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Space debris mitigation: dynamics based on maneuvers combined with ground laser and space blower propulsion


The main objective of this project is to develop and deepen the study of space debris mitigation using orbital maneuvers with and without laser propulsion and the "space blower" concept. This will be accomplished through the elaboration of mathematical models, considering the influence of the ground laser pulse in aiding reentry or escape maneuvers, as well as studying collision avoidance between debris and a space vehicle based on the just-in-time method (JCA). Such study tools will be used as a form of space mitigation, as well as explore the dynamics of debris re-entry through propulsion generated by a space fan. It will also be possible to evaluate the efficiency of the laser pulse on the orbital characteristics of individual space debris or clouds after passage near the Earth considering two and three-dimensional cases, as well as the variation of the space density, which will help in determining the probability of collision with a target. However, it will make it possible to understand its trajectory, its formation before and after passage by massive bodies, and the perturbative effect on the fragments. Finally, it will be possible to study the best characteristics of the space fan to achieve an efficient re-entry at the lowest possible cost. The explanation for the formation of this debris and the cloud can be given in several ways, particularly through explosions between one or more space vehicles and meteor fragmentation. A computational model will be built, implementing various perturbations, such as solar radiation pressure, third body (e.g. Sun-Earth-Moon), and atmospheric drag. After building the model, in particular, we will evaluate the optimum parameters with the help of the laser, to perform a re-entry of the debris or send it to another orbit. In this study, the system formed by the Sun, Earth, and fragments passing at a distance between $100km-1000km$ from Earth will be considered, evaluating the efficiency of the laser cannon within this distance. Finally, conditions will be implemented to evaluate the variation of energy, velocity, angular momentum, orbital elements before and after the maneuver for different positions, and intensity of the applied laser force, then its efficiency in space missions will be measured in space mitigation. (AU)

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