# Quasi-All-Passive Thermal Control System Design and On-Orbit Validation of Luojia 1-01 Satellite
## 3 TCS Design Proposal
### Heat Conduction Design  
Due to the poor heat conduction status of the satellite panels and instruments, an isothermal design for all internal instrument of the satellite is presented given the characteristics of the layout inside the satellite cabin. To improve the equivalent thermal conductivity and thermal conductive membrane structure strength, conductive grease and multilayer conductive membranes are applied to the TCS. Regions and the method of conductivity and are listed in Table 10.  
\begin{table}
\begin{tabular}{l l} \hline \hline \multicolumn{1}{c}{**Subject**} & **Heat Conductivity Method** \\ \hline \hline \multirow{2}{*}{Mounting surface among \(\pm Y\) and \(\pm Z\) panels} & Heat conductivity grease in contact surface and stickup of heat \\  & conductivity membrane \\ \multirow{2}{*}{Mounting surface between OBDH and \(-Z\) panel} & Heat conductivity grease in contact surface and stickup of heat \\  & conductivity membrane \\ \multirow{2}{*}{Mounting surface between navigation unit and \(-Y\) panel} & Heat conductivity grease in contact surface and stickup of heat \\  & conductivity membrane \\ \multirow{2}{*}{Mounting surface between reaction wheels and \(+Y\) panel} & Heat conductivity grease in contact surface and stickup of heat \\  & conductivity membrane \\ \multirow{2}{*}{Mounting surface between MEMS gyroscope and \(-X\) panel} & Heat conductivity grease in contact surface and stickup of heat \\  & conductivity membrane \\ \hline \hline \end{tabular}
\end{table}
Table 10: Description of regions and method of thermal conductivity applied in Luojia 1-01.  
\begin{table}
\begin{tabular}{l c} \hline \hline \multicolumn{1}{c}{**Regions and Instruments**} & **Amount of Layers** \\ \hline \(-X\) panel, \(\pm Y\) panel, \(\pm Z\) panel & 20 \\ \multirow{2}{*}{Internal surface of \(+X\) panel} & 20 \\  & Baffle of the camera & 20 \\ \multirow{2}{*}{Camera and its bracket} & 20 \\  & Battery (except the mounting suface) & 20 \\ \multirow{2}{*}{Star trackers and its brackets (2)} & 20 \\ \multirow{2}{*}{Brackets of the GPS Antennas (3)} & 20 \\ \multirow{2}{*}{Bracket of the digital sun sensor} & 20 \\ \hline \hline \end{tabular}
\end{table}
Table 8: Regions and instruments of Luojia 1-01 covered by MLI.  
\begin{table}
\begin{tabular}{l c} \hline \hline \multicolumn{1}{c}{**Subject**} & **Material of Heat Insulated Pads** \\ \hline \hline \multicolumn{1}{c}{Mounting surface between camera bracket and \(-X\) panel} & Polymide \\ \multicolumn{1}{c}{Mounting surface between baffle and camera} & Polymide \\ \multicolumn{1}{c}{Mounting surface between camera and focal plane unit} & Titanium alloy \\ \multicolumn{1}{c}{Mounting surface between battery and \(-Y\) panel} & Polymide \\ \multicolumn{1}{c}{Mounting surface between brackets of star trackers (2) and \(-X\) panel} & Polymide \\ \multicolumn{1}{c}{Mounting surface between GPS brackets (3) and \(-X\) panel} & Polymide \\ \multicolumn{1}{c}{Mounting surface between GPS brackets and \(-X\) panel} & Polymide \\ \multicolumn{1}{c}{Mounting surface between digital Sun sensor bracket and \(-X\) panel} & Polymide \\ \multicolumn{1}{c}{Mounting surface between data transmission antenna and \(+Z\) panel} & Polymide \\ \multicolumn{1}{c}{Mounting surface between TT\&C antenna and \(+Z\) panel} & Polymide \\ \multicolumn{1}{c}{Mounting surface between side \(-Z\) solar panel and \(-Z\) panel} & Polymide \\ \hline \hline \end{tabular}
\end{table}
Table 9: Description of instruments mounting surfaces using heat insulated pads.