Abstract: The specification relates to a gemstone setting. The gemstone setting includes a gemstone, a mounting surface and a braze joint. The braze joint is formed from a reactive metallic alloy with the reactive metallic alloy adhering the gemstone to the mounting surface. The braze joint is substantially concealed from a direct line of sight from a top portion of the gemstone by preventing excessive alloy from getting outside a desired braze area.

Abstract: A vehicle, such as a missile, is disclosed. The vehicle includes an optically transparent dome, a vehicle body, and a brazed joint directly coupling the dome to the vehicle body. The dome is formed of a Nanocomposite Optical Ceramic (NCOC) material comprising two or more different types of nanograins dispersed in one another. Each nanograin type has a coefficient of thermal expansion (CTE), and an aggregate CTE of the NCOC material is based on the CTE of each nanograin type.

Abstract: A vehicle, such as a missile, is disclosed. The vehicle includes an optically transparent dome, a vehicle body, and a brazed joint directly coupling the dome to the vehicle body. The dome is formed of a Nanocomposite Optical Ceramic (NCOC) material comprising two or more different types of nanograins dispersed in one another. Each nanograin type has a coefficient of thermal expansion (CTE), and an aggregate CTE of the NCOC material is based on the CTE of each nanograin type.

Abstract: The specification relates to a gemstone setting. The gemstone setting includes a gemstone, a mounting surface and a braze joint. The braze joint is formed from a reactive metallic alloy with the reactive metallic alloy adhering the gemstone to the mounting surface. The braze joint is substantially concealed from a direct line of sight from a top portion of the gemstone by preventing excessive alloy from getting outside a desired braze area.

Abstract: An optical component, for example a lens, integrally formed of a nano/nano class nanocomposite optical ceramic (NNCOC) material. The constituent nanograin materials of the NNCOC material are selected to tailor the thermal and optical properties of the lens so as to provide a lens with a substantially constant focal length over an operating temperature range and/or an optical system in which the image position does not change appreciably over the operating temperature range.

Abstract: A one-piece extended dome having a spanning angle greater than 180 degrees. The dome is integrally formed of a Nano/Nano class Nanocomposite Optical Ceramic (NNOC) material. The extended dome comprises seamless first and second non-complementary geometric shapes, such as a first spherical geometry and a second conical or ogive geometry. The Nano/Nano class NNOC material comprises two or more different chemical phases (nanograins) dispersed in one another, each type having a sub-micron grain dimension in at least the direction of light transmission. The material is a true NNOC material in that all of the constituent elements have sub-micron grain dimensions, there is no host matrix.

Abstract: A one-piece extended dome having a spanning angle greater than 180 degrees. The dome is integrally formed of a Nano/Nano class Nanocomposite Optical Ceramic (NNOC) material. The extended dome comprises seamless first and second non-complementary geometric shapes, such as a first spherical geometry and a second conical or ogive geometry. The Nano/Nano class NNOC material comprises two or more different chemical phases (nanograins) dispersed in one another, each type having a sub-micron grain dimension in at least the direction of light transmission. The material is a true NNOC material in that all of the constituent elements have sub-micron grain dimensions, there is no host matrix.

Abstract: A control mechanism pins an optical fiber assembly on and off gimbal and between gimbals to route the assembly from an off-gimbal optical source across the gimbal axis/axes to an on-gimbal optical element so that the fiber assembly moves with the rotation of the gimbals. To accommodate a relatively large range of motion, the control mechanism is suitably configured to route the fiber assembly in a “U-shaped” loop with one end pinned off-gimbal in a stationary guide track and the other end pinned on-gimbal point in a rotating guide track so that the loose fiber assembly is constrained in the concentric tracks on and off gimbal. As the gimbal rotates, the loop seats onto one guiding track and peels off of the other guiding track while always maintaining its U shape.

