Method of designing a composite laminate

• US 20100121625A1
• Filed: 11/13/2009
• Published: 05/13/2010
• Est. Priority Date: 11/13/2008
• Status: Active Grant

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus Operations Limited (Airbus SE)
• Inventors: Krog, Lars
• Granted Patent: US 8,306,789 B2
• Time in Patent Office: Days
• US Class Current: 703/6
• CPC Class Codes: G06F 2111/06 Multi-objective optimisation, e.g. Pareto optimisation using simulated annealing [SA], ant colony algorithms or genetic algorithms [GA]
• CPC Class Codes: G06F 2113/26 Composites
• CPC Class Codes: G06F 30/13 Architectural design, e.g. computer-aided architectural design [CAAD] related to design of buildings, bridges, landscapes, production plants or roads

Abstract

A method of designing a composite laminate, the laminate comprising a plurality of zones, each zone comprising a plurality of plies of composite material, each ply in each zone having a respective ply orientation angle. A global stacking sequence is determined for the laminate, the global stacking sequence comprising a sequence of stacking sequence elements. A local laminate thickness is determined for each zone. A local stacking sequence is then determined for each zone by extracting a subsequence of stacking sequence elements from the global stacking sequence. The global stacking sequence and the local laminate thicknesses are determined together in an optimisation process in which multiple sub-ply selection variables are assigned to each stacking sequence element, each sub-ply selection variable representing the density or sub-ply thickness for a respective candidate ply orientation angle. Optimal values are determined for the sub-ply selection variables and the local laminate thicknesses. A single one of the sub-ply selection variables is assigned to each stacking sequence element thereby forcing a discrete choice of global ply orientation angle for each stacking sequence element.

Claims

1. A method of designing a composite laminate, the laminate comprising a plurality of zones, each zone comprising a plurality of plies of composite material, each ply in each zone having a respective ply orientation angle, the method comprising:

a. determining a global stacking sequence for the laminate, the global stacking sequence comprising a sequence of stacking sequence elements each defining a respective global ply orientation angle, the percentages of the various ply orientations within the global stacking sequence defining a laminate constitution;

b. determining a local laminate thickness for each zone; and

c. determining a local stacking sequence for each zone by extracting a subsequence of stacking sequence elements from the global stacking sequence,

wherein the global stacking sequence, the laminate constitution and the local laminate thicknesses are determined together in an optimisation process in which multiple sub-ply selection variables are assigned to each stacking sequence element, each sub-ply selection variable representing the density or sub-ply thickness for a respective candidate ply orientation angle;

optimal values are determined for the sub-ply selection variables and the local laminate thicknesses; and

a single one of the sub-ply selection variables is assigned to each stacking sequence element thereby forcing a discrete choice of global ply orientation angle for each stacking sequence element.

2. The method of claim 1 further comprising determining multiple local ply orientation design variables for each zone, each local ply orientation design variable representing a local ply orientation correction for a respective global ply orientation angle as used in the global stacking sequence;

and wherein the local ply orientation design variables, the global stacking sequence, the laminate constitution and the local laminate thicknesses are determined together in the optimisation process.

3. The method of claim 1 wherein the optimisation process is a gradient-based optimisation process which performs repeated structural analysis, sensitivity analysis and mathematical optimisation steps, wherein each analysis step calculates current values for the objective functions and one or more constraint functions based on a current set of sub-ply selection variables and local laminate thicknesses, each sensitivity analysis step determines partial derivatives of the output of the structural analysis, and each mathematical optimisation step solves an approximate optimisation problem to determine improved values for the sub-ply selection variables and local laminate thicknesses which optimise the objective function whilst ensuring that each constraint function complies with an associated constraint requirement.

4. The method of claim 3 wherein the objective function contains a penalty term which pushes the optimisation process towards selecting a single one of the sub-ply selection variables for each stacking sequence element.

5. The method of claim 3 wherein the structural analysis step further comprises calculating the laminate constitution and calculating stiffness properties of the composite laminate from the laminate constitution.

6. The method of claim 5 wherein the stiffness properties are calculated by interpolating stiffness properties found at discrete local laminate thickness values.

7. The method of claim 3 wherein the structural analysis comprises a first structural analysis which calculates internal loads within the laminate and a second structural analysis which calculates strength and/or buckling properties of the laminate;

and wherein the sensitivity analysis comprises a first sensitivity analysis which determines partial derivatives of the output of the first structural analysis and a second sensitivity analysis which determines partial derivatives of the output of the second structural analysis and is combined with the first sensitivity analysis.

8. The method of claim 7 wherein the first and second sensitivity analyses are performed by parallel computing streams.

9. The method of claim 3 wherein the sensitivity analysis is based on a set of intermediate variables which are derived from the sub-ply selection variables and/or the local laminate thicknesses.

10. The method of claim 9 wherein the intermediate variables include the laminate constitution.

11. The method of claim 9 wherein the intermediate variables include laminate bending stiffness parameters.

12. The method of claim 1 wherein the subsequence of stacking sequence elements from the global stacking sequence is a contiguous subsequence of stacking sequence elements from the global stacking sequence.

13. A method of manufacturing a composite laminate, the method comprising designing the composite laminate by the method of claim 1;

and manufacturing the composite laminate in accordance with the design.