upon removal of the peel ply from the outer surface of the composite structure, the microcapsules fracture and release the resin to form an uncured surface for joining.

Abstract: The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be oriented at angles to other plies. Nevertheless, in a preferred embodiment of the invention, a substantial majority of, or all of, the fibers of the hybrid laminates are oriented in a common direction. The outer surfaces of the laminates include a layer of titanium foil to protect the underlying composite-containing structure from the environment, and attack by solvents, and the like.

Abstract: The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be oriented at angles to other plies. Nevertheless, in a preferred embodiment of the invention, a substantial majority of, or all of, the fibers of the hybrid laminates are oriented in a common direction. The outer surfaces of the laminates include a layer of titanium foil to protect the underlying composite-containing structure from the environment, and attack by solvents, and the like.