## 4 Discussion
### Discussion of the Results of the Analysis of the Possible Change in Inclination
0.3 kg), nanosatellites of such low weight may have limited operational capacity, including fewer telescopes on board or limited fuel capacity, which reduces their ability to perform a larger number of adjustment manoeuvres. For satellites of medium weight, from 11 kg to 15 kg, the frontal surface increases to 0.03 m\({}^{2}\), which leads to a stronger drag force of 0.00000203 N. In spite of larger energy losses (approx. 40960 J) and drops of altitude of about 2 km, nanosatellites in this weight category offer a better balance between efficiency and functional capacity. Higher weight allows them to carry more fuel, which improves the flexibility of the mission. For example, a nanosatellite weighing 15 kg, with a specific impulse of 220 s, uses in total, approx. 0.442 of fuel in six months. This is acceptable in the context of long-term orbital missions. Thanks to their moderate fuel consumption and better orbital stability, nanosatellites in this weight category seem to be more universal. Finally, heavy satellites that weigh from 16 kg to 18 kg are characterised by a larger frontal surface of approx. 0.04 m\({}^{2}\), which causes a further increase in the drag forces to 0.00000270 N. Increased orbital energy losses (54613.72 J) and drops in altitude exceeding 2.4 km in six months require higher fuel consumption. A satellite that weight 18 kg uses as much as 0.488 kg of fuel. In spite of their great operational capacity, nanosatellites in this category are less fuel efficient, and their weight may limit the viability of an orbit launch. Conclusions:  
Although heavier satellites offer more advanced functional capabilities, their fuel requirements are increasing. Based on the data analysis, one may assume that the optimum configuration is a satellite weighing 5 kg. This range of weight ensures a proper balance between the capacity and orbital stability, while, at the same time, enabling the installation of an advanced sensor. The specific impulse of 220 s guarantees high fuel efficiency with moderate technical requirements. Higher values of the specific impulse might reduce fuel consumption, yet they are less cost-efficient for satellites in this weight category. The weight of fuel of 0.5 kg is perfectly suitable for missions lasting up to six months, provided that the amount of fuel spent on manoeuvres to adjust the orbit is moderate. This amount allows six manoeuvres to be performed, increasing the altitude of the orbit by 643 m, which effectively prevents orbit degradation. The drag force increases in proportion to the face area, which in turn, scales with the mass of the satellite. The frontal surface of 0.02 m\({}^{2}\) that is determined by the satellite's dimensions minimises the influence of drag, which translates into lower energy losses and a more stable trajectory. This type of nanosatellite offers a compromise between fuel efficiency and operational capacity. The fuel consumption per six months, taking into account only the manoeuvreof increasing orbit altitude, is 0.154 kg, which enables efficient resource management while maintaining orbital stability. The selection of the nanosatellite with the parameters presented above minimises both the energy losses and the complexity of the mission, while ensuring sufficient flexibility for potential modifications of the orbit.