Abstract: A control mechanism pins an optical fiber assembly on and off gimbal and between gimbals to route the assembly from an off-gimbal optical source across the gimbal axis/axes to an on-gimbal optical element so that the fiber assembly moves with the rotation of the gimbals. To accommodate a relatively large range of motion, the control mechanism is suitably configured to route the fiber assembly in a “U-shaped” loop with one end pinned off-gimbal in a stationary guide track and the other end pinned on-gimbal point in a rotating guide track so that the loose fiber assembly is constrained in the concentric tracks on and off gimbal. As the gimbal rotates, the loop seats onto one guiding track and peels off of the other guiding track while always maintaining its U shape.

Abstract: A control mechanism pins an optical fiber assembly on and off gimbal and between gimbals to route the assembly from an off-gimbal optical source across the gimbal axis/axes to an on-gimbal optical element so that the fiber assembly moves with the rotation of the gimbals. To accommodate a relatively large range of motion, the control mechanism is suitably configured to route the fiber assembly in a “U-shaped” loop with one end pinned off-gimbal in a stationary guide track and the other end pinned on-gimbal point in a rotating guide track so that the loose fiber assembly is constrained in the concentric tracks on and off gimbal. As the gimbal rotates, the loop seats onto one guiding track and peels off of the other guiding track while always maintaining its U shape.

Abstract: A ceramic element, e.g., a sapphire dome, is joined to a metallic element, e.g., a vehicle body comprising a titanium alloy, by an attachment structure, e.g., comprising niobium. The attachment structure comprises: (1) a form-factored, compliant metallic transition element having a “C” shape; (2) a first joint material connecting an upper portion of the transition element to the ceramic element; and (3) a second joint material connecting a lower portion of the transition element to the metallic element. A method is provided for attaching the ceramic element to the metallic element, using a single brazing operation. The presence of the attachment structure further minimizes the stresses related to the different coefficients of thermal expansion in the ceramic/attachment/titanium connection.

Abstract: A missile has a body with a substantially circular nose opening therein, and a ceramic radome sized to cover the nose opening. A compliant metallic circular "T"-flexure element is disposed structurally between the radome and the body and is integral with the body. A niobium-containing washer is disposed between the radome and the "T"-flexure element. The "T"-flexure element includes an elongated compliant arm region and a cross bar region positioned adjacent the radome such that the niobium-containing washer is situated between a lower margin surface of the radome and an upper side of the crossbar region. A first brazed butt joint is formed between the lower margin surface of the radome and an upper surface of the niobium-containing washer, while a second brazed butt joint is formed between a lower surface of the niobium-containing washer and the crossbar region of the "T"-flexure element.

Abstract: A rolling gimbal harness for interconnecting between a gimbal mounted electronics assembly and a near gimbal electronics assembly in an airborne missile. The harness negotiates the dynamic range of the gimbal while exerting very little spring torque and friction. The harness is a flat ribbon of many shielded twisted wire pairs embedded in a highly flexible insulation material. The twisted wire pairs are terminated in very small connectors with pins having 0.025 spacing. The harness includes a pre-formed arcuate region which follows a circumferential path defined by the periphery of the gimbal platform.

Abstract: An umbilical release mechanism (10) for disconnecting an electrical umbilical (14, 16) extending between a host and a releasable vehicle accomplishes the disconnection without imparting any force to the releasable vehicle, and without leaving pieces of the disconnection mechanism (10) in the releasable vehicle. The umbilical release mechanism (10) includes an umbilical connector (12) in which two electrical harness connectors (22, 24) are releasably clamped together, with an intermediate plate (28) using a mat (32) of electrically conductive wires to complete the electrical conduction path between the harness connectors (22, 24). A pair of backing plates (34, 36) having a clamping bore (38) therethrough capture the harness connectors (22, 24) therebetween. A clamping force is releasably applied to the backing plates (34, 36) by engaging a hollow outer shaft (40) through the clamping bore (38), and reacting a clamping force on the backing plates (34, 36) through the outer shaft (40).