# Optimization of DLTS Hinges for the Assembly of the Solar Arrays of a Communication CubeSat
###### Abstract  
This paper demonstrates the analytical and numerical investigations for the obtainment of the predefined critical parameters of double-layer tape spring (DLTS) hinges. The DLTS hinge is utilized for the coupling between the solar panels to assist the accommodation and formulation of the assumed origami-based pattern of the solar arrays. They are examined for the assurance of safety, durability, non-permanent deformation, and stability from the stowed to the deployment configuration. Von [PERSON] stress (\(\sigma_{v}\)) and steady-state moment simulations are investigated by varying the critical hinge design parameters of curvature radius (\(R\)), subtended angle (\(\theta\)) and layer thickness (\(t\)). Two optimization models, Taguchi and response surface methodology/RSM, are utilized by employing the computational findings to obtain and validate the modified optimal geometric parameters within this analytical experiment. For the Taguchi method, the optimization of \(\sigma_{v}\) and the steady-state moment is accomplished with a \(t\) of 1.75-2.25 mm, \(R\) of 1.5-2.0 mm, and \(\theta\) of 1-1.2\({}^{\circ}\). Furthermore, the RSM model shows that the \(t\), \(R\), and \(\theta\) parameters are determined to be 2.90 mm, 2 mm, and 1.35\({}^{\circ}\), respectively. For optimization of the hinge design, both models should be considered for improved verification and accuracy of the results. CubeSat; solar panel array; coupling/driving mechanisms; tape spring hinges; Taguchi method; response surface methodology/RSM +
Footnote †: journal: Applied Sciences  
0000-0002-4000-0000][PERSON] 0000-0002-0002-0002-0002][PERSON] 0000-0002-0002-0002-0002-0002-0002-002-0002-0002-002-0002-002-0002-0002-002-0002-002-0002-0002-002-002-0002-0002-00  
thus, supplementary deployable solar panel arrays are introduced to fulfil the power requirements for the functionality of the whole system [7]. The supplementary deployable solar panel arrays are transitioned from a folded to extended/unfolded arrangement when they reach the correct position in the low Earth orbit [8]. The solar panel arrays' stability and reliability at extended configuration can be at risk during deployment because of sudden vibrations and solar heat radiation changes which can cause potential failure of the performance of the coupling mechanisms and insufficient power generation [9]. Ubiquitous driving/coupling mechanisms (passive mechanisms) are often dependent on torsion springs, tape springs (flexible joints), coil springs, latches, and shape memory alloys (SMAs). The passive mechanisms are preferred compared to the active mechanisms because of the non-operational power requisite, an increase in power acquisition, and a reduction in the weight and volume [10]. Researchers have scrutinized various hinges over the years to satisfy the requirements of solar array deployment such as thickness accommodation, high deployment stiffness, nominal latch-up load, and high torque margin. Therefore, flexible hinges have dominated and been utilized for the folding and deployment mechanisms of solar arrays as they are capable of self-deployment, self-latch, and elastic fold due to the release of stored strain energy [11]. They are characterized by the design's simplicity, light weight, and evenly distributed \(\sigma_{\text{v}}\) before and after the deployment [11]. Throughout the years, analytical, experimental, and numerical investigations have been carried out to observe the flexible hinges' behaviors from the stowed to deployed state by focusing on their configuration methods [12; 13]. Particularly, researchers [PERSON] and [PERSON] developed tape spring hinges (flexible hinges) for solar panel coupling which were found to satisfy the requisites for the amount of extra torque capacity and latch-up load, while optimization of the first natural frequency occurred effectively at the deployed state [14].