Abstract: A system for determining an optimal clocking orientation of an object at which to attach mating structure to the object includes a plurality of radiation devices, a plurality of transceivers, and a processor. The radiation devices are mounted on the object which has an as-designed object configuration. The transceivers are configured to generate distance measurements between the transceivers and the radiation devices at different clocking orientations of the object. The processor is configured to determine, based on the distance measurements, as-built object configurations corresponding to the different clocking orientations of the object. The processor is configured to compare the as-built object configurations to the as-designed object configuration and determines an optimal clocking orientation at which the as-built object configuration has the smallest deviation from the as-designed object configuration.

Abstract: A system for determining an optimal clocking orientation of an object at which to attach mating structure to the object includes a plurality of radiation devices, a plurality of transceivers, and a processor. The radiation devices are mounted on the object which has an as-designed object configuration. The transceivers are configured to generate distance measurements between the transceivers and the radiation devices at different clocking orientations of the object. The processor is configured to determine, based on the distance measurements, as-built object configurations corresponding to the different clocking orientations of the object. The processor is configured to compare the as-built object configurations to the as-designed object configuration and determines an optimal clocking orientation at which the as-built object configuration has the smallest deviation from the as-designed object configuration.

Abstract: A system for determining an optimal clocking orientation of an object at which to attach mating structure to the object includes a plurality of radiation devices mounted on an object, a plurality of transceivers configured to emit radiation toward the object, and a processor. The object potentially has a first as-built object configuration that differs from an as-designed object configuration. The transceivers continuously generate distance measurements between the transceivers and the radiation devices during rotation of the object. The processor continuously determines, based on the distance measurements, additional unique as-built object configurations corresponding to changing clocking orientations of the object during rotation.

Abstract: Methods and systems for monitoring an integrity of electrical connectivity between a repair patch and a parent structure include providing the repair patch with an embedded sensor configured to detect electrical conductivity. The repair patch includes a ply of conductive material that overlaps a portion of a conductive layer of the parent structure. A baseline set of sensor data is acquired from the sensor indicative of an electrical connectivity between the ply of conductive material of the repair patch and the conductive layer of the parent structure. One or more additional sets of data may be obtained from the sensor and compared to the baseline set of data to determine an integrity of the electrical connectivity between the ply of conductive material of the repair patch and the conductive layer of the parent structure.

Abstract: An edge stabilizer for a composite structure includes an elongate edge support segment, defining a geometric shape of an edge of the composite structure, and a connector, configured to attach the edge support segment to the edge of the composite structure. The edge support segment comprises first and second halves configured to attach together around the edge, each half including a shoulder, opposing mating relationship of the shoulders defining a slot for receiving the edge. The edge stabilizer can be part of a system for stabilizing an edge of a composite barrel section. The system can also include a moveable cart, the barrel section being supportable upon the cart.

Abstract: A system for determining an optimal clocking orientation of an object at which to attach mating structure to the object includes a plurality of radiation devices mounted on an object, a plurality of transceivers configured to emit radiation toward the object, and a processor. The object potentially has a first as-built object configuration that differs from an as-designed object configuration. The transceivers continuously generate distance measurements between the transceivers and the radiation devices during rotation of the object. The processor continuously determines, based on the distance measurements, additional unique as-built object configurations corresponding to changing clocking orientations of the object during rotation.

Abstract: A barrel assembly for a composite structure includes a barrel of composite material, a first end ring, and a mid support. The barrel of composite material has a first end, an interior surface and an outer surface, and the first end ring is removably attached to the first end. The first end ring has a perimeter that is substantially congruent with the first end, and is configured to maintain a shape of the barrel. The mid support is removably disposed within the barrel, and has a plurality of spokes extending outwardly from a central hub to contact the interior surface, to maintain a shape of the barrel.

Abstract: A system comprising: a parent structure made of composite material and having a repair site; a repair patch made of composite material, the repair patch being bonded to the parent structure at the repair site; and a sensor embedded in the repair patch. The system may further comprise non-volatile memory and an interface unit embedded in the repair patch and electrically connected to the sensor. In one embodiment, the sensor is a loop-shaped sensor comprising an electrically conductive structure having an electrical conductivity that varies as a function of a pressure exerted on the repair patch. In another embodiment, the sensor comprises a sensor chip having nonvolatile memory. In a further embodiment, the sensor comprises an optical fiber that is sensitive to changes in pressure on or strain in the repair patch.

Abstract: Methods and systems for monitoring an integrity of electrical connectivity between a repair patch and a parent structure include providing the repair patch with an embedded sensor configured to detect electrical conductivity. The repair patch includes a ply of conductive material that overlaps a portion of a conductive layer of the parent structure. A baseline set of sensor data is acquired from the sensor indicative of an electrical connectivity between the ply of conductive material of the repair patch and the conductive layer of the parent structure. One or more additional sets of data may be obtained from the sensor and compared to the baseline set of data to determine an integrity of the electrical connectivity between the ply of conductive material of the repair patch and the conductive layer of the parent structure.

