nomad-vagabond : Rectangular_Wing
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Rectangular wing console design parameters study
This repository contains results of parametric studies of the wing model. Design parameters as a function of the payload mass were found using knowledge-based model of the wing console, built with the help of CadQuery and SciPy.
Several aerodynamic profiles were considered, and generative algorithms were developed to construct wing section and 3D model of the wing console. Wing console consists of the internal rigid box, made up of the composite material, outer shape-forming body (foam or other low density material) and thin composite cover, like fiberglass. Results in this study correspond to the next materials that were assigned:
- carbon-epoxy composite for the rigidity box;
- polystyrol foam as a fillament;
- fiberglass composite as a thin shell cover.
A next simplified static load scheme was considered:
- Wing console with a fixed end is considered;
- A uniform aerodynamic lift load acts on the wing console;
- A uniform gravity load acts in opposite direction;
- Pure moment bending is considered;
- Wing tip bends at the value of 'h' as a result of the combined wing load forces.
Design parameters, namely console chord and console length, were found using SciPy's optimization module such that wing console with selected geometry produces lift force equal to half of the payload weight multiplied by load factor 1.2.
Rectangular wing console design parameters study
This repository contains results of parametric studies of the wing model. Design parameters as a function of the payload mass were found using knowledge-based model of the wing console, built with the help of CadQuery and SciPy.
Several aerodynamic profiles were considered, and generative algorithms were developed to construct wing section and 3D model of the wing console. Wing console consists of the internal rigid box, made up of the composite material, outer shape-forming body (foam or other low density material) and thin composite cover, like fiberglass. Results in this study correspond to the next materials that were assigned:
- carbon-epoxy composite for the rigidity box;
- polystyrol foam as a fillament;
- fiberglass composite as a thin shell cover.
A next simplified static load scheme was considered:
- Wing console with a fixed end is considered;
- A uniform aerodynamic lift load acts on the wing console;
- A uniform gravity load acts in opposite direction;
- Pure moment bending is considered;
- Wing tip bends at the value of 'h' as a result of the combined wing load forces.
Design parameters, namely console chord and console length, were found using SciPy's optimization module such that wing console with selected geometry produces lift force equal to half of the payload weight multiplied by load factor 1.2.
