Lamination parameter-based method for optimal design and manufacturing options

• US 10,183,449 B2
• Filed: 09/25/2015
• Issued: 01/22/2019
• Est. Priority Date: 09/25/2015
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Rassaian, Mostafa, Epton, Michael A., Cramer, Evin J., Balabanov, Vladimir, Weckner, Olaf
• Primary Examiner(s): Aftergut, Jeffry H
• Application Number:
  US14/866,597
• Publication Number:
  US 20170087779A1
• Time in Patent Office: 1,215 Days
• Field of Search: 156 64
• 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

Abstract

A design process that uses lamination parameter inversion to generate a set of baseline layups having desired stiffness properties. Then the underdetermined Newton'"'"'s method can be applied to explore solution manifolds describing alternative designs having similar if not identical stiffness properties. The manifold of solutions can be methodically examined to find those with desirable properties. Desirable properties include those that have been traditionally captured by design rules or those that improve manufacturability. Combining lamination parameters as design variables with lamination parameter inversion provides an efficient optimization process for non-traditional laminates.

Claims

1. A method for designing and manufacturing a composite laminate, the method comprising:

(a) generating target lamination parameters for a composite laminate using structural optimization to optimize a weight function subject to design and/or manufacturing constraints;

(b) generating a baseline set of layups having lamination parameters which match the target lamination parameters;

(c) determining additional layup solutions lying on a same solution manifold for each baseline layup, each solution manifold being a respective set of alternative designs having identical stiffness properties;

(d) filtering layups on solution manifolds using design rules to produce a reduced set of candidate layups, wherein the design rules include limits on (i) the gap angle between any two layers of the complete layup, (ii) the swerve angle, the change in layup angle between adjacent layers, and (iii) adequate diversity of layup angle over every neighborhood of adjacent layers;

(e) verifying maximum strain and buckling properties of the candidate layups by performing an engineering analysis using a finite element model; and

(f) manufacturing a composite laminate having a layup corresponding to a candidate layup having verified maximum strain and buckling properties.

2. The method as recited in claim 1, wherein each of the candidate layups has stiffness properties which are similar to stiffness properties characterized by the target lamination parameters.

3. The method as recited in claim 1, wherein process (a) comprises:

selecting design variables;

determining design and manufacturing constraints;

selecting an objective weight function; and

determining an optimal value of the objective weight function that satisfies user-provided limits on both the design variables and the constraints by solving a constrained optimization problem,

wherein the target lamination parameters are a function of optimal design variables corresponding to the optimal value of the objective function.

4. The method as recited in claim 3, wherein the design variables comprise a set of fiber angles and ply thicknesses, further comprising converting the optimal design variables corresponding to the optimal value of the objective function into the target lamination parameters.

5. The method as recited in claim 3, wherein the design variables comprise a set of lamination parameters and total thickness.

6. The method as recited in claim 1, wherein process (b) comprises:

defining a layup strategy;

selecting a number of solution attempts to be made; and

employing the layup strategy, executing a mathematical method starting with a number of random initial points and searching for layups whose lamination parameters match the target lamination parameters,

wherein the number of random initial points equals the number of solution attempts to be made.

7. The method as recited in claim 6, wherein the mathematical method is an underdetermined Newton'"'"'s method or an algebraic geometry method.

8. The method as recited in claim 6, wherein process (c) comprises recursively applying a curve tracing algorithm to determine points on the solution manifold containing the baseline layup.

9. A method for manufacturing a laminated composite structure using plies of fiber-reinforced plastic, the method comprising:

(a) determining target lamination parameters for a composite laminate using structural optimization to optimize a weight function subject to design and/or manufacturing constraints;

(b) determining a set of baseline layups whose lamination parameters match the target lamination parameters using lamination parameter inversion to find families of alternative layups with stiffness matrices specified by their lamination parameters;

(c) determining alternative layups lying on a solution manifold for each of the baseline layups, each solution manifold being a respective set of alternative designs having identical stiffness properties;

(d) selecting alternative layups which satisfy a set of design rules, wherein the design rules include limits on (i) the gap angle between any two layers of the complete layup, (ii) the swerve angle, the change in layup angle between adjacent layers, and (iii) adequate diversity of layup angle over every neighborhood of adjacent layers;

(e) verifying maximum strain and buckling properties of a selected alternative layup by performing an engineering analysis using a finite element model; and

(f) manufacturing a laminated composite structure having the selected alternative layup.

10. The method as recited in claim 9, wherein process (a) comprises:

selecting design variables;

determining design and manufacturing constraints;

selecting an objective weight function; and

determining an optimal value of the objective weight function that satisfies user-provided limits on both the design variables and the constraints by solving a constrained optimization problem,

wherein the target lamination parameters are a function of optimal design variables corresponding to the optimal value of the objective function.

11. The method as recited in claim 10, wherein the design variables comprise a set of fiber angles and ply thicknesses, further comprising converting the optimal design variables corresponding to the optimal value of the objective function into the target lamination parameters.

12. The method as recited in claim 10, wherein the design variables comprise a set of lamination parameters and total thickness.

13. The method as recited in claim 9, wherein process (b) comprises:

defining a layup strategy;

selecting a number of solution attempts to be made; and

employing the layup strategy, executing a mathematical method that searches for layups whose lamination parameters match the target lamination parameters.

14. The method as recited in claim 13, wherein the mathematical method is an underdetermined Newton'"'"'s method.

15. The method as recited in claim 13, wherein process (c) comprises recursively applying a curve tracing algorithm to determine points on the solution manifold containing the baseline layup.

16. The method as recited in claim 9, wherein the engineering analysis comprises determination of maximum strains and buckling analysis.

17. The method as recited in claim 9, wherein at least process (b), (c) and (e) are performed by a computer system.

18. The method as recited in claim 9, wherein process (f) comprises laying tows of fiber-reinforced plastic material using an automated tow placement machine.

19. A method for designing and manufacturing a composite laminate, the method comprising:

generating target lamination parameters for a composite laminate using structural optimization to optimize a weight function subject to design and/or manufacturing constraints;

generating a baseline set of layups having lamination parameters which match the target lamination parameters using lamination parameter inversion to find families of alternative layups with stiffness matrices specified by their lamination parameters;

determining additional layup solutions lying on a same solution manifold for each baseline layup, each solution manifold being a respective set of alternative designs having identical stiffness properties; and

manufacturing a composite laminate having a layup corresponding to an additional layup solution.

20. The method as recited in claim 19, further comprising:

filtering layups on solution manifolds using design rules to produce a reduced set of candidate layups, wherein the design rules include limits on (i) the gap angle between any two layers of the complete layup, (ii) the swerve angle, the change in layup angle between adjacent layers, and (iii) adequate diversity of layup angle over every neighborhood of adjacent layers; and

verifying maximum strain and buckling properties of the candidate layups by performing an engineering analysis using a finite element model,

wherein the manufactured composite laminate has a layup corresponding to a candidate layup having maximum strain and buckling verified properties.