Analysis and Implementation of an Earth Observation mission using a Novel Space Mobility Software

The design of a space mission is a long and demanding process that requires extensive resources and meticulous attention to detail. Before a spacecraft can be launched and deployed into orbit, it must pass through a series of phases, sub-phases, and milestones, leading to a final version that is capable of performing its planned operations. This development process, characterized by continuous iterations of design, testing, trade-offs, and optimization, ensures the proper functioning of all subsystems in orbit. Among the essential tools supporting mission development — from the initial studies to end-of-life — are mission analysis platforms, which simulate and optimize trajectories (from terrestrial to interplanetary), operations, and system designs. With the rise of the New Space Economy, these tools have become even more crucial, not only for ensuring mission success but also for addressing issues such as space debris mitigation. They allow for the simulation of collision avoidance maneuvers and atmospheric re-entry. This is particularly significant considering miniaturized satellites like CubeSats, which are often less robust and reliable, due to lower costs and shorter development times. Given these constraints, it is often challenging to incorporate a propulsion system on board. Whether an innovative nano-thruster is installed or reliance is placed on alternative solutions such as natural decay for satellites in Low Earth Orbit (LEO) — as per the latest requirements of the European Space Agency (ESA) — mission analysis tools are indispensable for studying spacecraft mobility. This thesis explores the capabilities of '360', a mission analysis and space mobility software developed by IENAI SPACE, to simulate and analyze an operational CubeSat mission. IENAI SPACE, a space company, is focused on providing innovative in-space mobility solutions, particularly through its flagship products: the ATHENA electric propulsion system and the 360 software. The latter offers advanced tools for mission design, propulsion system optimization, and high-fidelity simulations, streamlining the engineering process for small satellites like CubeSats. The primary objective of this thesis is to evaluate the performance of 360 in replicating real-world satellite operations, with a specific focus on attitude dynamics. In particular, the study investigates an operational Earth Observation CubeSat mission characterized by stringent Attitude Determination and Control System (ADCS) requirements. By developing a detailed model of the CubeSat and its subsystems within the 360 environment, this project simulates various operational modes and pointing strategies. Additionally, the thesis validates the newly integrated ADCS module within the software and introduces navigation features to enhance attitude estimation. Ultimately, this study aims to contribute to the ongoing development of 360, expanding its functionality to support attitude dynamics and enhance its overall mission analysis capabilities.