*2.3.4 Loading conditions*

*Environmental Impact of Aviation and Sustainable Solutions*

**2.3 General finite element model setup**

reduces computational time significantly **Table 1**.

This material's properties are presented in **Table 2**.

a fine mesh representative of the geometric features (**Figure 3a**).

*2.3.1 Geometry and discretization*

*2.3.2 Materials*

winding frame:

*2.3.3 Boundary conditions*

a "stick" condition (no sliding) between the two surfaces. However, if no sliding occurs, stress concentration around the contact interface is bound to rise past the allowable limit—thus, some sliding must be ensured to provide stress relief.

All the cross sections to be analyzed are expected to be symmetric in both horizontal and vertical directions due to the homogenous pressure that they are subjected to. The finite element models constructed, take full advantage of this geometric symmetry by simulating only one quarter of each cross section. This

Solid 3D elements with an approximate global size of 2.5 mm were used to create

The following material properties were applied to the aluminum yoke plates and

For the composite winding, carbon fiber prepreg (Zoltek Panex 35) was used.

Symmetry boundary conditions were applied as shown in **Table 3**.

*(a) Updated cross-section assembly without press cylinder tube and (b) updated contact definition.*

**26**

**Figure 4.**

A homogenous pressure of 165 MPa is applied to the inner faces of the yoke plates as shown in **Figure 3b**.
