## 6 Results and Discussion
\begin{table}
\begin{tabular}{c c c c c c c c} \hline \hline  & & **Iteration** & **Initial Weight** & \
\begin{tabular}{c} **Optimized** \\ **Weight** \\ \end{tabular} &
\begin{tabular}{c} **Weight** \\ **Reduction Ratio** \\ \end{tabular} & **Deformation** & **Stress** \\ \hline \multirow{8}{*}{Fixed Wing} & Rib 1 & 41 & 0.539 kg & 0.279 kg & 48.2\% & 0.024 mm & 0.85 MPa \\  & Rib 2 & 27 & 0.237 kg & 0.1 kg & 57.8\% & 0.0088 mm & 2.26 MPa \\  & Rib 3 & 26 & 0.209 kg & 0.095 kg & 54.5\% & 0.003 mm & 1.11 MPa \\  & Rib 4 & 24 & 0.167 kg & 0.09 kg & 46.1\% & 0.023 mm & 3.813 MPa \\  & Rib 5 & 20 & 0.137 kg & 0.086 kg & 37.2\% & 0.04 mm & 5.462 MPa \\  & Rib 6 & 9 & 0.107 kg & 0.086 kg & 19.6\% & 0.082 mm & 5.737 MPa \\  & Rib 7 & 0 & 0.086 kg & 0.086 kg & 0 & 0 & 0 \\  & Rib 1 & 40 & 0.134 kg & 0.04 kg & 70.1\% & 0.00034 mm & 0.19 MPa \\  & Rib 2 & 30 & 0.086 kg & 0.028 kg & 67.4\% & 0.00002 mm & 0.047 MPa \\  & Rib 3 & 30 & 0.086 kg & 0.028 kg & 67.4\% & 0.00002 mm & 0.047 MPa \\ \multirow{2}{*}{Moving Wing} & Rib 4 & 29 & 0.086 kg & 0.028 kg & 67.4\% & 0.00001 mm & 0.032 MPa \\  & Rib 5 & 32 & 0.086 kg & 0.028 kg & 67.4\% & 0.00001 mm & 0.027 MPa \\  & Rib 6 & 31 & 0.086 kg & 0.028 kg & 67.4\% & 0.00001 mm & 0.027 MPa \\  & Rib 7 & 0 & 0.113 kg & 0.113 kg & 0 & 0 & 0 \\ \hline \hline \end{tabular}
\end{table} 
Table 6: Parameters of the wing segments for the ribs obtained from topology optimization based on Finite Element Analysis. Figure 22: Deformation results based on TO for: (**A**) rib 1 of a fixed wing, (**B**) rib 2 of a fixed wing, (**C**) rib 1 of a moving wing, and (**D**) rib 6 of a moving wing. Figure 23: Stress results based on TO for: (**A**) rib 1 of a fixed wing, (**B**) rib 2 of a fixed wing, (**C**) rib 1 of a moving wing, and (**D**) rib 6 of a moving wing. The optimized wing segments modeled as solid suggest that a wing should have strut elements obtained from TO in order to meet their strengths requirements. Various aerodynamic load scenarios obtained for extreme flight conditions were evaluated to design the support parts, as indicated in Table 3, and in Figures 3 and 4. The baseline TO was conducted on the support elements' structure for both wing segments using the required load conditions. Certain support elements were excluded from the TO due to their geometrical designs. The results obtained from various TOs were represented as density cloud maps for the support elements, as shown in Figures 24 and 25 for fixed wing and moving wing segments, respectively. The red sections represent the solid region, while the blue sections represent the void region. The basic structure of support elements was highly minimized based on the TO results, thereby reducing the support elements weights. Moreover, it is clear that the structural compliance decreased as the number of iterations increased, as shown in Figures 26 and 27. Figure 24: Element density plots with the iteration numbers for fixed wing: (**A**) leading edge of rib \(1\), (**B**) trailing edge of rib \(1\), (**C**) bottom support surface between rib 6 and rib 7, and (**D**) front spar support. Figure 25: Element density plots with the iteration number for moving wing: (**A**) leading edge of rib \(1\), (**B**) trailing edge of rib \(1\), (**C**) support stringer of a front spar, and (**D**) support stringer of a rear spar. Figures 28-31 show the effects of a TO process on the structural changes in mechanical properties, such as deformations and stresses. These figures indicate that the strain can be reduced, while the structural stiffness progressively increases. Figure 28: Deformation results based on topology optimization of a fixed wing: (**A**) leading edge of rib 1, (**B**) trailing edge of rib 1, (**C**) bottom support surface between ribs 6 and 7, and (**D**) support of a front spar. Figure 27: Convergence graphs of the objective function for a moving wing: (**A**) leading edge of rib 1, (**B**) trailing edge of rib 1, (**C**) support stringer of a front spar, and (**D**) support stringer of a rear spar.