System for analysis of a repair for a structure

Patent metadata

Field	Value
Publication number	US-10275564-B2
Application number	US-201615186200-A
Country	US
Kind code	B2
Filing date	Jun 17, 2016
Priority date	Jun 17, 2016
Publication date	Apr 30, 2019
Grant date	Apr 30, 2019

Abstract

An apparatus is provided for analysis of a repair for a structure by identifying component parts of the structure that have common material properties and geometric constraints, and based thereon determining a generic repair component for the component parts that also have the common material properties and the geometric constraints. A set of loads are extracted from a loads model of the undamaged structure and redistributed in a loads redistribution model at a damaged or defective portion of the component part. The set of redistributed loads indicate loading incurred by the generic repair component under an external load. The apparatus then uses the redistributed loads to perform an analysis to determine a margin of safety of the generic repair component and, in instances in which the margin of safety is positive, outputs the material properties and geometric constraints of the generic repair component to a fabrication system for production thereof.

First claim

What is claimed is:

1. An apparatus for analysis of a repair for a structure including component parts, the apparatus comprising a processor and a memory storing executable instructions that, in response to execution by the processor, cause the apparatus to at least:
identify a plurality of component parts of the structure that have common material properties and common geometric constraints, and that are identified from a lay-up design of the structure;
determine a generic repair component for the plurality of the component parts to repair the plurality of the component parts, the generic repair component having the common material properties and the common geometric constraints; and for a component part of the plurality of component parts,
determine a second generic repair component for the plurality of the component parts, including being caused to at least:
determine a material property or a geometric constraint having a negative impact on the margin of safety; and
determine the second generic repair component having the common material properties and the common geometric constraints, excluding the material property or the geometric constraint having the negative impact on the margin of safety, the second generic repair component being different from the first generic repair component;

extract a set of loads from a loads model of the structure, the loads model representing the structure in an undamaged state;
redistribute the set of extracted loads using a loads redistribution model in which a representation of a damaged or defective portion of the component part is replaced or coupled with a representation of the generic repair component, the set of extracted loads thereby being a set of redistributed loads that indicate loading incurred by the generic repair component under external loads applied to the loads model;
perform an analysis using the set of redistributed loads to determine a margin of safety for the generic repair component under the set of extracted loads; and in at least one instance in which the margin of safety is positive,
output the common material properties and geometric constraints of the generic repair component of the at least one instance to a fabrication system for production thereof, the generic repair component being suitable for repairing the component part.

2. The apparatus of claim 1 , wherein the apparatus being caused to determine the generic repair component includes being caused to determine a plurality of generic repair components each of which has the common material properties and the common geometric constraints, the generic repair component being a user-selected one of the plurality of generic repair components.

3. The apparatus of claim 1 , wherein the apparatus being caused to determine the generic repair component includes being caused to determine a bolted or bonded repair that is suitable for replacing or coupling the damaged or defective portion of the component part with the generic repair component.

4. The apparatus of claim 1 , wherein the memory stores further executable instructions that, in response to execution by the processor and in at least one instance in which the margin of safety is negative, cause the apparatus to further at least:
for the component part of the plurality of component parts,
extract a second set of loads from the loads model of the structure;
redistribute the second set of extracted loads using a second loads redistribution model in which the representation of the damaged or defective portion of the component part is replaced or coupled with a representation of the second generic repair component; and
perform an analysis using the second set of redistributed loads.

5. The apparatus of claim 1 , wherein the common material properties include a material type, skin structure, or stiffness, and the common geometric constraints include a doubler geometry, bolt and bolt pattern geometry, or pad-up geometry.

6. The apparatus of claim 1 , wherein in at least one instance, the structure includes an aircraft, the plurality of the component parts include a plurality of stringers, and the generic repair component includes a bolted hat section formed of carbon-fiber-reinforced plastic (CFRP).

7. A method of producing a generic repair component for a repair for a structure including component parts, the method comprising:
identifying a plurality of component parts of the structure that have common material properties and common geometric constraints, and that are identified from a lay-up design of the structure;
determining a generic repair component for the plurality of the component parts to repair the plurality of the component parts, the generic repair component having the common material properties and the common geometric constraints; and for a component part of the plurality of component parts,
determining a second generic repair component includes: determining a material property or a geometric constraint having a negative impact on the margin of safety; and determining the second generic repair component having the common material properties and the common geometric constraints, excluding the material property or the geometric constraint having the negative impact on the margin of safety, the second generic repair component being different from the first generic repair component;

extracting a set of loads from a loads model of the structure, the loads model representing the structure in an undamaged state; redistributing the set of extracted loads using a loads redistribution model in which a representation of a damaged or defective portion of the component part is replaced or coupled with a representation of the generic repair component, the set of extracted loads thereby being a set of redistributed loads that indicate loading incurred by the generic repair component under external loads applied to the loads model; performing an analysis using the set of redistributed loads to determine a margin of safety for the generic repair component under the set of extracted loads; and in at least one instance in which the margin of safety is positive, outputting the common material properties and geometric constraints of the generic repair component of the at least one instance to a fabrication system for production thereof, the generic repair component being suitable for repairing the component part; and producing the generic repair component by the fabrication system before repairing the component part.

8. The method of claim 7 , wherein determining the generic repair component includes determining a plurality of generic repair components each of which has the common material properties and the common geometric constraints, the generic repair component being a user-selected one of the plurality of generic repair components.

9. The method of claim 8 , wherein in at least one instance, the structure includes an aircraft, the plurality of the component parts include a plurality of stringers, and the generic repair component includes a bolted hat section formed of carbon-fiber-reinforced plastic (CFRP).

10. The method of claim 7 , wherein determining the generic repair component for the plurality of the component parts includes determining a bolted or bonded repair that is suitable for replacing or coupling the damaged or defective portion of the component part with the generic repair component.

11. The method of claim 7 further comprising, in at least one instance in which the margin of safety is negative: for the component part of the plurality of component parts, extracting a second set of loads from the loads model of the structure; redistributing the second set of extracted loads using a second loads redistribution

Assignees

• Boeing Co

Inventors

• Ridgeway Larry Dean
• Oakes Gary D
• Krishnaswamy Pradeep
• Staal Remmelt Andrew

Classifications

• G06F30/20

  Design optimisation, verification or simulation (optimisation, verification or simulation of circuit designs G06F30/30) · CPC title

• G06F30/15 Primary

  Vehicle, aircraft or watercraft design · CPC title

• G06F2113/28

  Fuselage, exterior or interior · CPC title

• G06F2113/26

  Composites · CPC title

• G06F30/23

  using finite element methods [FEM] or finite difference methods [FDM] · CPC title