## 2 Materials and Methods
### Laminate Properties  
The individual layer properties were used to compute the \(\mathbf{A}\), \(\mathbf{B}\), and \(\mathbf{D}\) matrices for the equivalent orthotropic shell laminate according to CLT [26] and can be expressed as:  
\[\mathbf{A}_{i\bar{\eta}}=\sum_{k=1}^{N_{l}}\overline{C}_{ij}(z_{k}-z_{k-1}) \tag{1}\]  
\[\mathbf{B}_{i\bar{\eta}}=\frac{1}{2}\sum_{k=1}^{N_{l}}\overline{C}_{ij}\Big{(}z_{k }^{2}-z_{k-1}^{2}\Big{)} \tag{2}\]  
\[\mathbf{D}_{i\bar{\eta}}=\frac{1}{3}\sum_{k=1}^{N_{l}}\overline{C}_{i\bar{\eta}} \Big{(}z_{k}^{3}-z_{k-1}^{3}\Big{)} \tag{3}\]  
where \(\overline{C}_{ij}\) is the stiffness matrix rotated from \(\mathbf{C}\) (which is the stiffness matrix of a base layer whose fibers are parallel to the global coordinate direction, i.e., a 0-degree angle). The subscript \(k\) denotes the layer, \(N_{l}\) the total number of layers, and \(z\) the laminate package thickness coordinate originating from its centroid (Figure 1). The mean density of the laminate is \(\rho=1.56\) g/cm\({}^{3}\). The obtained values were as follows  
\[\mathbf{A}= \begin{bmatrix}119.4&19.8&0\\ 19.8&30.05&0\\ 0&0&19.16\end{bmatrix} \text{GPa mm} \tag{4}\]  
\[\mathbf{B}= \begin{bmatrix}0&0&0\\ 0&0&0\\ 0&0&0\end{bmatrix} \text{GPa mm}^{2} \tag{5}\]  
\[\mathbf{D}= \begin{bmatrix}9.653&4.558&0\\ 4.558&6.209&0\\ 0&0&4.372\end{bmatrix} \text{GPa mm}^{3} \tag{6}\]  
To completely characterize the laminate, three-point bending tests were completed via a dynamical mechanical analysis (DMA). In this test, the storage modulus and loss modulus are measured. The damping factor \(\tan(\delta)\) is computed as the ratio between the two moduli. Tests were carried out in a temperature range from 30 \({}^{\circ}\)C to 200 \({}^{\circ}\)C using four samples to verify temperature influence on the laminate properties. Figure 6 shows a scheme of this kind of test (a), and the actual experimental setup (b). Sample dimensions were 40 mm \(\times\) 15 mm \(\times\) 1.32 mm. Figure 6: DMA three-point bending test: (**a**) schematic representation; (**b**) sample mounted for experimental tests. To perform the DMA tests, other parameters had to be selected, including the distance between the inferior supports (i.e., the span), the frequency at which the soliciting force was applied, the offset force, and the displacement amplitude. The span value was settled to 35 mm according to the DMA's software preliminary evaluation about the expected modulus magnitude. Concerning the frequency, a standard value of 1 Hz was used. The offset force and the displacement amplitude were found to be equal to 3 N and 10 \(\upmu\)m after preliminary dedicated tests. Figure 7 depicts the tests results for the storage modulus and the damping factor. The modulus at the test starting temperature (30 \({}^{\circ}\)C) was 30.25 \(\pm\) 3.25 GPa, in agreement with the value obtained after the quasi static three-point bending tests described in Section 4.2. Increasing the temperature, the glass transition temperature of the matrix (143 \({}^{\circ}\)C) was reached and the material softened. However, the modulus decrease was limited, with around 27 GPa at 150 \({}^{\circ}\)C and 21 GPa at 200 \({}^{\circ}\)C. Concerning the damping factor, we identified three regions approximated by a linear behavior for \(\tan(\delta)\): in the range T \(<\) 118 \({}^{\circ}\)C, \(\tan(\delta)\) mean value was equal to 0.012; and increased until reaching \(\tan(\delta)=0.034\) at 160 \({}^{\circ}\)C. From 160 to 200 \({}^{\circ}\)C, \(\tan(\delta)\) decreased to a value of 0.025. In the analyzed case study, i.e., a solar panel, environmental temperatures are considered to vary up to 130 \({}^{\circ}\)C, as for analogous composite structures in space operating conditions [27; 28]. Hence, the modulus of the material could be assumed constant in the examined temperature range, while the damping factor was characterized by a higher relative variation, and its change was taken into account in the numerical simulations.