The invention provides a sonotrode (100) for welding a material, the sonotrode (100) comprising a welding section (110) configured for contacting the material, wherein the welding section (110) defines a rounded shape (111) in a cross-section parallel to a longitudinal axis (A) of the sonotrode (100), wherein the rounded shape (111) approximates a circular sector (20), wherein the circular sector (20) has a central angle α.sub.c selected from the range of 25°-300°, and wherein the circular sector (20) has a central radius r.sub.c selected from the range of 5-30 mm, and wherein the sonotrode (100) has a width W perpendicular to the longitudinal axis (A) [and to the cross-section], wherein W is selected from the range of 10-100 mm.

A method for joining two components of a meltable material comprises the steps of providing a first component having a first border region and a second component having a second border region, placing the second component relative to the first component so as to form an overlap between the first border region and the second border region under a gap between the first border region and the second border region, continuously heating opposed sections of the first border region and the second border region at the same time through at least one energy source arranged in the gap at least partially, continuously providing a relative motion of the at least one energy source along the first border region and the second border region in the gap, and continuously pressing already heated sections of the first border region and the second border region onto each other.

A polymer composite composition for use in high temperature applications such as furnaces, heat shields and aeronautical jet and rocket motors. In a particular application, the disclosed composition is applied to the manufacture of rocket motor cases, or parts thereof, to provide rigid thermal protection (RTP). The polymer composite composition comprises cyanate ester resin, fine lengths of carbon fibre and refractory filler material.

A system and method for vaporizing space debris in space. The system includes a spacecraft body, a primary solar concentrator mounted to the spacecraft body that collects and focuses solar flux from the sun, and a secondary solar concentrator positioned at a focal point of the primary solar concentrator that refocuses the focused solar flux. A manipulator arm coupled to the spacecraft body grabs the space debris in space and positions it at a location where the refocused solar flux vaporizes the debris. The secondary solar concentrator can be a point-source concentrator, the primary solar concentrator can be a parabolic mirror, a Fresnel lens or a light focusing element or assembly, and the space debris can be a retired spacecraft or launch vehicle upper stage or component.

Systems and methods for 3D printing hollow bodies, such as bodies having an exterior cylindrical shape with a hollow interior, are described. Such systems and methods utilize rotatable hollow print base supports having an interior size and/or shape that matches the desired exterior shape of the final printed structure. The printed bodies, methods, and systems enable printing of the desired hollow printed body from the outside-to-inside. They also allow easy production, customization, and modification of internal structures within the printed hollow body.

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.

Grid structure, such as a lattice or grid-stiffened structure and a process of manufacturing such a grid structure. Fiber material is laid up on a base tool to form intersecting ribs defining a grid with a plurality of cavities. In the same step fiber material is laid to form one or more; local substructures. Blocks are placed, at the positions of the cavities. The fiber material of the ribs and. the local substructures is impregnated with a resin. Optionally, one or more layers of fiber material are placed on the base tool and/or over the ribs and the blocks to form an outer skin. The ribs, the local substructure and optionally the outer skin jointly consolidated to form, the grid, structure.

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 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.

A multilayer sealed skin, in particular for an inflatable structure and that includes a first polymer film, a reinforcing fabric disposed on the first polymer film and a second polymer film disposed on the reinforcing fabric and adhered by means of an adhesive to the first polymer film through cavities in the reinforcing fabric. The skin can be applied to the production of an inflatable structural element such as an inflatable beam for which the skin forms an outer wall of the structural element and for which the first film of the skin forms an inner face of the outer wall of the structural element, and the second film forms an outer face of the wall.