Abstract: A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing.

Abstract: A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing.

Abstract: A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing.

Abstract: In one embodiment, a wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side, the second side comprising a plurality of vortex generators arranged in an array configuration, the array configuration of vortex generators operable to weaken a wingtip vortex generated by the wing by generating one or more vane vortices near an end of the low pressure side of the wing.

Abstract: A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing.

Abstract: In one embodiment, a wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side, the second side comprising a plurality of vortex generators arranged in an array configuration, the array configuration of vortex generators operable to weaken a wingtip vortex generated by the wing by generating one or more vane vortices near an end of the low pressure side of the wing.

Abstract: A variable hardness gradient armor alloy is produced with a liquid-state reaction between a metallic molten pool and a gaseous atmosphere having a small fraction of reactive gas. The content of the reactant gas is varied as the armor is fabricated in order to vary the properties of the resultant material across its thickness and typically include, for example, a hardened outer or initial layer for impact resistance, and at least one inner layer having a lower hardness than the outer layer but greater energy absorption.

Abstract: Ring-shaped shape memory alloys put disk-shaped ceramic materials in a state of compression. The rings are radially deformed to introduce plastic strain into the rings. The rings are sized to closely receive the disk-shaped ceramic strike plates. When the assembly is heated, the rings attempt to regain their original shape and thereby put the ceramic strike plates into uniform, two-dimensional compression.

Abstract: The present invention provides fabrics that have unique mechanical, chemical, electrical, and thermal properties. The fabrics comprise layers of woven, knit or felted fibers, yarns or tow. Interstitially synthesized nanotubes, such as single-walled or multi-walled carbon nanotubes, enhance the fabric's antiballistic properties. These nanotubes may also insulate, semi-conduct or super-conduct electrical charges, or provide enhanced thermal properties of these fabrics which can be layered to form unique garments or structures.

Abstract: Leading edge structures for high performance aircraft and the direct manufacture thereof are disclosed. Direct manufacturing technology is used to deposit leading edge structures directly from a digital model to form near-net shape products. This technique permits a wider range of materials to be utilized, such as casting alloys capable of the highest temperature usage that are not available in billet or sheet form. Refractory metals or high temperature ceramics also may be used to form the entire lead edge structure, or just a replaceable tip of the leading edge structure.

Abstract: An open cell or highly porous woven composite truss utilizes fibers of carbon, glass, ceramic, or the like that are woven together in a loom. The warps or tow are woven with the wefts, while the fibers are impregnated with resin. The resin impregnation step may be performed before or after the weaving step. The truss is then cured on the loom and later may be machined as needed. A rigid foam material may be used to stabilize the shape of the truss prior to curing and while machining. The foam may be later chemically dissolved or otherwise disposed of.

Abstract: A ballistic armor uses shape memory alloys and novel joining techniques to form a solution from a combination of shape memory metallic alloys (SMA) and ceramic materials. The SMA allows a high amount of strain to be recovered through a low temperature heat treatment. The amount of strain recoverable is much higher than that available through conventional thermal expansion mismatch solutions. Solid state or low temperature bonding methods are used to join the dissimilar materials. This joining technique avoids introducing excessive heat that would cause the SMA to transform before the armor system is assembled.

Abstract: A ballistic armor uses shape memory alloys and novel joining techniques to form a solution from a combination of shape memory metallic alloys (SMA) and ceramic materials. The SMA allows a high amount of strain to be recovered through a low temperature heat treatment. The amount of strain recoverable is much higher than that available through conventional thermal expansion mismatch solutions. Solid state or low temperature bonding methods are used to join the dissimilar materials. This joining technique avoids introducing excessive heat that would cause the SMA to transform before the armor system is assembled.

Abstract: An apparatus and method for hologram induced deposition of material for use in the formation of three-dimensional structures is described. An electromagnetic energy source may be directed in the form of a hologram to a process chamber with a medium. The medium may be an organometallic gaseous medium. The hologram may induce the medium to form a solid structure associated with the shape of the hologram. The pressure of the gaseous medium may range from subatmospheric to greater than 100 psi. Alternatively, the medium may be a liquid polymer, a solid particle, or others. The hologram may be formed with an LCD panel or other means. Further, a holographic movie may be projected into one or more mediums to form complex three-dimensional structures.

Abstract: Leading edge structures for high performance aircraft and the direct manufacture thereof are disclosed. Direct manufacturing technology is used to deposit leading edge structures directly from a digital model to form near-net shape products. This technique permits a wider range of materials to be utilized, such as casting alloys capable of the highest temperature usage that are not available in billet or sheet form. Refractory metals or high temperature ceramics also may be used to form the entire lead edge structure, or just a replaceable tip of the leading edge structure.

Abstract: The present invention provides fabrics that have unique chemical, electrical, and thermal properties. The fabrics comprise layers of yarns woven together wherein the yarns further comprise carbon nanotube fibers. These carbon nanotube fibers may be either single-walled or multi-walled carbon nanotubes. The use of carbon nanotube fibers allows the fabrics to insulate, semi-conduct or super-conduct electrical charges. Additionally, the thermal properties of carbon nanotubes allow thermal energy to flow efficiently between the fabric and a heat sink or source. Additional yarns of materials other than carbon nanotubes can be integrated or woven into the fabric to provide other unique properties for the fabric. These fabrics can be layered to form unique garments or structures.

Abstract: Warhead structures and features are fabricated using direct manufacturing technologies, a method for fabricating bulk warhead structures by sequential and additive deposition of melted feedstock layers. Suitable energy sources for melting the feedstock can be various high energy density technologies including laser, electron beam, plasma arc deposition, and the like. The high energy density in combination with high cooling rates results in structures with homogeneous microstructures. The feedstock can be in the form of wire or powder and is applied to a substrate by introduction to a molten pool on the substrate, accumulating to additively combine with the substrate. The approach provides for warhead structures with singular and combined unique features to include: integral constructions, tailored fragmentation patterns, use of dissimilar materials for special effects, and variable material property constructions for enhanced performance.

Abstract: An apparatus and method for hologram induced deposition of material for use in the formation of three-dimensional structures is described. An electromagnetic energy source may be directed in the form of a hologram to a process chamber with a medium. The medium may be an organometallic gaseous medium. The hologram may induce the medium to form a solid structure associated with the shape of the hologram. The pressure of the gaseous medium may range from subatmospheric to greater than 100 psi. Alternatively, the medium may be a liquid polymer, a solid particle, or others. The hologram may be formed with an LCD panel or other means. Further, a holographic movie may be projected into one or more mediums to form complex three-dimensional structures.