SYSTEM AND METHOD FOR OPTIMIZING COMPOSITE LAMINATE STRUCTURES

• US 20160052214A1
• Filed: 08/22/2014
• Published: 02/25/2016
• Est. Priority Date: 08/22/2014
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Gilbert, Anthony K., Nakhjavani, Omid B., Khosravani, Shahriar, Heidari, Mohammad Ali, Ackermann, James F., Rassaian, Mostafa, Behzadpour, Forouzan
• Granted Patent: US 9,770,873 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B29C 70/30 Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
• CPC Class Codes: B29C 70/38 Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns application heads for tyres B29D30/28
• CPC Class Codes: B29L 2031/3076 Aircrafts blades, propellers B29L2031/08
• CPC Class Codes: G05B 11/011 details of the correcting means

Abstract

A system and method for creating an optimized composite laminate structure containing a plurality of plies. The system has a processor and a memory, including an application interface. The application interface, when executed by the processor, is configured to operably: receive an input file having one or more of a maximum number of plies, design variables, material properties, and design constraints; determine an initial layup sequence defining parameters of a fiber orientation angle for each ply, and a total percentage of plies at a given fiber orientation angle; iteratively adjust the parameters, until an optimum set of parameters is obtained that achieves one or more predetermined margins of safety, and that achieves optimization of the composite laminate structure; and generate an output file for creating a layup, according to the parameters. The system further has a layup system for creating the optimized composite laminate structure.

Claims

1. A system for creating an optimized composite laminate structure containing a plurality of plies, the system comprising:

a processor;

a memory in communication with the processor, including an application interface which, when executed by the processor, is configured to operably;

receive an input file comprising one or more of a maximum number of plies, design variables, material properties, and design constraints, for a composite laminate structure containing the plurality of plies;

determine an initial layup sequence defining parameters comprising a fiber orientation angle for each ply, and a total percentage of plies at a given fiber orientation angle in the composite laminate structure;

iteratively adjust the parameters, until an optimum set of parameters is obtained that achieves one or more predetermined margins of safety for the composite laminate structure, and that achieves optimization of the composite laminate structure, resulting in the optimized composite laminate structure; and

generate an output file for creating a layup of the optimized composite laminate structure, according to the parameters; and

a layup system configured to operably lay up the plurality of plies for creating the optimized composite laminate structure, according to the output file and the parameters.

2. The system of claim 1 wherein the application interface is further configured to operably use an analysis system comprising:

an integrated analysis tool configured to operably calculate the one or more predetermined margins of safety for the composite laminate structure; and

,

an optimization tool configured to operably receive the one or more predetermined margins of safety from the integrated analysis tool, to operably achieve optimization of the composite laminate structure, and to operably generate the output file,

wherein the optimization tool comprises an optimization algorithm to obtain optimization tool results to test for convergence, and if convergence is achieved, then optimization is complete and the output file is generated, and if convergence is not achieved, then design variables are updated and one or more design cycles are repeated until convergence is achieved.

3. The system of claim 2 further comprising a conversion software which, when executed by the processor, is operable to convert data for the initial layup sequence to an analysis system format for use in the integrated analysis tool of the analysis system.

4. The system of claim 2 wherein the one or more predetermined margins of safety calculated by the integrated analysis tool comprise a predetermined stress margin of safety and a predetermined strain margin of safety, based on one or more predefined design rules.

5. The system of claim 2 wherein the optimization algorithm is a genetic algorithm.

6. The system of claim 1 wherein the application interface iteratively adjusts the parameters subject to design constraints comprising less than fifty percent (50%) of the total percentage of plies containing a zero degree (0°

) fiber orientation angle, less than sixty percent (60%) of the total percentage of plies containing a plus or minus forty-five degree (+/−

45°

) fiber orientation angle, and more than ten percent (10%) of the total percentage of plies containing a ninety degree (90°

) fiber orientation angle.

7. The system of claim 1 wherein the fiber orientation angle comprises one of a zero degree (0°

) fiber orientation angle, a ninety degree (90°

) fiber orientation angle, or a plus or minus forty-five degree (+/−

45°

) fiber orientation angle.

8. The system of claim 1 wherein the system is a non-finite element model (non-FEM) system that does not require use of a finite element model (FEM), and further wherein the system is automated to find either a global optimum solution or a local optimum solution.

9. The system of claim 1 wherein the composite laminate structure comprises a composite laminate skin.

10. The system of claim 1 wherein the layup system comprises a manual layup system or an automated layup system.

11. The system of claim 10 wherein the automated layup system comprises a numerical control tow placement machine for creating the layup of the optimized composite laminate structure, according to the output file and the parameters.

