## 4 Discussion
### Discussion of the Results of the Analysis of the Possible Change in Inclination  
This sub-section discusses the conclusions from the data presented in Table 9, focusing, in particular, on the key parameters, such as the initial and end weight of the satellite, increase in velocity, change in inclination, and the influence on the duration of the flight over a given area. Reducing the weight of the satellite by consuming fuel has a direct influence on the satellite's ability to perform the manoeuvre changing the inclination. For example, as the end weight increases from 7.5 kg (for a satellite of the initial weight of 8 kg) to 14.3 kg (for the initial weight of 15 kg), one may notice that the fuel consumption increases, which offers more possibilities to change the inclination. The possible change in inclination depends on the velocity increase achieved as a result of the manoeuvre. The higher this increase, the larger the possible change in inclination. For example, for a satellite of the initial weight of 15 kg and fuel weighing 0.5 kg, the change in inclination is approx. 0.009 rad (0.54\({}^{\circ}\)), while for a satellite with 0.7 kg of fuel, the change in inclination is approx. 0.014 rad (0.83\({}^{\circ}\)). An increase in velocity is the key factor that determines the satellite's ability to change the orbit inclination. For larger amounts of fuel, the values increase, which enables a larger change in inclination. For example, for the fuel weight of 0.5 kg, the increase in velocity is 73.17 \(\frac{\mathrm{m}}{\mathrm{s}}\), while for the fuel weight of 0.7 kg, it increases to 112.52 \(\frac{\mathrm{m}}{\mathrm{s}}\). The duration of the satellite's flight over the given area also depends directly on the angle of inclination of the trajectory in reference to the equator. As this angle increases, the duration of the flight over the given area decreases. For example, for a satellite with 0.5 kg of fuel, the duration is 3.87 s, while for larger amounts of fuel (e.g., 0.7 kg), the duration is 3.29 s. Even slight changes in inclination may significantly influence the satellite's ability to observe specific areas of the Earth. For example, although a change in inclination by 0.83\({}^{\circ}\) may be sufficient to improve the coverage of the target area, a larger amount of fuel will allow to adjust the satellite's trajectory to its mission more accurately. Improving the manoeuvring capacity of the satellite by increasing fuel consumption makes it possible to better adjust the orbit to the objectives of the mission. Effective exhaust velocity that results from the specific impulse also influences the satellite's ability to change its orbit. Higher specific impulse means an increased exhaust velocity, which enables more efficient fuel consumption. For a satellite with the specific impulse of 220 s, effective exhaust velocity is 1867.80 \(\frac{\mathrm{m}}{\mathrm{s}}\), which allows to achieve a higher increase in velocity than for a satellite with a specific impulse of 180 s, where the exhaust velocity is 1528.20 \(\frac{\mathrm{m}}{\mathrm{s}}\). In conclusion, a larger amount of fuel and higher specific impulse enable the satellite to introduce larger changes to the inclination and velocity, which is essential for adjusting the orbit to mission objectives. The duration of the satellite's flight over the area of interest decreases with the increase in the angle of trajectory inclination, which affects the efficiency of observations. The analysis of Table 9 revealed one anomaly. In the table, for the fuel weight of 0.35 kg, the angle of the inclination of trajectory in reference to the equator is 1.263 rad. This is a relatively large angle, which influences the satellite's velocity in reference to the surface of the Earth. The angle corresponds to orbit inclination, which means that the satellite moves more diagonally in reference to Earth's surface, which reduces the velocity of the projection of its movement on the surface of our planet.