Multi-scale modeling of composite structures

• US 8,862,437 B1
• Filed: 03/30/2010
• Issued: 10/14/2014
• Est. Priority Date: 03/30/2010
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Rassaian, Mostafa, Gosse, Jonathan Henry, Christensen, Stephen
• Primary Examiner(s): Lo, Suzanne
• Application Number:
  US12/749,594
• Time in Patent Office: 1,659 Days
• Field of Search: 703/6
• US Class Current: 703/1
• CPC Class Codes: G06F 2113/26 Composites
• CPC Class Codes: G06F 30/15 Vehicle, aircraft or watercraft design
• CPC Class Codes: G06F 30/20 Design optimisation, verification or simulation optimisation, verification or simulation of circuit designs G06F30/30

Abstract

A method, apparatus, and computer program product are present for creating a composite structure. A number of characteristics for a number of components for the composite structure is obtained from a simulation of the composite structure using a model of the composite structure. A number of changes in the number of characteristics needed to meet a desired level of performance for the number of characteristics is ascertained. A number of attributes for a number of composite materials used to form the number of components corresponding to the number of characteristics having the number of changes is identified. The number of attributes for the number of composite materials for the number of characteristics having the number of changes based on the desired level of performance is changed.

Claims

1. A method for creating a composite structure and reducing an amount of time to certify an aircraft manufactured with the composite structure, the method comprising:

a computer obtaining a number of characteristics for a number of components for the composite structure from a simulation of the composite structure using a model of the composite structure;

the computer ascertaining a number of changes in the number of characteristics needed to meet a desired level of performance for the number of characteristics;

the computer identifying a number of attributes for a number of composite materials used to form the number of components corresponding to the number of characteristics having the number of changes;

the computer changing the number of attributes for the number of composite materials for the number of characteristics having the number of changes based on the desired level of performance, wherein the computer changing the number of attributes further comprises;

the computer identifying the number of attributes in which changes to the number of attributes cause changes to the number of characteristics to increase a level of performance towards the desired level of performance;

the computer changing the number of attributes to cause the number of characteristics to increase a level of performance towards the desired level of performance; and

the computer changing at least an amount of resin in the number of composite materials,

the computer performing the simulation using the model of the composite structure;

the computer receiving first results from the simulation, wherein the first results include a first performance of the composite structure in the simulation;

the computer determining whether the first performance of the composite structure is acceptable;

the computer, responsive to a determination that the first performance of the composite structure is acceptable, selecting a physical object of the composite structure for physical testing;

the computer receiving second results from the physical testing, wherein the second results include a second performance of the physical object in the physical testing; and

the computer comparing at least one first result from the first results and at least one second result from the second results to validate a composition of the composite structure, whereby the amount of time to certify the aircraft is reduced.

2. The method of claim 1, wherein the composite structure is selected from one of a fuselage, a portion of the fuselage, an engine inlet, a wing, a stabilizer, a strut, and a fairing.

3. An apparatus comprising:

a bus;

a memory containing program code;

and a processor unit configured to run the program code to;

obtain a number of characteristics for a number of components for a composite structure from a simulation of the composite structure using a model of the composite structure;

ascertain a number of changes in the number of characteristics needed to meet a desired level of performance for the number of characteristics

identify a number of attributes for a number of composite materials used to form the number of components corresponding to the number of characteristics having the number of changes; and

change the number of attributes for the number of composite materials for the number of characteristics having the number of changes based on the desired level of performance, the number of characteristics comprising at least an amount of resin in the number of composite materials;

perform the simulation using the model of the composite structure;

receive first results from the simulation, wherein the first results include a first performance of the composite structure in the simulation;

determine whether the first performance of the composite structure is acceptable; and

select, responsive to a determination that the first performance of the composite structure is acceptable, a physical object of the composite structure for physical testing;

receive second results from the physical testing, wherein the second results include a second performance of the physical object in the physical testing; and

comparing at least one first result from the first results to at least one second result from the second results to validate a composition of the composite structure, whereby the amount of time to certify the aircraft is reduced.

4. The apparatus of claim 3, wherein the composite structure is selected from one of a fuselage, a portion of the fuselage, an engine inlet, a wing, a stabilizer, a strut, and a fairing.