## 4 Simulation and Analysis
### Comparison between SS-LCBBA and Baseline Algorithms
#### 4.2.2 Satellite Cluster Architecture Settings  
In this paper, the satellite constellation configuration of Walker is defined as \(i:t/p/f=90^{\circ}:28/4/2\), where \(i\) is the inclination, \(t\) is the total number of satellites, \(p\) is the number of equally spaced planes, and \(f\) is the relative spacing between satellites in adjacent planes. The notation means that the satellite constellation consists of 28 satellites with an orbital inclination of 90 degrees, evenly distributed over four orbital planes, with relative spacing being set to two. The orbital altitude of the satellite constellation is set to 1200 km.  
Each satellite carries an infrared sensor. The visual field of the sensor is a cone with an angle of \(3^{\circ}\), and the detection distance of the sensor is \(r=6500\) km. The sensor has two states: standby and tracking. The sensor in the standby state is capable of flying back to the target position at a maximum rotation speed up to \(60^{\circ}/\)s. In the tracking state, the sensor is constrained by the imaging stability, so the rotation speed is set to \(5^{\circ}/\)s. The range of the sensor pitch angle [\(\theta_{\text{min}}\), \(\theta_{\text{max}}\)] is \([\arcsin(\frac{R_{e}}{H_{s}+R_{e}})\), \(\arcsin(\frac{H_{s}+R_{e}}{H_{s}+R_{e}})\)], where \(H_{s}\) is the satellite orbit altitude, and \(H_{n}\) is the height of near space.  
The interstellar link uses laser communication. In order to reduce link loss, it is necessary to avoid crossing the near space, so a minimum link height needs to be considered link height \(H_{c}\). The maximum inter-satellite communication distance can be expressed as:  
\[L_{r}^{\text{max}}=2\sqrt{\left(H_{s}+R_{e}\right)^{2}-\left(H_{n}+R_{e} \right)^{2}} \tag{35}\]  
\begin{table}
\begin{tabular}{c c c c c c} \hline \hline \(\theta\) (**deg**) & \(\phi\) (**deg**) & \(h\) (km) & \(v\) (m/s) & \(\gamma\) (**deg**) & \(p\) (**deg**) \\ \hline
0 & 0 & 59 & 3060 & \(-1\) & 15 \\
10 & 30 & 56 & 3060 & \(-5\) & \(-20\) \\ \(-10\) & \(-30\) & 46 & 2040 & \(-4\) & 30 \\ \hline \hline \end{tabular}
\end{table}
Table 1: Initial conditions.  
\begin{table}
\begin{tabular}{c c} \hline \hline Trajectory 1 & HGV does \(SG\) glide in the longitudinal direction. The normalized lift coefficient for \(SG\) maneuver is \(c_{l}=0.7\). It does no lateral evasive maneuver. \\ \hline Trajectory 2 & HGV does \(QEG\) glide in the longitudinal direction. The normalized lift coefficient for \(QEG\) maneuver is \(c_{l}=1.6\). It does lateral evasive maneuvers with the bank angle of \(\pm 10^{\circ}\) degrees at 200\(\sim\)400 s, no maneuvers laterally with the bank angle of \(\pm 20^{\circ}\) degrees at 401\(\sim\)750 s, and lateral evasive maneuvers after 750 s. \\ \hline Trajectory 3 & HGV does \(QEG\) glide in the longitudinal direction. The normalized lift coefficient for \(QEG\) maneuver is \(c_{l}=1.6\). It does lateral turning maneuvers with the bank angle of \(-70^{\circ}\) degrees at 200\(\sim\)600 s, and lateral turning maneuvers with the bank angle of \(+70^{\circ}\) degrees at 600\(\sim\)1200 s, and lateral evasive maneuvers after 1200 s. \\ \hline \hline \end{tabular}
\end{table}
Table 2: Maneuver type settings.