## 5 Conclusions  
This paper analyzes and assigns various factors affecting the uncertain region of satellite laser communication loads in orbit in order to meet the requirements of rapid acquisition and chain construction in the business mode of laser communication satellites, reduce the acquisition time of laser communication loads between satellites, and narrow the orientation of laser communication loads to the uncertain region of the optical axis. As a result of the thermal deformation of the satellite bus, the angle variation between the laser communication load and star sensor should be limited to 0.16 mrad. The satellite's temperature field in orbit under high- and low-temperature situations is obtained by simulation analysis. As the input boundary conditions for satellite thermal deformation analysis, it is found that the influence of thermal deformation on the angle variation between the laser communication load and the star sensor installed on the honeycomb sandwich structure does not conform to the requirement of index allocation. It is necessary to optimize the thermal deformation control of the angle variation between the laser communication load and the star-sensor optical axis. A local accurate thermal deformation control method based on the design of a flexible isolation common physical reference is proposed in this study to reduce the influence of the whole satellite temperature variation on the laser communication load alignment uncertainty region and acquisition time. The goal of the optimization design is to connect the laser communication load and the star-sensor load using the same physical reference bracket and stable thermal deformation with 55% SiC/Al material. Second, it uses flexible isolation with the satellite bus to lessen the impact of the entire satellite's temperature variation on the support's temperature swings as well as the impact of the entire satellite's thermal deformation on the uncertain region of laser communication alignment. Finally, satellite load isolation was used to reduce the thermal control challenge, precisely manage the temperature of the isolated physical reference support, and lessen the impact of the physical reference support's temperature fluctuation. Topology optimization is used to determine the relative placement of the star sensor and the laser communication load and \(\varphi_{i}=15^{\circ}\) is the best result we select while taking into account the mass of the structure, the radius of rotation, and other engineering considerations. The reference bracket adopts an I-section design based on the structural topological relationship found through topological optimization, and size optimization establishes the critical dimensions. The combination of active and passive temperature control is adopted to control the temperature within the range between 19.86 \({}^{\circ}\)C and 22.18 \({}^{\circ}\)C so as to reduce the deformation of the reference structure itself. The thermal deformation between the \begin{table}
\begin{tabular}{c} **Capture Time** \\ **/s** \\ \end{tabular} \\ \hline
1 & 20 July 2022 & Scan & Gaze & 35 \\
2 & 21 July 2022 & Scan & Gaze & 45 \\
3 & 22 July 2022 & Gaze & Scan & 87 \\
4 & 22 July 2022 & Gaze & Scan & 42 \\
5 & 25 July 2022 & Scan & Gaze & 16 \\
6 & 25 July 2022 & Scan & Gaze & 28 \\
7 & 25 July 2022 & Scan & Gaze & 28 \\
8 & 25 July 2022 & Gaze & Scan & 16 \\
9 & 25 July 2022 & Gaze & Scan & 14 \\
10 & 25 July 2022 & Gaze & Scan & 18 \\
11 & 25 July 2022 & Scan & Gaze & 26 \\
12 & 25 July 2022 & Gaze & Scan & 18 \\
13 & 26 July 2022 & Scan & Gaze & 28 \\
14 & 27 July 2022 & Scan & Gaze & 29 \\ \hline \hline \end{tabular}
\end{table} 
Table 13: Statistical table of capture time in orbit. optimized laser communication load and the star sensor angle variation is decreased to 14.25\" according to the entire satellite simulation analysis of the modified structure. After completing the optimized design, we carried out ground and space test validations.