초록 ▼

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 desi

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.

대표청구항 ▼

1. A method of repairing an area in a composite structure, the method comprising: generating electronic data defining first boundaries of the area;using the electronic data to calculate second boundaries of a cutout in the composite structure encompassing the area;removing the cutout from the compos

1. A method of repairing an area in a composite structure, the method comprising: generating electronic data defining first boundaries of the area;using the electronic data to calculate second boundaries of a cutout in the composite structure encompassing the area;removing the cutout from the composite structure;designing a repair for the area, including designing a component to restore the composite structure within the cutout; and,installing the component within the cutout. 2. The method of claim 1, wherein generating the electronic data includes: using an energy beam to select points along the first boundaries of the area, and determining corresponding 3-D locations of the points in a coordinate system of the composite structure. 3. The method of claim 1, further comprising: electronically generating a visual model of the composite structure; anddisplaying the second boundaries of the cutout on the visual model. 4. The method of claim 1, wherein designing the repair includes: generating at least a first computer graphics display of a plurality of selectable repair components and selectable values for each of the plurality of selectable repair components, and using the computer graphics display to select the component and a value for the component. 5. The method of claim 4, further comprising: using a computer to perform an analysis of the repair based on the component and the value. 6. The method of claim 5, further comprising: generating a second computer graphics display of a plurality of selectable types of analyses and selectable conditions the selectable types of analyses, using the second computer graphics display to select at least one analysis to be performed and conditions for the at least one analysis. 7. The method of claim 1, wherein designing the repair includes using a programmed computer to generate a pattern of fasteners used to install the repair on the composite structure. 8. The method of claim 7, wherein generating the pattern includes generating a set of electronic data defining corresponding 3-D locations of the fasteners in the pattern in a coordinate system of the composite structure, wherein the method further includes: projecting the pattern onto the composite structure. 9. The method of claim 1, further comprising: using a programmed computer to generate and send an order to at least one vendor for the component. 10. A method of repairing an area in a composite fuselage of an aircraft, comprising: locating first boundaries of the area in a coordinate system of the aircraft;determining second boundaries of a cutout in the composite fuselage to be used for the repair:using a programmed computer to automatically design a set of repair components based on the second boundaries of the cutout;removing the cutout from the composite fuselage; and,installing the set of repair components in the repair area. 11. The method of claim 10, wherein: removing the cutout includes removing a section of skin of the composite fuselage and removing a structural component attached to the skin, and locating the first boundaries of the area includes locating each of a plurality of points on the skin of the composite fuselage, wherein the plurality of points indicate an outline of the first boundaries of the area. 12. The method of claim 11, wherein determining the second boundaries of the cutout is based on the plurality of points, and includes determining a location of the structural component attached to the skin in the area. 13. The method of claim 10, wherein: determining the second boundaries of the cutout includes identifying frame members and stingers attached to a skin of the composite fuselage in the area, and removing the cutout includes removing at least portions of identified stringers and frames. 14. The method of claim 10, wherein automatically designing the set of repair components includes identifying parameters related to a set of fasteners used to fasten the set of repair components to the composite fuselage. 15. The method of claim 14, wherein installing the set of repair components includes: generating a fastener pattern, and using a laser to project the fastener pattern onto a skin of the composite fuselage. 16. The method of claim 10, wherein determining the second boundaries of the cutout includes: retrieving a model of the composite fuselage, converting coordinates of located points defining the first boundaries of the area into a coordinate system of the model, and using converted coordinates of the located points to locate the first boundaries of the area on the model. 17. The method of claim 11, wherein locating the plurality of points includes: projecting a laser beam onto the plurality of points on the skin of the composite fuselage, and determining corresponding locations of the plurality of points on the skin within the coordinate system of the aircraft. 18. A system used in repairing an area in a composite body of a vehicle, comprising: means for generating electronic data defining first boundaries of an area on a skin of the composite body; and,a computer including a software program configured to calculate second boundaries of a cutout in the composite body encompassing the area using the electronic data, and for designing a set of repair components for installation in the cutout. 19. The system of claim 18, wherein; the computer includes a graphical user interface (GUI), and a screen display produced by the software program and displayed by the GUI, the screen display including a plurality of selectable repair components and selectable values for each of the plurality of selectable repair components. 20. The system of claim 19, wherein the screen display includes a plurality of selectable types of analyses and selectable conditions for the plurality of selectable types of analyses. 21. The system of claim 18, wherein the means for generating the electronic data includes means for projecting a beam onto a surface of the composite body. 22. The system of claim 18, further comprising: means for projecting a fastener pattern onto a surface of the body. 23. A system used in repairing an area in a fuselage of an aircraft, comprising: a laser device configured to locate a plurality of points on a skin of the fuselage, the plurality of points indicating first boundaries of the area in a 3-D coordinate system of the aircraft;a database including a 3-D model of the fuselage;a computer coupled with the database, wherein the computer is configured to convert the location of the points on the skin into the coordinate system of the model and to determine second boundaries of a cutout in the fuselage required to repair the area;a graphical user interface coupled with the computer, wherein the graphical user interface is configured to display first boundaries of the area on the model and to produce a screen display including a plurality of selectable repair components and selectable values for each of the plurality of selectable repair components;a software program used by the computer to design repair components for the area based on the second boundaries of the cutout, and to produce a pattern of fasteners used to fasten the repair components to the fuselage; anda laser device configured to project the fastener pattern onto a surface of the skin. 24. A method of repairing an area in a composite fuselage of an aircraft, comprising: using a laser to locate each of a plurality of points on a skin of the composite fuselage, wherein the plurality of points indicate first boundaries of the area in a 3-D coordinate system of the aircraft;generating a display of a model of the composite fuselage showing the first boundaries of the area relative to frame members and stringers in the area;determining second boundaries of a cutout in the composite fuselage required for the repair based on the plurality of points;generating a display of a model of the composite fuselage showing the second boundaries of the cutout relative to the frame members and the stringers in the area;using a programmed computer to automatically design a set of repair components based on the second boundaries of the cutout, including to generate a first screen display of a plurality of selectable repair components and selectable values for each of the plurality of selectable repair components used to repair the area, and to generate a second screen display of selectable types of analyses and selectable conditions for each of the selectable types of analyses;fabricating the set of repair components; andinstalling the set of repair components in the area of the cutout.