# A Lunar-Orbiting Satellite Constellation for Wireless Energy Supply
## 8 Discussion and Conclusions  
This paper aimed to demonstrate the potential of the proposed system focusing on the selection of the optimal laser, different orbits, and initial sizing of satellite batteries and ground receivers. Additionally, a power budget analysis was conducted for various scenarios considering different orbits, Moon bases, and system architectures. With the renewed interest in lunar exploration and the increasing number of planned lunar missions, the energy demand is expected to rise. The highlighted system offers scalability in meeting  
Figure 17: Power vs. time with a three-satellite constellation placed in an Earth–Moon DRO with different maximum transmission angles. (**a**) \(\alpha_{max}=50^{\circ}\); (**b**) \(\alpha_{max}=60^{\circ}\); (**c**) \(\alpha_{max}=70^{\circ}\); (**d**) \(\alpha_{max}=80^{\circ}\). Figure 18: Power vs. time with a 10-satellite constellation placed in an Earth–Moon DRO with different maximum transmission angles. (**a**) \(\alpha_{max}=50^{\circ}\); (**b**) \(\alpha_{max}=60^{\circ}\); (**c**) \(\alpha_{max}=70^{\circ}\); (**d**) \(\alpha_{max}=80^{\circ}\). the power requirements without the need for designing and launching new technologies for each specific mission, unlike vertical solar panels or future lunar nuclear reactors. The obtained results indicate that a constellation of 10 satellites could potentially provide up to 519 kWh of power in a single day, under the best sub-case scenario, utilizing current technologies. Further advancements in laser technology will increase the available power onboard and enable new possibilities for WPT in future lunar exploration. However, the amount of power transmitted is closely tied to the duration of time a satellite remains within the transmission cone. Future developments in pointing system accuracy may allow for satellites to be placed in higher orbits, resulting in longer durations within the cone and higher power transmission capabilities. The adaptability of satellite orbital disposal to the needs of the lunar base is a significant advantage of this solution. For instance, in scenarios requiring power peaks for short durations, such as mining activities, satellites can be positioned in close proximity to each other (with slight differences in true anomalies), enabling power peaks equivalent to \(N\times 10.34\) kW, where \(N\) represents the number of satellites within the transmission cone. The choice of laser technology demonstrates its suitability for transmitting specific power values, although further development and TRL advancements are necessary. Future focus on the development of laser beam sources will play a crucial role in improving the TRL of the system, setting the stage for their use in upcoming space missions. The overall efficiency of the system primarily depends on the laser efficiency and receiver cell efficiency. Starting from solar power, considerations include the solar panel efficiency of the satellite and distribution losses from the battery to the laser. Other losses related to the shape and size of the receiver can be minimized by utilizing the proposed design. Future studies will focus on identifying unexplored orbits that facilitate power transmission to key surface points of interest, such as the lunar base's south pole. These investigations will aim to minimize fuel requirements for maintaining stability. Furthermore, the feasibility of long-duration transmissions, such as in the \(\alpha_{max}=80^{\circ}\) case, will be examined, assessing the limits of the satellite's thermal management system and pointing system, allowing for transmission over greater distances. The development of these technologies could significantly increase the amount of energy transmitted. In general, the future of this field is expected to witness the advancement of high-power lasers for increasingly effective space applications, leading to substantial improvements in the amount of energy transmitted.