Abstract: A gas dispersion shield and method for protecting the bottom surface of a gas deposition chamber, while injecting gas from a gas insertion channel into the chamber at a non-vertical angle. The gas dispersion shield includes a cylindrically shaped vertical sidewall, an annular flange extending horizontally and outwardly from the sidewall upper end, and a horizontal wall that extends inwardly from the sidewall lower end. The flange includes a top surface, a bottom surface, and a plurality of holes formed through the flange each extending in a non-vertical direction from the bottom surface to the top surface. The bottom surface includes an annular protrusion that fits at least partially into the gas insertion channel, to ensure the gas flows through the non-vertical holes instead of escaping around the flange.

Abstract: A gas dispersion shield and method for protecting the bottom surface of a gas deposition chamber, while injecting gas from a gas insertion channel into the chamber at a non-vertical angle. The gas dispersion shield includes a cylindrically shaped vertical sidewall, an annular flange extending horizontally and outwardly from the sidewall upper end, and a horizontal wall that extends inwardly from the sidewall lower end. The flange includes a top surface, a bottom surface, and a plurality of holes formed through the flange each extending in a non-vertical direction from the bottom surface to the top surface. The bottom surface includes an annular protrusion that fits at least partially into the gas insertion channel, to ensure the gas flows through the non-vertical holes instead of escaping around the flange.

Abstract: A lightweight composite fairing bar (14) for use in fabricating a composite component (16) of an aircraft. The fairing bar (14) includes a core (18) and an elongated outer shell (20) surrounding the core (18). The outer shell (20) is comprised of a laminate material, and the core (18) is comprised of epoxy syntactic foam having a lower density than that of the laminate material. The outer shell (20) is configured for supporting the composite component (16) during the manufacture of the same.

Abstract: A gas dispersion shield and method for protecting the bottom surface of a gas deposition chamber, while injecting gas from a gas insertion channel into the chamber at a non-vertical angle. The gas dispersion shield includes a cylindrically shaped vertical sidewall, an annular flange extending horizontally and outwardly from the sidewall upper end, and a horizontal wall that extends inwardly from the sidewall lower end. The flange includes a top surface, a bottom surface, and a plurality of holes formed through the flange each extending in a non-vertical direction from the bottom surface to the top surface. The bottom surface includes an annular protrusion that fits at least partially into the gas insertion channel, to ensure the gas flows through the non-vertical holes instead of escaping around the flange.

Abstract: A lightweight composite fairing bar (14) for use in fabricating a composite component (16) of an aircraft. The fairing bar (14) includes a core (18) and an elongated outer shell (20) surrounding the core (18). The outer shell (20) is comprised of a laminate material, and the core (18) is comprised of epoxy syntactic foam having a lower density than that of the laminate material. The outer shell (20) is configured for supporting the composite component (16) during the manufacture of the same.

Abstract: A method for determining a condition of the laser system includes determining a change in a laser current from an initial value. A method for measuring a laser current includes determining a difference between the values of a power supply current, which is the value of the laser current. A method for measuring a transmitted power includes generating a first control signal that sets a magnitude of a bias current supplied to a laser, generating a second control signal that sets a of a modulation current supplied to the laser, and determining a difference between values of a high and a low transmitted powers. A method for measuring a received optical power includes determining a received OMA corresponding to the power signal, which is the transmitted OMA minus a known loss through a calibration fiber that couples the laser transmitter to the laser receiver.

Abstract: An aircraft part manufacturing device for automated composite lay up includes a mandrel tool having a an interior mandrel surface that conforms to an outside mold line (OML) of a part: to be manufactured. One or more circular rings surround the mandrel and are attached to the mandrel. The circular rings rotate supported by bearings in a bearing cradle so that the mandrel rotates concentrically with the circular rings about an axis of rotation passing through the center of the circular rings. Multiple composite material delivery heads simultaneously deliver material directly to the outside mold line on the interior mandrel surface while the mandrel is rotated. A cantilever supported gantry beam supports the material delivery heads inside the interior mandrel surface. A connecting mechanism connects the material delivery heads to the gantry beam and provides motion of the material delivery heads relative to the interior mandrel surface.

Abstract: A healthcare revenue cycle management analytics system enables healthcare business professionals to perform multidimensional data analysis without the assistance of IT or analyst intermediaries. The system provides a user interface which presents views selectable by a user from a plurality of built-in views relevant to healthcare revenue cycle management. The system further provides a user interface having a tree-like filter made up of numerous relevant dimensions and members of target data sources for highly granular control over the data populating the built-in revenue cycle visualizations. The system further allows healthcare business professionals to access healthcare revenue cycle management data over the Internet, via a web services approach.

Abstract: A method for determining a condition of the laser system includes determining a change in a laser current from an initial value. A method for measuring a laser current includes determining a difference between the values of a power supply current, which is the value of the laser current. A method for measuring a transmitted power includes generating a first control signal that sets a magnitude of a bias current supplied to a laser, generating a second control signal that sets a of a modulation current supplied to the laser, and determining a difference between values of a high and a low transmitted powers. A method for measuring a received optical power includes determining a received OMA corresponding to the power signal, which is the transmitted OMA minus a known loss through a calibration fiber that couples the laser transmitter to the laser receiver.

Abstract: An aircraft part manufacturing device for automated composite lay up includes a mandrel tool having a an interior mandrel surface that conforms to an outside mold line (OML) of a part: to be manufactured. One or more circular rings surround the mandrel and are attached to the mandrel. The circular rings rotate supported by bearings in a bearing cradle so that the mandrel rotates concentrically with the circular rings about an axis of rotation passing through the center of the circular rings. A composite material delivery head delivers material directly to the outside mold line on the interior mandrel surface while the mandrel is rotated. A cantilever supported gantry beam supports the material delivery head inside the interior mandrel surface. A connecting mechanism connects the material delivery head to the gantry beam and provides motion of the material delivery head relative to the interior mandrel surface.

Abstract: An aircraft part manufacturing device for automated composite lay up includes a mandrel tool having a an interior mandrel surface that conforms to an outside mold line (OML) of a part: to be manufactured. One or more circular rings surround the mandrel and are attached to the mandrel. The circular rings rotate supported by bearings in a bearing cradle so that the mandrel rotates concentrically with the circular rings about an axis of rotation passing through the center of the circular rings. Multiple composite material delivery heads simultaneously deliver material directly to the outside mold line on the interior mandrel surface while the mandrel is rotated. A cantilever supported gantry beam supports the material delivery heads inside the interior mandrel surface. A connecting mechanism connects the material delivery heads to the gantry beam and provides motion of the material delivery heads relative to the interior mandrel surface.