Abstract
The paper presents an application of the inhouse implementation of the evolutionary multi-objective algorithm. Different types of functionals, which depend on equivalent stress, displacement and total mass of the structure are defined. Values of the functionals are calculated on the basis of results obtained from numerical simulations. Numerical model of the UAV wing, composed of different laminate materials has been prepared and verified experimentally. Automatic calculation of the fitness functionals for the parameterized model is prepared. Examples of multi-objective optimization by means of 2D and 3D Pareto-optimal set of solutions are presented. Effectiveness and usefulness of proposed method of multi-objective optimization are shown.
| Original language | English |
|---|---|
| Pages (from-to) | 530-536 |
| Number of pages | 7 |
| Journal | Mechanika |
| Volume | 22 |
| Issue number | 6 |
| DOIs | |
| Publication status | Published - 2016 |
Keywords
- Composite materials
- Evolutionary algorithms
- Finite element method
- Multi-objective optimization
- UAV wing
ASJC Scopus subject areas
- Condensed Matter Physics
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