A method of manufacturing an arc-shaped fiber composite component includes forming a preform with a planar fiber layer arrangement formed along an arc and having an outer edge assigned to a convex outer side of the arc. The outer edge is formed with gaps extending into the arrangement in such a manner that a contour of the gaps is formed at least in sections near a target contour of a respective recess to be provided in the component. The preform is formed such that a first region of the arrangement, adjacent to the outer edge and extending substantially in the direction of the arc, is bent or angled relative to a second region of the arrangement, adjacent to the first region remote from the outer side of the arc. The gaps that the preform has prior to reshaping merge into recesses of the formed preform and remain open.

A reinforcing component for a structure of an aircraft or spacecraft has a first component region for reinforcing at least one other element, and at least one second component region, which is permanently connected to the first component region. The reinforcing component is formed using a thermoplastic plastics material in each of the first component region and the second component region. In the first component region, the thermoplastic plastics material forms a matrix in which continuous reinforcing fibres are embedded. In the second component region, the reinforcing component comprises discontinuous reinforcing fibres or is free of reinforcing fibres.

The present invention generally relates to a system and method for using a volatile organic compound (VOC) free low radiant flux LED UV curable composition, and more particularly to unique and novel uses of the composition such as one or two or more of a fire retardant, clear coat, composite material, resin, top coat, improved holdout coating, a sealant coat, and combinations of the same.

The present invention is a unique process of manufacturing rigid members with precise “shape keeping” properties and with reflective properties pertaining to radio frequency energy, so that air, land, sea and space devices or vehicles may be constructed including parabolic reflectors formed without discrete permanent layering. Rather, such parabolic reflectors or similarly, vehicles, may be formed by homogeneous construction where discrete layering is absent, and where energy reflectivity or scattering characteristics are embedded within the homogeneous mixture of carbon nanotubes and associated graphite powders and epoxy, resins and hardeners. The mixture of carbon graphite nanofiber and carbon nanotubes generates higher electrode conductivity and magnetized attraction through molecular polarization. In effect, the rigid members may be tuned based on the application. The combination of these materials creates a unique matrix that is then set in a memory form at a specific temperature, and then applied to various materials through a series of multiple layers, resulting in unparalleled strength and durability.

A vessel includes a vessel wall and an insulation assembly coupled to the vessel wall. The insulation assembly includes a stochastic foam material and a microtruss structure encased within the foam material. The microtruss structure includes a plurality of truss members interconnected at a plurality of nodes. Each truss member is in contact with the foam material such that the microtruss structure provides a structural core for the foam material.

A structural spacecraft component comprising internal microstructure; wherein said microstructure comprises a plurality of parallel layers and a plurality of spacers that connect adjacent parallel layers; wherein said structural spacecraft component is a product of an additive manufacturing process.

Chopped fiber composite systems and methods are disclosed. Sorting systems include a conveyor, an imager, a plurality of receptacles, a pneumatic device, and controller. Molding systems include a conveyor, an imager, a mold, a pneumatic device, and a controller. The controller directs the pneumatic device to alter the freefall of chopped fiber composite pieces based on characteristics of the chopped fiber composite pieces as they drop from the conveyor and into a receptacle or a mold. Sorting and molding methods include dropping chopped fiber composite pieces, detecting characteristics of the dropping pieces, and directing the pieces based on the detected characteristics.

An apparatus, system, and method utilizes at least two separate components during the process of producing the final product. At least one component during the process is produced using additive manufacturing, and additional components are components that are combined with the additively manufactured part. The apparatus, system, and method includes at least one energetic component and at least one second inert component. An additive manufacturing system produces a scaffold of said first energetic component(s). A system adds the second component(s) to the scaffold to produce the energetic material product.

A system is used for additively manufacturing propellant elements, such as for rocket motors, includes partially curing a propellant mixture before extruding or otherwise dispensing the material, such that the extruded propellant material is deposited on the element in a partially-cured state. The curing process for the partially-cured extruded material may be completed shortly after the material is put into place, for example by the material being heated at or above its cure temperature, such that it finishes curing before it fully cools. The propellant material may be prepared by first mixing together, a fuel, an oxidizer, and a binder, such as in an acoustic mixer. After that mixing a curative may be added to the mixture. The propellant mixture may then be directed to an extruder (or other dispenser), in which the mixture is heated to or above a cure temperature prior to the deposition, and then deposited.

A method for welding thermoplastic components, in particular, thermoplastic fiber composite structural components for an aircraft or spacecraft, having the following steps. Arranging an insert, which has a conductor structure having a plurality of parallel electrical conductor elements, in a joining zone between a first thermoplastic component and a second thermoplastic component such that at least some portions of the parallel electrical conductor elements are located in the joining zone; locally melting the components in the region of the joining zone by supplying current to the conductor structure; disconnecting the connector elements; and removing the insert from the joining zone by pulling out the disconnected conductor elements. An insert for the resistance welding of thermoplastic components is also provided.