## 4 Discussion
### Discussion of the Results of the Analysis of the Possible Change in Inclination
Conclusions concerning the swath width and flight duration:  
The swath width depends mainly on the quality of the sensor installed on the board of the satellite. Analyses reveal that for a satellite weighing 15 kg, the swath width is approx. 19.4 km. This is sufficient to provide an effective coverage of areas similar in size to Kampinos National Park during a single flight. However, it should be noted that a single flight will almost completely cover the area of the Kampinos National Park. Full coverage of the area requires two flights, since the scenes should partly overlap in order to ensure the consistency of observational data and an accurate representation of the terrain. However, for heavier satellites, the swath width may increase to 21 km, which involves higher costs of weight and of fuel consumption. A satellite equipped with a sensor that offers the swath width of 19.4 km seems to be sufficient for a mission that focuses on one region. Conclusions concerning the change in inclination:  
Although changing the orbit inclination may be essential in certain missions, the analysis revealed that in the case discussed here, it is rather not cost effective. Even a slight change in inclination (0.47\({}^{\circ}\) for a satellite with the initial weight of 15 kg and 0.5 kg of fuel) requires a large amount of fuel, which affects the overall efficiency of the mission. Considering that such change in inclination does not significantly improve the coverage of the target area, it seems more reasonable to focus on other operational areas. For example, one might use the change in the orientation of the satellite and sensor to prolong the duration of observations (by manoeuvres performed with the use of reaction wheels that consume power). Instead of changing the inclination, it is worth investing the fuel resources in regular manoeuvres to increase the altitude of the orbit, as they are more efficient and enable to extend the lifespan of the mission. Manoeuvres changing the inclination should be considered only in situations when they are absolutely necessary to achieve the goals of the mission. Conclusions concerning the power system and orientation manoeuvres:  
Using reaction wheels to precisely set the orientation of the satellite in reference to the selected area allows to extend the duration of observations. The analyses revealed that the M6P satellite by NanoAvionics, of the weight of 4.5 kg (without fuel) and the dimensions of 0.1 m \(\times\) 0.2 m \(\times\) 0.3 m, is optimised for short orientation manoeuvres. At the solar panel charging power of 70 W, the time needed for power regeneration after the manoeuvre is minimal, ranging from 0.0013 s (for the tilt angle of 1\({}^{\circ}\)) to 0.0386 s (for the angle of 30\({}^{\circ}\)). This enables the satellite's power system to support intensive observation operations, even if a large number of tilt manoeuvres are performed. Discussion of the Results of the Selection of the Optimum Nanosatellite Dedicated to Maximise the Specific Operational Task  
The analysis of Table 12 refers to various types of satellites in terms of their initial weight, fuel weight, specific impulse, and frontal surface. Some operational parameters, including the drag force, orbital energy loss, and the resulting decrease in altitude were also taken into account. The aim of the analysis was to select the optimum nanosatellite that will balance fuel efficiency, orbital stability, and the operational complexity of the mission. Satellites of a low initial weight, ranging from 8 kg to 10 kg are characterised by relatively low drag thanks to their small frontal surface of 0.02 m\({}^{2}\). This translates into a low drag force of 0.0000135 N, which, in turn, results in reduced orbital energy losses and a moderate decrease in altitude of approx. 2 km per half a year. However, in spite of low fuel consumption (approx.