12. A non-finite element model system for optimizing a composite laminate structure containing a plurality of plies, the system comprising:

a controller powered by a power element, the controller comprising a processor and a memory in communication with the processor;

an application interface coupled to the processor, which when executed by the processor, is configured to operably receive an input file comprising one or more of a maximum number of plies, design variables, material properties, and design constraints, for the composite laminate structure, and is further configured to operably determine an initial layup sequence defining parameters comprising a fiber orientation angle for each ply, and a total percentage of plies at a given fiber orientation angle, in the composite laminate structure;

a conversion software which, when executed by the processor, is operable to convert data for the initial layup sequence to an analysis system format;

an analysis system configured to operably receive with the application interface the parameters and the data for the initial layup sequence, and iteratively adjust the parameters subject to design constraints comprising less than fifty percent (50%) of the total percentage of plies containing a zero degree (0°

) fiber orientation angle, less than sixty percent (60%) of the total percentage of plies containing a plus or minus forty-five degree (+/−

45°

) fiber orientation angle, and more than ten percent (10%) of the total percentage of plies containing a ninety degree (90°

) fiber orientation angle, until an optimum set of parameters is obtained that achieves one or more predetermined margins of safety for the composite laminate structure, and that achieves optimization of the composite laminate structure, resulting in an optimized composite laminate structure;

an output file generated by the analysis system for forming a layup of the optimized composite laminate structure, according to the parameters; and

an automated layup system or a manual layup system configured to operably lay up the plurality of plies for forming the optimized composite laminate structure, according to the output file and the parameters.

13. The system of claim 12 wherein the analysis system comprises:

an integrated analysis tool configured to operably calculate the one or more predetermined margins of safety for the composite laminate structure, wherein the one or more predetermined margins of safety comprise a predetermined stress margin of safety and a predetermined strain margin of safety, based on one or more predefined design rules; and

,

an optimization tool configured to operably receive the one or more predetermined margins of safety from the integrated analysis tool, to operably achieve optimization of the composite laminate structure, and to operably generate the output file, the optimization tool comprising an optimization algorithm to obtain optimization tool results to test for convergence, and if convergence is achieved, then optimization is complete and the output file is generated, and if convergence is not achieved, then design variables are updated and one or more design cycles are repeated until convergence is achieved.

14. A method executed by a processor for optimizing a composite laminate structure containing a plurality of plies, the method comprising the steps of:

receiving with an application interface executed by the processor, an input file comprising one or more of a maximum number of plies, design variables, material properties, and design constraints, for the composite laminate structure containing the plurality of plies;

determining with the application interface executed by the processor, an initial layup sequence defining parameters comprising a fiber orientation angle for each ply, and a total percentage of plies at a given fiber orientation angle in the composite laminate structure;

using with the application interface executed by the processor, an analysis system for iteratively adjusting the parameters, until an optimum set of parameters is obtained that achieves one or more predetermined margins of safety for the composite laminate structure and that achieves optimization of the composite laminate structure, resulting in an optimized composite laminate structure;

generating with the application interface executed by the processor, an output file for creating a layup of the optimized composite laminate structure, according to the parameters; and

automatically or manually laying up the plurality of plies for creating the layup of the optimized composite laminate structure, according to the output file and the parameters.

15. The method of claim 14 wherein the method is a non-finite element model (non-FEM) method that does not require use of a finite element model (FEM), and is automated to find either a global optimum solution or a local optimum solution.

16. The method of claim 14 wherein the step of determining the initial layup sequence comprises determining the initial layup sequence defining parameters comprising fiber orientation angles of zero degree (0°

) fiber orientation angles, ninety degree (90°

) fiber orientation angles, and plus or minus forty-five degree (+/−

45°

) fiber orientation angles.

17. The method of claim 14 further comprising after the step of determining the initial layup sequence, the step of using with the application interface executed by the processor, a conversion software configured to operably convert data for the initial layup sequence to an analysis system format for use in the analysis system.

18. The method of claim 14 wherein the step of using the analysis system comprises iteratively adjusting the parameters subject to design constraints comprising less than fifty percent (50%) of the total percentage of plies containing a zero degree (0°

) fiber orientation angle, less than sixty percent (60%) of the total percentage of plies containing a plus or minus forty-five degree (+/−

45°

) fiber orientation angle, and more than ten percent (10%) of the total percentage of plies containing a ninety degree (90°

) fiber orientation angle.

19. The method of claim 14 wherein the step of using the analysis system comprises the step of using an integrated analysis tool configured to operably calculate the one or more predetermined margins of safety comprising a predetermined stress margin of safety and a predetermined strain margin of safety, based on one or more predefined design rules.

20. The method of claim 19 wherein the step of using the analysis system further comprises the steps of:

exporting the one or more predetermined margins of safety from the integrated analysis tool to an optimization tool for optimization;

using in the optimization tool, an optimization algorithm configured to operably obtain optimization tool results to test for convergence; and

testing the optimization tool results for convergence, and if convergence is achieved, then optimization is complete and the output file is generated, and if convergence is not achieved, then design variables are updated and one or more design cycles are repeated until convergence is achieved.