## 3 Control of Thermal Deformation Optimization Strategy
### Orbital Temperature Distribution
#### 3.1.1 Heat Dissipation Surface Analysis
The infrared heat flux from the satellite to the ground (+Z plane) is greater but smaller from the perspective of infrared radiation heat flux straight into the earth. The satellite +Y/\(-\)Y plane is significantly impacted by the alternating external heat flux from the direct incoming solar radiation heat flux (including the earth's albedo heat flux). The satellite's +Z-plane changes the least during its whole life cycle because of its orientation to the earth, while the satellite's -Z, +X, and -X planes also shift dramatically when the \(\beta\)-angle changes. The satellite's Y and Z opposing planes obtain direct solar radiation. The OSR cerium glass secondary surface mirrors are firmly mounted to lessen the impact of solar irradiation  
Figure 5: Finite element model for thermal analysis. Figure 6: Satellite surface heat flux. \begin{table}
\begin{tabular}{c c c c c c c} \hline \hline \multirow{2}{*}{\(\beta\)} & \multicolumn{4}{c}{**Earth Infrared Incident Heat Flux on a Honeycomb Plate (W/m\({}^{2}\))**} \\ \cline{2-7}  & **+X** & \(-\)**X** & **+Y** & \(-\)**Y** & **+Z** & \(-\)**Z** \\ \hline \(-\)90–88\({}^{\circ}\) & 51.5 & 51.5 & 34.7 & 35.1 & 191.0 & 0.0 \\ \hline \hline \end{tabular}
\end{table} 
Table 3: Earth Infrared Incident Heat Flux on a Honeycomb Plate. on the entire satellite (low solar absorption and slow degradation in orbit). According to the terminal properties of the heat dissipation surface, OSR_EOL (\(\alpha/\varepsilon\) = 0.13/0.79), the thermal control white paint with small solar absorption and large hemisphere emissivity, brand KS-ZA, is used because X and +Z surfaces are primarily affected by the earth's albedo, whose magnitude is much smaller than the direct solar irradiation surface. Figure 7 depicts the heat dissipation capability of each surface of the KS-ZA EOL (\(\alpha/\varepsilon\) = 0.22/0.92) and the relationship with the \(\beta\)-angle. The \(\beta\)-angle has a significant impact on the ability of Y planes to dissipate heat. The satellite's ability to dissipate heat is stable and powerful while it is in a shadowy area. When the Y planes were in an area that was sunny, the ability to dissipate heat gradually reduced as the \(\beta\)-angle (\(0^{\circ}\) + \(70^{\circ}\), \(0^{\circ}\) \(-\)\(70^{\circ}\)) increased. The heat dissipation ability increases gradually as the Y-angle increases (from \(-70^{\circ}\) to \(-90^{\circ}\), from +\(70^{\circ}\) to +\(90^{\circ}\)), primarily because the solar panels' rotation in relation to the sun blocks the Y planes; at \(90^{\circ}\), the Y planes are completely blocked, which is equivalent to the Y planes being in the shadow area and represents the maximum heat dissipation capacity of the entire satellite; The heat dissipation capability of the +Z plane is the smallest and weakest of all planes because of the significant infrared heat flow to the ground. OSR absorbs little sunlight at various angles, and the variation in its ability to dissipate heat is negligible. The capacity of the X plane to dissipate heat remains constant. According to the above analysis results, Table 4 shows the unit heat dissipation capacity of the heat dissipation surface in orbital space. Honeycomb sandwich construction is often utilized in the main bearing force of spacecraft, which has the features of light weight and many performance parameters that may be designed [25]. The communication test confirms that the satellite uses a honeycomb panel with an aluminum skin honeycomb sandwich structure as the cooling surface of the satellite, and the honeycomb structure is also the main bearing structure of the entire satellite because aluminum skin and aluminum honeycomb have good heat conduction characteristics. Table 5 displays the design criteria for each honeycomb panel. The heat of the satellite is transferred through the heat pipe network implanted in each honeycomb plate, allowing the heat to dissipate more quickly into space. Figure 8 shows the satellite bus's primary structure. Figure 7: Each panel’s heat dissipation.