## Conflicts of Interest: The authors declare no conflict of interest. ### Time Window Calculation Method  
The satellite needs to aim its camera to the target so that the target is within the view of field through attitude maneuver and then maintain the attitude for push-broom imaging while observing the target. The start time and the end time of the observation can be calculated as  
\[ \begin{cases}t_{osi}=t_{oi}-\Delta t_{o}/2\\ t_{oci}=t_{oi}+\Delta t_{o}/2^{\prime}\end{cases}  \tag{1}\]  
where the moment when the optical axis of the satellite camera is aligned with the target is \(t_{oi}\) and the satellite observation time is a fixed value \(\Delta t_{o}\). The satellite studied in this paper is an AEOS that can perform attitude maneuvers around the roll and pitch axes. This allows the satellite to observe the target at different moments when it is visible. The time period when the target is observable by the satellite is the observation time window. The visibility condition requires that the target be visible to the satellite, without being blocked by the Earth. Meanwhile, it also requires the satellite to satisfy the satellite attitude cone angle constraint when pointing at the target. The satellite attitude cone angle constraint is that the angle \(\alpha_{c}\) between the \(Z\)-axis of the satellite body coordinate system and the \(Z\)-axis of the orbit coordinate system must not be greater than the maximum allowable half cone angle \(\alpha_{\rm{cmax}}\) during the operation period, which is  
\[\frac{(\mathbf{r}_{ti}-\mathbf{r}_{ri})\cdot(-\mathbf{r}_{ri})}{|\mathbf{r}_{ti}-\mathbf{r}_{ri}|| -\mathbf{r}_{ri}|}\leq\alpha_{\rm{cmax}}, \tag{2}\]  
where \(\mathbf{r}_{ri}\) is the satellite position vector in the inertial coordinate system, and \(\mathbf{r}_{ti}\) is the target position vector in the inertial coordinate system, whereas the observation time window \([t_{psi},t_{wei}]\) can be calculated through state propagation. In this paper, each only scheduling considers the scheduling period within one orbital period; if the scheduling period is more than one orbital period, the scheduling of subsequent orbital periods can employ this method repeatedly. In the meantime, targets that are not visible during the scheduling period are not considered. These invisible targets are judged and eliminated before scheduling, therefore, the number of observation time windows \(n_{t}\) corresponds to the number of targets. \(\Delta t_{A,ij}\) is the attitude maneuver time between the observation of target \(i\) and target \(j\). In this paper, the camera was installed along the \(+Z\)-axis of the satellite body coordinate system, and the satellite observation attitude \(A_{i}=[\varphi_{i},\theta_{i},\psi_{i}]\) was the Euler angle of the satellite camera's optical axis pointing to target \(i\) at \(t_{oi}\). The attitude maneuver time can be computed as \(\Delta t_{A,ij}=f_{t}\left(A_{i},A_{j}\right)\), where \(f_{t}\) is a function for calculating the attitude maneuver time according to the current attitude \(A_{i}\) and the next attitude \(A_{j}\) of the satellite. When a satellite establishes a data connection link to a ground station for data transmission, the satellite antenna and ground station should be visible to one another. Antennas that are commonly used on satellites include shaped-beam antennas and rotatable spot beam antennas. The beam angle of rotatable spot beam antenna is small, but the coverage can be increased by rotating the antenna pointing, and the sum of rotation range and beam angle is equivalent to the antenna coverage beam angle. As for the shaped-beam antenna, it is non-rotatable and has a larger beam angle, in which this beam angle is the antenna coverage angle that is defined as \(\alpha_{b}\).