A printing system for producing at least one three dimensional (3D) printed part is described. The printing system includes a deposition system configured to continuously deposit a layer onto a cylinder to outwardly extend a diameter of the cylinder, wherein the layer comprises a first pattern. The printing system also includes a rotating system configured to rotate the cylinder, and a control system configured to synchronize the deposition system with the cylinder.

A method of providing high-speed three dimensional (3D) printing is described. The method includes producing at least one three dimensional (3D) printed part. Producing the 3D part includes continuously constructing to extend outwardly a diameter of a rotating cylindrical core via continuous deposition of a layer, and defining a first pattern in the continuously deposited layer corresponding to a cross-section of the at least one 3D printed part.

Techniques for evaluating support for an object to be fabricated via an additive fabrication device are provided. In some embodiments, a three-dimensional representation of the object is obtained and a plurality of voxels corresponding to the representation of the object is generated. A first supportedness value may be assigned to a first voxel of the plurality of voxels based on an amount of support provided by a support structure to the first voxel, and a second supportedness value determined for a second voxel of the plurality of voxels, wherein the second voxel neighbors the first voxel, and wherein the second supportedness value is determined based on the first supportedness value of the first voxel and a weight value representing a transmission rate of supportedness through voxels of the plurality of voxels.

A method of forming a sandwich structure including at least partially filling an open volume of an open cellular core with a sacrificial mold material, consolidating the sacrificial mold material to form a sacrificial mold, laying up a composite facesheet on each of at least two surfaces of the open cellular core, co-curing the composite facesheets by applying a consolidation temperature and a compaction pressure to the composite facesheets to form the sandwich structure, and removing the sacrificial mold. The compaction pressure is greater than a compressive strength of the open cellular core and less than a combined compressive strength of the open cellular core and the sacrificial mold.

A method produces an elastically deformable molded part having a number of undercut molded-part regions, by use of a mold. To provide a technique which makes it possible to produce individual molded parts which are elastically deformable and have undercut regions from soft materials in a precise and cost-effective manner, a method is performed in which a molded-part material is introduced into the mold. The mold has a shaping contour with a number of special contour regions, which are configured for shaping the number of undercut molded-part regions of the molded part, and in which the molded part is removed from the mold by at least partially deforming the mold together with the molded part therein in such a way that the molded part elastically deforms and the mold at least partially, but in any event to the extent of the special contour regions, breaks up.

A method for manufacturing a fiber reinforced structure includes the following. A mandrel of a first material comprises a hollow interior and an aperture that allows a fluid to enter the interior. A layer of a second material provided on the mandrel includes an uncured resin and fibers. The mandrel and the layer are placed in a mold cavity formed by a mold. A pressurized fluid is introduced into the interior of the mandrel via the aperture to generate a force acting to expand the mandrel outward. The mandrel is heated so that it becomes deformable and expand outward to press the layer against the mold. The layer is heated so that it cures. The mandrel is then heated to a temperature above its melting point of the first material so that it melts, after which it is removed.

A printing system for producing at least one three dimensional (3D) printed part is described. The printing system includes a deposition system configured to continuously deposit a layer onto a cylinder to outwardly extend a diameter of the cylinder, wherein the layer comprises a first pattern. The printing system also includes a rotating system configured to rotate the cylinder, and a control system configured to synchronize the deposition system with the cylinder.

A method for providing high-speed three dimensional (3D) printing is provided. The method includes producing at least one three dimensional (3D) printed part. Producing the 3D part includes continuously constructing to extend outwardly a diameter of a rotating cylindrical core via continuous deposition of a layer, and defining a first pattern in the continuously deposited layer corresponding to a cross-section of the at least one 3D printed part.

A structural component having an internal support structure extending between outer wall portions of the component with one or more compartments included within the support structure. The support structure has support members including internal walls positioned between and/or defined by the compartments. At least one support member connects between the outer wall portions of the component to enhance the structural integrity of the component. The structural component, including the internal support, are cast from a molten material, and in some cases the support members of the internal support structure are formed with a rectilinear configuration. In some cases the cast structural component is a container and the one or more compartments are configured to store a fluid, such as a gas or a liquid. One or more preforms can be used to form a container and may be retained or eliminated from the container after casting.

Systems and methods for casting solid propellants include a mandrel for forming geometric features in a perforation of a propellant grain. In various embodiments, the mandrel includes a frangible portion that is removed from the propellant grain after the propellant grain has cured around the mandrel. A second portion of the mandrel may be left behind in the propellant grain. The mandrel may include a support structured disposed in the through hole of the mandrel. The support structure may include a plurality of longitudinal channels for directed exhaust gasses through the mandrel upon ignition of the propellant grain.