## 1 Introduction
The method takes into account various types of sensors, the manoeuvre of their position, and various range efficiency indicators. On the other hand, [PERSON] et al. [23] presented a new method of configuration of orbital satellite constellations based on [PERSON]'s theorem. They emphasised that, due to the cost and risk reduction, it is essential to consider the problem of the reconfiguration of satellite constellation, with two limitations: minimisation of the overall mission costs and the desired final configuration. In order to meet the requirements in the monitoring of crisis situations, in a recent study, [PERSON] et al. [24] proposed a solution in the form of a multi-task framework for the problem of the optimisation of a satellite constellation that will be suitable for satellite constellation designers to identify the key compromises and make decisions. Although the issue of orbital manoeuvre optimisation has already been addressed in the literature, these issues are still relatively rarely explored, particularly in the context of nanosatellites, which operate under significant resource constraints, such as limited fuel mass, restricted energy availability, or simplified propulsion systems. The literature is dominated by studies focused on classical satellites or comprehensive optimisations using advanced algorithms, while there is a lack of simple and comparative analyses of manoeuvres typical for NanoSat-class missions. This study attempts to solve the issue of the possibility to conduct orbital manoeuvres of nanosatellites in the context of the maximisation of a specific operational task. The satellite may change its orbit, by performing an impulsive manoeuvre in a specific time, which, in turn, affects the efficiency of the orbit. The determination of a well-conceived power and direction of the impulse, as well as the moment of performing the manoeuvre, are of fundamental importance. As opposed to most of the previous works, which were aimed at the determination of a promising position (i.e., elements of the orbit) of the satellite, this study focuses on maximising a defined operational task by performing an orbital manoeuvre by the nanosatellite. The authors of this paper focus only on impulsive manoeuvres, where rockets are launched in relatively short series to create the required change in velocity (\(\Delta\)v). The main contribution of this research consists of conducting a detailed analysis of orbital manoeuvres of nanosatellites in terms of their fuel and energy efficiency. The analysis allowed for the identification of the optimal manoeuvring strategies that may contribute to improving the efficiency of satellite missions. Numerical experiments were conducted, including various operational scenarios, such as changes in the altitude, inclination of the orbit, and the tilt of the satellite platform, with the aim to assess the efficiency and the energy costs of manoeuvres in the context of their practical applications. The performed analyses revealed the following:  
1. Different types of orbital manoeuvres of nanosatellites differ significantly in terms of fuel consumption, depending on the scale of change in the required parameter. For example, the altitude change manoeuvre is characterised by relatively low fuel consumption when the impulses are precisely planned, but the consumption of fuel for additional orbital manoeuvres is significantly limited by performing regular orbit adjustments. 2. Parameters, such as altitude, inclination, and the tilt of the satellite have a major influence on the fuel and energy requirements of the manoeuvres. The optimum strategies vary depending on the specific requirements of the given mission, such as the need for the precise coverage of target areas or to maintain the orbit for a longer period. 3. Impulsive manoeuvres proved to be an effective method to modify the parameters of the orbit, enabling precise control over the trajectory with a minimum time required to perform the manoeuvre.