Alessandro Nitti
Optimal Minimum-Propellant Trajectories for De-Orbiting Satellites into a Northern Lunar Polar Graveyard Region.
Rel. Manuela Battipede, Luigi Mascolo. Politecnico di Torino, Corso di laurea magistrale in Ingegneria Aerospaziale, 2024
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Abstract
Recent developments in the global space exploration have put a spotlight on the Moon, attracting the attention of major space agencies and private companies. NASA's ambitious plans for sustained human presence in cislunar space, e.g. the Lunar Orbital Platform-Gateway program, has raised interest in cislunar orbits, looking for some desirable properties such as relatively low transfer costs from Earth, low orbit maintenance costs, and favourable communications opportunities with both Earth and the lunar south pole. Among libration-point orbits, Halo Orbit families, and particularly Near Rectilinear Halo Orbits, are of special interest due to their appealing characteristics from multiple perspectives. Perfectly periodic in the Circular Restricted Three Body Problem model, NRHOs comprise a subset of the halo orbit families in the Earth-Moon system, characterized by close lunar passages and nearly-stable behaviour, thus requiring low-cost maintenance.
As the cislunar region is anticipated to become increasingly populated with spacecraft, including potential debris, it is important to highlight the necessity of strategic deorbiting planning and compliance with international laws governing space debris
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