## 1 Introduction
This mode \"intercepts\" the GEO belt by commanding the observation sensor to set up a fence with an FOV across a \(30^{\circ}\) orbit on the GEO belt, allowing for the observation of more than 85 percent of the GEO objects in a single day [13]. [PERSON] et al. presented a new pseudo-fixed latitude observation mode in 2017 based on the GEO belt development rule. In this mode, the sensor's orientation is dynamically modified based on the GEO band's sinusoidal distribution, allowing most GEO targets to be viewed with a limited FOV [14]. The summarized research status shows that when satellite detection needs are specified, the orbital features and observation tactics of the satellite have a direct impact on the sensor's FOV. For space-based visual sensors, there are commonly two observing modalities. The first is the natural rendezvous observation mode, in which the sensor is typically fixed on the observation satellite and passively monitors the GEO target using only the features of the satellite's own orbital motion. The other option is active observation, in which the sensor's orientation is modified using various tactics to cover certain spatial regions. The pseudo-fixed latitude observation mode is a novel, natural intersection mode [14], and the natural rendezvous observation mode is a frequently utilized observation mode for space-based surveillance systems. Because LEO satellites have a small orbital radius, they may scan the GEO band numerous times a day [15]. DDSSO is the low orbit with a short orbital period. In this orbit, satellites can run multiple laps in one day and visit GEO targets multiple times to achieve higher observation efficiency. At the same time, the satellite runs on the DDSSO and can maintain good optical observation conditions throughout the day. Because of their orbital features, DDSSO satellites offer favorable optical observation conditions for most of the year [16]. As a result, the observation satellites specified in this study are LEO satellites in DDSSO that naturally rendezvous with the GEO target in the pseudo-fixed latitude observation mode. There are four common approaches for getting the satellite to view the chosen GEO targets in a short amount of time:  
1. An observation constellation is made up of many satellites carrying separate sensors. 2. Building an observation fence to cover the whole GEO belt using active observation mode. 3. Multiple sensors with different orientations are carried by a single satellite. 4. A sensor with a large enough FOV is carried by a single satellite. From a purely engineering standpoint, using a single satellite to perform an observation plan is easier than using numerous satellites, and carrying a single sensor on the same satellite is easier than carrying multiple sensors of the same sort at the same time. Furthermore, the approach of erecting the observation fence is no longer appropriate due to the evolution of the PP zone of the GEO belt. As a result, the most typical observation strategy is to carry a single big FOV sensor on a single satellite. The implementation of this observation method is complicated by the need to achieve a broad FOV. However, as image sensor production technology improves, the area array of the image sensor grows, and the FOV that can be reached by a single sensor grows. Furthermore, related researchers presented a multi-scale FOV splicing technology to overcome the problem of big FOV observations being difficult to perform, assessed the practicality of this technology through tests, and applied it to an actual space-based detection system [17; 18]. The higher the FOV, the better the observation effectiveness of the space-based detecting system, but the more difficult the image sensor manufacturing process becomes. Simultaneously, it mandates the employment of more image sensors for splicing, increasing the cost and difficulty of system development significantly. As a result, selecting an appropriate FOV for space-based detection systems is essential.