Abstract: A method including placing first and second measurement devices proximate first and second aircraft doors, respectively, and determining a first position of the second measurement device relative to a second position of the first measurement device. The method includes placing first and second pluralities of reflective devices inside the aircraft proximate the first and second doors, respectively. The method includes measuring first and second distances from the first and second measurement devices to the first and second pluralities of reflective devices, respectively, and measuring second distances from the second measurement device to the second plurality of reflective devices. Based on a determined position of the second measurement device and further based on the first distances and second distances, third distances are determined between each of the first and second pluralities of reflective devices. The third distances provide a measurement baseline for points on a fuselage and wings.

Abstract: A method including placing first and second measurement devices proximate first and second aircraft doors, respectively, and determining a first position of the second measurement device relative to a second position of the first measurement device. The method includes placing first and second pluralities of reflective devices inside the aircraft proximate the first and second doors, respectively. The method includes measuring first and second distances from the first and second measurement devices to the first and second pluralities of reflective devices, respectively, and measuring second distances from the second measurement device to the second plurality of reflective devices. Based on a determined position of the second measurement device and further based on the first distances and second distances, third distances are determined between each of the first and second pluralities of reflective devices. The third distances provide a measurement baseline for points on a fuselage and wings.

Abstract: Systems and methods for providing interactive production illustration information are provided. One system includes a machine vision system configured to attach to a user, wherein the machine vision system when attached to the user is aligned with a line of sight of the user towards a physical location. The machine vision system controllable by the user and configured to acquire an image of an article. The system also includes an interactive production illustration system coupled to the machine vision system, wherein the interactive production illustration system has stored therein interactive production illustration. The interactive production illustration system is configured to select interactive production illustration information for an assembly process for the article at the physical location based at least in part on the acquired image.

Abstract: A method for monitoring structural integrity of a repaired aircraft component made of composite material. The method comprises: (a) placing a multiplicity of plies of repair composite material over a repair site on the component with a sensor disposed between two plies; (b) curing the plies of repair composite material so that the repair composite material, with the sensor embedded therein, is bonded to the repair site; (c) acquiring first sensor data from the sensor before a flight of the aircraft; (d) acquiring second sensor data from the sensor during or after the flight; (e) comparing the first sensor data to the second sensor data; (f) identifying differences between the first and second sensor data indicative of structural change; and (g) determining whether the identified differences indicate structural change in excess of a specified threshold. Steps (c) through (g) are performed by a computer system.

Abstract: A barrel assembly for a composite structure includes a barrel of composite material, a first end ring, and a mid support. The barrel of composite material has a first end, an interior surface and an outer surface, and the first end ring is removably attached to the first end. The first end ring has a perimeter that is substantially congruent with the first end, and is configured to maintain a shape of the barrel. The mid support is removably disposed within the barrel, and has a plurality of spokes extending outwardly from a central hub to contact the interior surface, to maintain a shape of the barrel.

Abstract: A barrel assembly for a composite structure includes a barrel of composite material, a first end ring, and a mid support. The barrel of composite material has a first end, an interior surface and an outer surface, and the first end ring is removably attached to the first end. The first end ring has a perimeter that is substantially congruent with the first end, and is configured to maintain a shape of the barrel. The mid support is removably disposed within the barrel, and has a plurality of spokes extending outwardly from a central hub to contact the interior surface, to maintain a shape of the barrel.

Abstract: A barrel assembly for a composite structure includes a barrel of composite material, a first end ring, and a mid support. The barrel of composite material has a first end, an interior surface and an outer surface, and the first end ring is removably attached to the first end. The first end ring has a perimeter that is substantially congruent with the first end, and is configured to maintain a shape of the barrel. The mid support is removably disposed within the barrel, and has a plurality of spokes extending outwardly from a central hub to contact the interior surface, to maintain a shape of the barrel.

Abstract: A method is provided for assessing accuracy of positioning a NC machine having a spindle that is movable along each of at least two mutually orthogonal translational axes. The method Includes creating a master flame of reference relative to the translational axes by moving the machine along first and second translational axes. For each translational axis, coordinates of a target mounted adjacent the spindle are determined at a number of points along the respective translational axis. A linear fit of the coordinates is then calculated so as to create a set of mutually orthogonal axes defining the master frame of reference. Accuracy of positioning the machine in the master frame of reference is checked by positioning the spindle at a number of locations, measuring the coordinates of the target for each location, and determining errors in positioning of the machine by based upon the measured coordinates and machine-determined coordinates.

Abstract: Positioning errors of a numerically controlled machine and a fixture are related through a mathematical model to the statistical total error in the position of the machine tool, and maximum allowable amounts are assigned for each of the individual contributing factors to the total error. The relationship between the machine and fixture is checked by a probe mounted in the machine spindle. Functioning and alignment of the probe are checked with the probe. Global positioning accuracy of the machine is checked throughout a working envelope of the machine using a laser measuring instrument. A master coordinate system relative to the ways of the machine is created within the laser instrument by calculating a linear fit of machine position coordinates acquired as the machine is moved along each of two perpendicular axes of the machine, and the master coordinate system is used for the global accuracy and fixture accuracy checks.

Abstract: Polychlorinated biphenyls are removed from oil by extracting the biphenyls into methanol. The mixture of methanol and extracted biphenyls is distilled to separate methanol therefrom, and the methanol is recycled for further use in extraction of biphenyls from oil.