Optimization of composite structures involves the consideration of several design variables, including ply material, thickness, angle, and stacking sequence. In HyperX, each of these variables is evaluated not only for weight and positive margins of safety, but also for producibility - allowing the engineer to make decisions with regards to their program's priorities at every step of the way.
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There are infinite workflows for solving this optimization problem, the most general of which are summarized here. Note that the workflow that is best for you and your team depends on your inputs and the desired outputs.
The first workflow is our take on the desires of the early stages of sizing - rapidly producing results, but at a lower fidelity. The remaining two workflows should be used to obtain an optimum, discretely defined Laminate for each Zone in the Structure (rather than just thickness and ply percentages). If each Zone has a defined Laminate, those Laminates can be Sequenced into a set of Structure-level Plies in order to attain a result that is more communicable with CAD.
Inputs - Ply Angle Percentage bounds, Layup Rule preferences, Thickness bounds (EL only).
Outputs - Optimum Zone thickness, Ply Angle Percentages.
In this workflow, rather than generating discretely defined Laminates, the optimization will result in only Thickness and Ply Angle Percentage for each Zone. There are two possible sizing routines that generate this result fidelity:
This workflow is particularly advantageous for early design and trade studies, as both sizing routines have quick runtimes. These results can also be taken one step further by using them as inputs to another composites optimization workflow below. Collier Aerospace particularly recommends Sizing with Laminate Families where these results are used as inputs for Laminate Family Generation.
Inputs - There are a few different input options for the Laminate Family workflow, as there are several different ways to obtain Laminate Families.
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Program standard Laminate Family (manually created or imported from Excel).
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HyperX can also generate Laminate Families from:
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Laminates imported from FEM
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Plies imported from CAD
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Preliminary Sizing Results from Effective Laminates
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Ply Angle Targets and Layup Rules
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Outputs - Discretely defined Laminate for each Zone, with option to Sequence results into global Plies.
The quickest and most robust Sizing approach recommended by Collier Aerospace engineers is Detailed Sizing with a Laminate Family - where the optimum Sizing result for each Zone is chosen from a predefined selection of Candidate Laminates. Since a Laminate Family consists of Laminates that are related to one another, a weight optimum and manufacturable design is obtained in less steps.
Inputs - Ply Angle Percentage bounds, Layup Rule preferences, Thickness bounds.
Outputs - Discretely defined Laminate for each Zone, with option to Sequence results into global Plies.
This is the workflow that previous HyperSizer users are likely most familiar with. While this process does produce Zones with weight-optimum Laminates, the results are typically difficult to Sequence into global Plies - as Orphan Laminate solutions are less likely to be compatible with their neighbors. This is why the Laminate Family Sizing process is typically recommended. See Sizing with Effective and Discrete Laminates.