Mission analysis of Small Debris Removal with Laser Ablation

In recent decades, the proliferation of space debris has emerged as a critical chal- lenge for space operations and satellite missions. Space debris poses significant risks to operational spacecraft, increases the likelihood of damage, and compli- cates future space endeavors. The accumulation of debris in Earth’s orbit has reached alarming levels, necessitating the implementation of effective mitigation strategies to ensure the long-term sustainability of space activities. A particularly severe threat is posed by small debris fragments, which constitute the majority of orbital debris currently present in Low Earth Orbit (LEO). These fragments are especially hazardous due to their high velocity and the inability to be detected from ground-based control stations. This thesis explores space debris mitigation through various active removal tech- niques, focusing on laser ablation technology. Laser ablation is a promising method for removing small debris (1 to 10 cm) by using high-powered lasers to vaporize a thin layer of the debris surface. This creates a plasma plume that alters the object’s trajectory, helping it reenter Earth’s atmosphere where it safely burns up. The study begins by analyzing the evolution of the space environment and the des- ignation of protected orbital regions, assessing the space industry’s impact over the past six decades. It then examines various active debris removal methods, compar- ing their effectiveness, feasibility, and technological readiness. The primary focus is on laser ablation, exploring its principles and its impact on the de-orbiting time of debris. The physical and mathematical principles underpinning the analyses and simula- tion codes are then presented and discussed in detail. The theoretical framework focuses on evaluating temporal changes in a body’s semi-major axis using Gauss’s planetary equations. Subsequent sections explore how the de-orbiting time of space debris varies based on the object’s physical parameters and how it is affected by laser intervention. A thorough investigation is also conducted into the problem of identifying small- sized debris, with an in-depth analysis of the detection and identification systems suitable for this purpose. This analysis has allowed for the determination of the operational ranges (range of action in which debris can be identified and beamed) of the satellites, taking into account both geometric constraints and orbital dy- namics, an essential factor in the development of different mission architectures. Finally, the mission design and various architectural configurations are presented. These architectures are assessed through trade-off analyses, ultimately leading to the selection of the configuration that best fulfills the mission requirements. Specifically, a satellite constellation has been developed, capable of adjusting its semi-major axis to modify its operational range, operating within an altitude range of 250 to 1000 kilometers and an inclination range between 60 and 105 degrees. Each satellite is equipped with a dedicated payload for the detection and identifi- cation of debris, whose systems have been previously analyzed, as well as a laser payload specifically designed for the surface ablation of space debris. The final architecture enables the removal of approximately 25% of small-sized debris within a timeframe of less than 25 years, as defined by the IADC in the first Space Debris Mitigation Guidelines, using fewer than 20 satellites.