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.

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.

A method for joining together different components or different sections of a single component, wherein at least one of the components is a thermoplastic fiber composite component, by using a threaded fastener. Heat is used for softening the thermoplastic fiber composite component to be joined together with the threaded fastener. A joined-together fiber composite component of a vehicle, aircraft or spacecraft, can be obtained by the disclosed method.

A hybrid rocket solid fuel grain having a cylindrical shape and defining a center port is additive manufactured from a compound of thermoplastic fuel and passivated nanocomposite aluminum additive. The fuel grain comprises a stack of fused layers, each layer formed as a plurality of fused abutting concentric circular beaded structures arrayed to define a center port. During operation, an oxidizer is introduced along the center port, with combustion occurring along the exposed port wall. Each circular beaded structure defines geometry that increases the surface area available for combustion. As each layer ablates the next abutting layer, exhibiting a similar geometry, is revealed, undergoes a gas phase change, and ablates. This process repeats and persists until oxidizer flow is terminated or the fuel grain material is exhausted. To safely achieve this construction, a fused deposition additive manufacturing apparatus, modified to shield the nanocomposite material from the atmosphere, is used.

Spacecraft including a spacecraft bus. An additive manufacturing system of the spacecraft bus including at least one extruder for delivering feedstock to print an object outside of the spacecraft bus. A sensor for determining a pose of the spacecraft bus relative to an astronomical body. At least one processor in communication with the additive manufacturing system and the sensor, controls an operation of the additive manufacturing system as a function of the pose of the spacecraft bus, to manufacture the object outside of the spacecraft bus.

A hybrid rocket solid fuel grain having a cylindrical shape and defining a center port is additive manufactured from a compound of thermoplastic fuel and passivated nanocomposite aluminum additive. The fuel grain comprises a stack of fused layers, each layer formed as a plurality of fused abutting concentric circular beaded structures arrayed to define a center port. During operation, an oxidizer is introduced along the center port, with combustion occurring along the exposed port wall. Each circular beaded structure defines geometry that increases the surface area available for combustion. As each layer ablates the next abutting layer, exhibiting a similar geometry, is revealed, undergoes a gas phase change, and ablates. This process repeats and persists until oxidizer flow is terminated or the fuel grain material is exhausted. To safely achieve this construction, a fused deposition additive manufacturing apparatus, modified to shield the nanocomposite material from the atmosphere, is used.

A system for producing an object is disclosed including a build device having a build area and a material bonding component to receive portions of a material that are used to produce the object, at least one gripper within the build area to contact the object to provide support and to provide for at least one of a heat sink for the object, a cold sink for the object, and electrical dissipation path from the object, and a movement mechanism to move the build device relative to the object to position the build device at a position to further produce the object. Another system and methods are also disclosed.

Disclosed herein is a reinforced panel. The reinforced panel is produced by a process that comprises applying a reinforcing fiber material, comprising a first polymeric material, to only a portion of a panel sheet, comprising a second polymeric material. The process also comprises, after applying the reinforcing fiber material to the panel sheet, thermoforming both the second polymeric material of the panel sheet and the first polymeric material of the reinforcing fiber material. The thermoforming integrally couples the panel sheet with the reinforcing fiber material to produce the reinforced panel by fusion bonding the first polymeric material with the second polymeric material. The reinforced panel includes one or more reinforced portions, defined by the reinforcing fiber material, and one or more non-reinforced portions, defined between the reinforcing fiber material.

A method for assembling two parts, referred to as first and second parts, the first part being produced from composite material with fibrous reinforcement embedded in a thermosetting or thermoplastic matrix, the method comprising the steps of: obtaining the first part comprising, on all or part of an outer surface, a first amorphous thermoplastic film; positioning the first part and the second part such that the first amorphous thermoplastic film is placed opposite the second part; introducing a thermosetting resin between the first amorphous thermoplastic film and the second part; at least partially polymerising the thermosetting resin. When the two parts comprise an amorphous thermoplastic film, the parts are positioned such that the respective amorphous thermoplastic films are placed opposite each other, and the thermosetting resin is introduced between the amorphous thermoplastic films.

This invention relates to an assembly of regions (10a, 10b) of composite parts (2a, 2b) with thermoplastic matrix, including a plurality of riveting points along regions (10a, 10) of the parts that overlap through the superposition of two faces (12a, 12b) of these regions (10a, 10b) which are positioned facing one another, each region (10a, 10b) having another, opposite, face (11a, 11b) which remains visible with the part (2a, 2b). The riveting is performed using assembly ties (6) made of thermoplastic resin-based composite material compatible with the material of the parts (2a, 2b). These ties (6), which are made up at least in part of a stitch of backstitch produced using a filament of a material selected from a fiber coated with aramid resin, a carbon fiber and a glass fiber, are embedded in said regions (10a, 10b) and passing right through the same with an orientation comprised between 30 and 90 with respect to their faces (11a, 11b; 12a, 12b).