## 3 Background
### Other Key Components Selection
#### 3.5.3 Guidance, Navigation, and Control System
\begin{table}
\begin{tabular}{c c c c c c} \hline
**Product** & **Manufacturer** & **Mass (kg)** & **Peak Torque** & **Momentum** & **Radiation** & **Status** \\  & & **(N m)** & **Capacity (N m s)** & **Tolerance (Krad)** & **T**ela \\ \hline
10 SP-M & Surry Satellite Technology, & & & & \\  & Guildford, UK & 0.96 & 0.011 & 0.42 & 5 & TRI9 \\
100 SP-O & Surry Satellite Technology & 2.6 & 0.11 & 1.5 & 5 & TRI9 \\ RW-0.03 &
\begin{tabular}{c} Sinclair Interplanetary, \\ Toronto, ON, Canada \\ \end{tabular} & 0.185 & 0.002 & 0.04 & 20 & TRI9 \\ \hline \end{tabular}
\end{table} 
Table 15: Small Space Craft Reaction Wheel Performance Data [23]. Sun sensors present another viable technology for integration into the guidance system (Table 19). They possess the capability to approximate the Sun's position relative to the CubeSat body to estimate the craft's altitude. Sensors classed as \"course\" provide a non-directional cosine output, and therefore 6 units are required to be integrated into the CubeSat [55]. The alternative \"fine\" sun sensors require a minimum of 4 to be integrated into the design. \begin{table}
\begin{tabular}{c c c c c c} \hline \hline
**Product** & **Manufacturer** & **Mass (kg)** & **Peak Dipole (A m\({}^{2}\))** & \
\begin{tabular}{c} **Radiation** \\ **Tolerance (Krad)** \\ \end{tabular} & **Status** \\ \hline MTR-5 &
\begin{tabular}{c} Surry Satellite Technology \\ ZARM, Bremen, Germany \\ Space Flight Industries, \\ Seattle, WA, USA \\ \end{tabular} & 0.5 & 5 & 5 & 5 & 5 \\ \hline \hline \end{tabular}
\end{table} 
Table 17: Magnetorquer Performance Data [23]. \begin{table}
\begin{tabular}{c c c c c c c} \hline \hline
**Product** & **Manufacturer** & **Mass (kg)** & **Resolution** & **Orthogonality** & \begin{tabular}{c} **Radiation** \\ **Tolerance (Krad)** \\ \end{tabular} & **Status** \\ \hline \multirow{3}{*}{Magnetometer} & \
\begin{tabular}{c} New Space Systems, \\ Someest West, \\ South Africa \\ PNI Corp, \\ Santa Rosa, CA, USA \\ \end{tabular} & 0.2 & 6.5 nT & \textless{}1 deg & 10 & TRL9 \\ \cline{1-1} \cline{2-6} MicroMag3 &
\begin{tabular}{c} Norms Space Systems, \\ South Africa \\ PNI Corp, \\ Santa Rosa, CA, USA \\ \end{tabular} & 0.2 & 15 nT & \textless{}1 deg & 10 & TRL9 \\ \cline{1-1} \cline{2-6} Magnetometer & Surry Satellite Technology & 0.19 & 10 nT & \textless{}1 deg & 5 (Si) & TRL9 \\ \hline \hline \end{tabular}
\end{table} 
Table 18: Magnetometer Performance Data [51; 52]. Figure 34: KySat-1 Altitude Control System [54]. \begin{table}
\begin{tabular}{c c c c c c} \hline \hline
**Product** & **Manufacturer** & **Mass (kg)** & **Accuracy** & \begin{tabular}{c} **Radiation** \\ **Tolerance (Krad)** \\ \end{tabular} & **Status** \\ \hline Fine (Digital) Sun Sensor & \begin{tabular}{c} New Space System \\ Adole, \\ Marlborough, MA, USA \\ Space Micro, \\ San Diego, CA, USA \\ \end{tabular} & 0.035 & 0.1 deg & 10 & TRL9 \\ \cline{1-1} \cline{2-6} Fine (Digital) Sun Sensor & \
\begin{tabular}{c} New Space System \\ Adole, \\ Marlborough, MA, USA \\ Space Micro, \\ San Diego, CA, USA \\ \end{tabular} & 0.068 & 0.75 deg & 10 & TRL9 \\ \cline{1-1} \cline{2-6} CSS-01 &
\begin{tabular}{c} Space Micro, \\ San Diego, CA, USA \\ \end{tabular} & 0.0414 & 5 deg & 10 & TRL9 \\ \hline \hline \end{tabular}
\end{table} 
Table 19: Sun Sensor Performance Data [23]. The NSS CubeSat sun sensor costs \(\ell\)2646, as 6 would be required to be included in the design a total cost of \(\ell\)15,876. Earth Sensor technology range from simplistic infra-red horizon crossing indicators, to more advanced thermopile sensors [23]. The MAI-SES IR Earth sensor costs \(\ell\)11,498 for two units, integrating 4 thermopile detectors. It has a mass of 33 g, with an operating current and voltage of 40 mA and 3.3 V respectively. It has dimensions of 43.3 \(\times\) 31.8 \(\times\) 31.8 mm (Table 20) [56]. Gyroscopes are designed to measure angular velocity of a body. In the CubeSat domain gyroscopes are typically fiber-optic or MEMS, Table 21 illustrates Gyro performance data [23].