# Optimization of DLTS Hinges for the Assembly of the Solar Arrays of a Communication CubeSat
## 5 Conclusions  
The double-layer tape spring (DLTS) hinge is employed to facilitate the connection between the flasher solar panels, supporting the adaptation and realization of the assumed origami-based pattern in the solar arrays. This study aimed to discern the crucial parameters of the DLTS hinge during the transition from the stowed to the deployment configuration. The design methodology involved simulations to obtain the optimal solution for the critical design parameters of the DLTS hinge. The critical geometric parameters \(R\), \(\theta\), and \(t\) were identified and \(\sigma_{\mathrm{v}}\) and steady-state moment simulations were undertaken for the DLTS hinge in the stowed and deployed state. After the extraction of the computational results, optimization was conducted using Taguchi DOE and RSM. In the Taguchi L9 array method, a design with three factors and three levels \begin{table}
\begin{tabular}{c c c c c} \hline \hline \multirow{2}{*}{**Design**} & **Layer Thickness,** & **Subtended** & **\(\sigma_{\mathrm{v}}\) (N/mm\({}^{2}\))** & **Steady-State Moment (Nmm)** \\ \hline Optimal & 2.90 & 1.35 & 1493.87 & 145.76 \\ \hline \hline \end{tabular}
\end{table} 
Table 4: Optimal geometric configuration parameters for DLTS hinge. was employed to identify parameters with a low \(\sigma_{\rm v}\) and steady-state moment. Contour plots were utilized to investigate the relationship between the selected response variables of \(\sigma_{\rm v}\) and steady-state moment and the three denoted critical parameters. In the case of the RSM model, an LSGRG algorithm was employed, and the maximum \(\sigma_{\rm v}\) was identified as a constraint to eliminate the deformations and failure of the DLTS hinge. The \(t\) and \(\theta\) parameters were denoted as critical design parameters and the \(R\) parameter was neglected. The goal of this research is to enhance the integration of solar panels, minimizing the risk of failure during service. The findings have identified crucial parameters for producing a preliminary specification for the first stage of development. The key outcomes from the computational experimentation are as follows:  
* The predicted lowest \(\sigma_{\rm v}\) and steady-state moment were estimated to be 1661 N/mm\({}^{2}\) and 133.9 N/mm by setting an \(R\) of 6.0 mm, a \(\theta\) of 60\({}^{\circ}\), and a \(t\) of 0.1 mm, utilizing the RSM model. * Optimization was achieved by keeping \(\sigma_{\rm v}\) below 1700 N/mm\({}^{2}\) and the steady-state moment below 150 N/mm\({}^{2}\). * Consequently, the optimum parameters of \(t\), \(R\), and \(\theta\) were determined to be between 1.75 and 2.25 mm, 1.50 and 2.0 mm, and 1 and 1.2\({}^{\circ}\), respectively. * A safe limit of maximum \(\sigma_{\rm v}\) was determined for the avoidance of permanent deformation and degradation of the DLTS hinge, which could not exceed the 2.43 \(\times\) 10\({}^{3}\) N/mm\({}^{2}\) value. * Following this, the accuracy criterion for the max \(\sigma_{\rm v}\) and steady-state moment yielding value was satisfied by determining the percentage difference between \(R^{2}\) and \(R_{adj}\)\({}^{2}\) for the two responses. * Subsequently, the optimum values of the \(t\) and \(\theta\) parameters were 2.90 mm and 1.35\({}^{\circ}\), with a max \(\sigma_{\rm v}\) of 1.49 \(\times\) 10\({}^{3}\) N/mm\({}^{2}\) and steady-state moment of 145.76 Nmm. * The design goal of the DLTS hinges was to accommodate the thickness of the flasher pattern and rotate 90\({}^{\circ}\). The optimum values of \(t\) and \(\theta\) achieved this with a reduced \(\sigma_{\rm v}\) to the system, and hence, sufficient stability of the DLTS hinges was accomplished to ensure safe launch conditions, withstand the harsh environmental conditions, rotate appropriately the solar panels for the obtainment of power, and expand the life service of the whole system. * Future research investigations will require a life cycle assessment and on-site validation, with a focus on the deformation and degradation of DLTS hinges.