Abstract: An apparatus for removing for removing an out-of-tolerance area in a composite structure may include a machine tool having a machine head movable along at least one axis over the composite structure. The machine tool may include at least one of a video camera and a non-destructive inspection (NDI) scanner mounted to the machine head for scanning the composite structure and locating the out-of-tolerance area. The machine tool may also include a cutting tool movable along a tool path for removing a volume containing the out-of-tolerance area. The machine tool may additionally include a controller that may be programmable with a quantity of layers of the volume for which the cutting tool is paused following removal of each one of the layers.

Abstract: A method and apparatus may be present for managing rework. A section in a platform having a number of composite materials needing a rework may be identified to form an identified section. A selected rework process to perform the rework of the identified section may be identified. The selected rework process may comprise a process to bond a patch to the identified section. A computer system may perform a simulation of the selected rework process to determine whether the selected rework process provides the rework for the identified section. The simulation may include a thermal analysis. The thermal analysis may take into account a number of structures associated with the identified section. The number of structures associated with the identified section may be located within a distance of the identified section such that the number of structures affect or are affected by bonding of the patch to the identified section.

Abstract: An apparatus for removing for removing an out-of-tolerance area in a composite structure may include a machine tool having a machine head movable along at least one axis over the composite structure. The machine tool may include at least one of a video camera and a non-destructive inspection (NDI) scanner mounted to the machine head for scanning the composite structure and locating the out-of-tolerance area. The machine tool may also include a cutting tool movable along a tool path for removing a volume containing the out-of-tolerance area. The machine tool may additionally include a controller that may be programmable with a quantity of layers of the volume for which the cutting tool is paused following removal of each one of the layers.

Abstract: A method of removing an out-of-tolerance area in a composite structure may comprise determining a location of the out-of-tolerance area within the composite structure, and selecting a volume of the composite structure to be removed based on the location of the out-of-tolerance area. The method may further include programming a machine tool to remove the volume and to pause after removal of each one of a quantity of layers of the volume. The method may additionally include removing one of the layers using the machine tool.

Abstract: A system and method for an automatic drawing comparison are disclosed. A batch capture processing module captures a plurality of pairs of drawing picture frames, and a drawing normalization module normalizes the pairs of drawing picture frames of the plurality to establish pairs of normalized drawing picture frames. A drawing comparison module compares each drawing picture frame of each of the respective pairs to generate respective drawing comparisons thereof, and a statistical data generator module communicates a statistical report identifying which of the respective drawing comparisons are recommended and not recommended for review.

Abstract: A plurality of RFIDs is installed on aircraft or other structure. The RFIDs can query one another upon original installation and in response to predetermined event detection, and determine their relative locations within a mesh. The determined location data and other information are stored within the respect memories of the RFIDs. The stored data can be later accessed and used in analyzing damage or structural failure of the aircraft. Corrective measures are thus expedited because before-and-after structural comparisons can be readily made, with or without reference to original engineering data for the aircraft.

Abstract: A method of removing an out-of-tolerance area in a composite structure may comprise determining a location of the out-of-tolerance area within the composite structure, and selecting a volume of the composite structure to be removed based on the location of the out-of-tolerance area. The method may further include programming a machine tool to remove the volume and to pause after removal of each one of a quantity of layers of the volume. The method may additionally include removing one of the layers using the machine tool.

Abstract: A composite structure containing an out-of-tolerance area is restored using an automated material removal method. The location of an out-of-tolerance area within the structure is determined by non-destructive inspection and a volume of the structure to be removed is selected based on the location of the out-of-tolerance area. An automatic material removal tool is programmed and used to remove the selected volume of material. The volume of removed material may be is replaced by an integrated patch.

Abstract: A method of removing an out-of-tolerance area in a composite structure comprises determining the location of the out-of-tolerance area and selecting a volume of the composite structure to be removed based on the location of the out-of-tolerance area. The method may further include programming a machine tool to remove the volume and to pause after removal of each one of a quantity of layers of the volume. The method may additionally include removing one of the layers using the programmed machine tool. The method may further include restoring the volume removed using the programmed area removal digital definition.

Abstract: The design for a repair of an area of a composite structure is at least partially automated. Electronic data defining the boundaries of the area is used to calculate the boundaries of a cutout in the composite structure encompassing the area. Components used to repair the area are automatically designed based on the location of the cutout. Following removal of the cutout, the repair components are installed.

Abstract: A composite structure containing an out-of-tolerance area is restored using an automated material removal method. The location of an out-of-tolerance area within the structure is determined by non-destructive inspection and a volume of the structure to be removed is selected based on the location of the out-of-tolerance area. An automatic material removal tool is programmed and used to remove the selected volume of material. The volume of removed material may be is replaced by an integrated patch.

Abstract: A method of removing an out-of-tolerance area in a composite structure comprises determining the location of the out-of-tolerance area and selecting a volume of the composite structure to be removed based on the location of the out-of-tolerance area. The method may further include programming a machine tool to remove the volume and to pause after removal of each one of a quantity of layers of the volume. The method may additionally include removing one of the layers using the programmed machine tool. The method may further include restoring the volume removed using the programmed area removal digital definition.

Abstract: A method and apparatus may be present for managing rework. A section in a location of a platform having a number of composite materials needing rework may be identified to form an identified section. A layup for the number of composite materials in the identified section of the platform may be determined. A patch for the identified section of the platform and the layup for the number of composite materials may be generated. A simulation may be performed of a selected rework process and the patch in the identified section.

Abstract: The design for a repair of an area of a composite structure is at least partially automated. Electronic data defining the boundaries of the area is used to calculate the boundaries of a cutout in the composite structure encompassing the area. Components used to repair the area are automatically designed based on the location of the cutout. Following removal of the cutout, the repair components are installed.

Abstract: a plurality of RFIDs is installed on aircraft or other structure. The RFIDs can query one another upon original installation and in response to predetermined event detection, and determine their relative locations within a mesh. The determined location data and other information are stored within the respect memories of the RFIDs. The stored data can be later accessed and used in analyzing damage or structural failure of the aircraft. Corrective measures are thus expedited because before-and-after structural comparisons can be readily made, with or without reference to original engineering data for the aircraft.