# Quasi-All-Passive Thermal Control System Design and On-Orbit Validation of Luojia 1-01 Satellite
## 6 Analysis of in-Orbit Performance and Modeling Modification
### Thermal Model Modification  
Based on the in-orbit performance temperature data, the key thermal analysis parameters such as thermal coupling value, surface radiation properties, equivalent thermal conductivity of MLI and power consumption of instruments are amended and Monte Carlo methods and sensitivity analysis are introduced in this process [13].  
First the parametric sensitivity analysis is completed by the Monte Carlo method. Then according to the thermal balance test and in-orbit data, the Latin hypercube sampling and simplex mixed methods are applied to correct the model parameters by the classification layer by layer, and the optimal values are calculated. The amended results and comparison before and after the changes is shown in Table 17. From the comparison, it can be seen that the difference between in-orbit data and the ground test and thermal analysis data is within 3 \({}^{\circ}\)C, which indicates the model modification is effective.  
\begin{table}
\begin{tabular}{c c c c c c c} \hline \hline \multirow{2}{*}{**Heating Region**} & \multirow{2}{*}{\begin{tabular}{c} **Designed Power** \\ **Consumption** \\ **(W)** \\ \end{tabular} } & \multirow{2}{*}{\begin{tabular}{c} **On-Orbit Power** \\ **Consumption** \\ **(W)** \\ \end{tabular} } & \multirow{2}{*}{\begin{tabular}{c} **Power in High** \\ **Temp of Test** \\ **(W)** \\ \end{tabular} } & \multirow{2}{*}{\begin{tabular}{c} **Power in Low** \\ **Temp of Test** \\ **(W)** \\ \end{tabular} } & \multirow{2}{*}{\
\begin{tabular}{c} **Power in High** \\ **(W)** \\ \end{tabular} } & \multirow{2}{*}{
\begin{tabular}{c} **Power in Low** \\ **Temp of Test** \\ **(W)** \\ \end{tabular} } \\  & & & & & & **Thermal** & **Thermal** \\ \hline Heating region of the camera & 2 & 0.48 & 0.36 & 1.4 & 0.30 & 1.18 \\ Backup heating region of the camera & 2 & 0 & 0 & 0 & 0 & 0 \\ Heating region of the battery & 2 & 1.20 & 0.86 & 1.32 & 0.78 & 1.34 \\ Backup heating region of the battery & 2 & 0 & 0 & 0 & 0 & 0 \\ sum & 8 & 1.68 & 1.22 & 2.72 & 1.08 & 2.52 \\ \hline \hline \end{tabular}
\end{table}
Table 16: Temperature of instruments from on-orbit, ground thermal balanced test and thermal analysis.  
\begin{table}
\begin{tabular}{c c c c c c} \hline \hline \multirow{2}{*}{**Subject**} & \multirow{2}{*}{\begin{tabular}{c} **On-orbit Balanced** \\ **Temp (\({}^{\circ}\)C)** \\ \end{tabular} } & \multirow{2}{*}{\begin{tabular}{c} **High Temp in** \\ **Test (\({}^{\circ}\)C)** \\ \end{tabular} } & \multirow{2}{*}{\
\begin{tabular}{c} **Low Temp in Thermal** \\ **Test (\({}^{\circ}\)C)** \\ \end{tabular} } & \multirow{2}{*}{
\begin{tabular}{c} **Low Temp in Thermal** \\ **Analysis (\({}^{\circ}\)C)** \\ **Before** \\ \end{tabular} } \\  & & & & & \\ \hline Camera-1 & 12.20 & 12.8 & 12.5 & 11.3 & 11.9 \\ Camera-2 & 12.94 & 14.0 & 13.2 & 12.0 & 12.5 \\ \hline \hline \end{tabular}
\end{table}
Table 17: Amendment comparison of temperature of instruments from in-orbit and thermal analysis.  
\begin{table}
\begin{tabular}{c c c c c c} \hline \hline \multirow{2}{*}{**Subject**} & \multirow{2}{*}{\begin{tabular}{c} **On-orbit Balanced** \\ **Temp (\({}^{\circ}\)C)** \\ \end{tabular} } & \multirow{2}{*}{\begin{tabular}{c} **High Temp in** \\ **Test (\({}^{\circ}\)C)** \\ \end{tabular} } & \multirow{2}{*}{\
\begin{tabular}{c} **Low Temp in** \\ **Test (\({}^{\circ}\)C)** \\ \end{tabular} } & \multirow{2}{*}{
\begin{tabular}{c} **High Temp in Thermal** \\ **Analysis (\({}^{\circ}\)C)** \\ **Before** \\ \end{tabular} } \\  & & & & \\ \hline \hline \end{tabular}
\end{table}
Table 15: Temperature of instruments from on-orbit, ground thermal balanced test and thermal analysis.