Repairing Composite Structures
AssigneeThe Boeing Company
InventorLawrence S. Lindgren
Life of this patent
Estimating the term…
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.
Claims25
A method of repairing an area in a composite structure, comprising:
- generating electronic data defining the boundaries of the area;
- using the electronic data to calculate the 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 components to restore the composite structure within the cutout;
- and,
- installing the components within the cutout.
A method of repairing an area in a composite fuselage of an aircraft, comprising:
- locating boundaries of the area in a coordinate system of the aircraft;
- determining the boundaries of a cutout in the fuselage required for the repair;
- using a programmed computer to automatically design a set of repair components based on the boundaries of the cutout;
- removing the cutout from the fuselage;
- and,
- installing the repair components in the repair area.
A system used in repairing an area in a composite body of a vehicle, comprising:
- means for generating electronic data defining the boundaries of area on a skin of the body;
- and,
- a computer including a software program for calculating the boundaries of a cutout in the body encompassing the area using the electronic data, and for designing a set of repair components for installation in the cutout.
A system used in repairing an area in the fuselage of an aircraft, comprising:
- a laser device for locating a plurality of points on the skin of the fuselage generally defining the boundaries of the area in a 3-D coordinate system of the aircraft;
- a data base including a 3-D model of the fuselage;
- a computer coupled with the database for converting the location of the points on the skin into the coordinate system of the model and for determining the boundaries of a cutout in the fuselage required to repair the area;
- a graphical user interface coupled with the computer for displaying boundaries of the area on the model and for producing a screen display including a plurality of selectable repair components and selectable values for each of the components used to repair the area;
- a software program used by the computer to design repair components for the area based on the boundaries of the cutout, and for producing a pattern of fasteners used to fasten the repair components to the fuselage;
- and
- a laser device for projecting the fastener pattern onto the surface of the skin.
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 the skin of the fuselage generally outlining the boundaries of the area in a 3-D coordinate system of the aircraft;
- generating a display of a model of the fuselage showing the boundaries of the area relative to frame members and stringers in the area;
- determining the boundaries of a cutout in the fuselage required for the repair based on the located points;
- generating a display of a model of the fuselage showing the boundaries of the cutout relative to frame members and stringers in the area;
- using a programmed computer to automatically design a set of repair components based on the boundaries of the cutout, including generating a first screen display of a plurality of selectable repair components and selectable values for each of the components used to repair the area, and generating a second screen display of selectable types of analyses and selectable conditions for each of the analyses for analyzing a repair;
- fabricating the repair components;
- and
- installing the repair components in the area of the cutout.
Dependencies are inferred from the claim text.