# Impact of Mega Constellations on Geospace Safety
## 4 Impact of Starlink on Control Avoidance Strategies for low-orbiting Satellites in Geospace
### Impact on LEO Space Target Satellite Deorbit Capability
Early orbital maneuvering is advantageous in the avoidance operation because it reduces the orbital maneuvering consumption of various types of target satellites. The increase in the frequency of avoidance operation after considering Starlink brings the increase of \(\Delta V\), and the change of \(\Delta V\) supports the huge avoidance consumption of target satellites after considering Starlink from the level of results. Starlink has a huge impact on the target satellite. What is more intuitive than the speed required for orbital maneuvering is the propellant required for orbital maneuvering. The change of speed requires propellant, because the three target satellites have different orbital maneuvering methods and different satellite \begin{table}
\begin{tabular}{c c c c c c c} \hline \hline \multirow{2}{*}{**Name**} & \multicolumn{2}{c}{**Revolutions**} & \multirow{2}{*}{**0**} & \multirow{2}{*}{**5**} & \multirow{2}{*}{**10**} & \multirow{2}{*}{**0 Revs**} \\  & _Starlink_ & & & & & & 10 Revs \\ \hline \multirow{4}{*}{JILIN-01-01} & _Without_ & ACPL-\(10^{-6}\) & \(5.07\times 10^{-2}\) & \(1.12\times 10^{-2}\) & \(5.58\times 10^{-3}\) & 9.08 \\  & _Starlink_ & & & & & & \\ \cline{2-6}  & _With_ & ACPL-\(10^{-6}\) & \(2.02\times 10^{-1}\) & \(5.64\times 10^{-2}\) & \(2.82\times 10^{-2}\) & 7.16 \\ \cline{2-6}  & _With Starlink ACPPL_ & & & & & & \\ \cline{2-6}  & _Without Starlink ACPPL_ & & & & & & \\ \cline{2-6}  & _Without Starlink ACPPL_ & & & & & & \\ \hline \multirow{4}{*}{CORVUS BC5} & _Without_ & ACPL-\(10^{-6}\) & \(9.78\times 10^{-2}\) & \(2.17\times 10^{-2}\) & \(1.08\times 10^{-2}\) & 9.055 \\  & _Starlink_ & & & & & & \\ \cline{2-6}  & _With Starlink ACPPL_ & & & & & & \\ \cline{2-6}  & _Without Starlink ACPPL_ & & & & & & \\ \cline{2-6}  & _Without Starlink_ & & & & & & \\ \cline{2-6}  & _Without_ & ACPL-\(10^{-4}\) & \(1.55\times 10^{-3}\) & \(1.19\times 10^{-4}\) & \(5.95\times 10^{-5}\) & 26.050 \\ \cline{2-6}  & _With Starlink_ & & & & & & \\ \cline{2-6}  & _With Starlink ACPPL_ & & & & & & \\ \hline \multirow{4}{*}{YAOGAN-35C} & _Without_ & ACPL-\(10^{-6}\) & \(6.68\times 10^{1}\) & \(2.96\) & \(1.48\) & 45.135 \\ \cline{2-6}  & _With Starlink ACPPL_ & & & & & & \\ \cline{2-6}  & _Without Starlink ACPPL_ & & & & & & \\ \cline{2-6}  & _Without Starlink ACPPL_ & & & & & & \\ \cline{2-6}  & _Without Starlink ACPPL_ & & & & & & \\ \cline{2-6}  & _Without Starlink ACPPL_ & & & & & & \\ \cline{2-6}  & _Without Starlink ACPPL_ & & & & & & \\ \hline \multirow{4}{*}{_Without Starlink_} & _Without_ & ACPL-\(10^{-4}\) & \(3.15\times 10^{-3}\) & \(1.06\times 10^{-3}\) & \(5.31\times 10^{-4}\) & 5.932 \\ \cline{2-6}  & _With Starlink ACPPL_ & & & & & & \\ \cline{2-6}  & _Without Starlink ACPPL_ & & & & & & \\ \cline{2-6}  & _Without Starlink ACPPL_ & & & & & & \\ \hline \end{tabular}
\end{table} 
Table 4: Comparison of data from \(\Delta V\) in Figure 9.  
masses, so in order to compare the propellant consumption more intuitively, the propellant mass fraction is used to show the propellant consumption. In Figure 10, the propellant mass fraction (PMF) required by the target satellite before and after Starlink is considered and the effect of early orbital maneuvering on PMF are shown. It can be observed from Table 5 that the trend of PMF is basically consistent with \(\Delta V\). PMF expresses the ratio of consumed propellant to satellite mass, which is defined as shown in Equation (5), \(M_{prop-per}\) represents the consumed propellant mass, \(M_{sat}\) represents the satellite mass, and \(M_{prop-all}\) represents all propellant masses. \[PMF=\frac{M_{prop-per}}{M_{prop-all}+M_{sat}} \tag{5}\]  
Figure 10: _Cont._  
For most satellites the probability of problems with the payload itself is extremely low, so the life of a satellite is designed to be measured in terms of propellant, and when the propellant is depleted, the life of a satellite is over.