Design concept of the structural bus of microsatellites for lunar missions

Space Industry has been developing colossally in the close past. Over the past 50 years, more than 860 microsatellites (10–100 kg), 680 nanosatellites (1–10 kg) and 38 picosatellites (0.1–1 kg) have been launched worldwide for doing different missions in the Low Earth Orbit (LEO). This paper fundamentally concentrates on the configuration idea of a microsatellite to function in a much farther orbit, i.e. the Low Lunar Orbit (LLO). Quite evidently heading off to the moon brings with itself a great deal of obstacles; and when the errand needs to be performed by a microsatellite the task is much more strenuous. A microsatellite has a considerable measure of imperatives added to it, particularly focusing on the mechanical regions of the satellite. A microsatellite is a miniaturised variant of a satellite where it needs to perform every one of the assignments an ordinary satellite would just with a lesser mass, lesser propellant and smaller components.