Libration Point Orbits (LPOs) and Highly Elliptical Orbits (HEOs) are often selected for astrophysics and solar terrestrial missions. No guidelines currently exist for their end-of-life disposal. However, as current and future missions are planned to be placed on these orbits, it is a critical aspect to clear these regions at the end of operations to avoid damage to other spacecraft and ensure on-ground safety. This paper presents an analysis of possible disposal strategies for LPO and HEO missions as a result of a European Space Agency study. The dynamical models and the design approach are presented for each disposal option. Five current missions are selected as test cases Herschel, Gaia, SOHO as LPOs, and INTEGRAL and XMM-Newton as HEOs. A trade-off on the disposal options is made considering technical feasibility, as well as the sustainability context
KeywordsCoupled circular resriied tree-body problem, libra ion poin , weak cap ure, lunar impai, lunar cap ure Abstract is paper examines the design of transfers from the Sun-Earth libration orbits, at the L1 and L2 points, towards the Moon using natural dynamics in order to assess the feasibility of future disposal or lifetime extension operations. With an eye to the probably small quantity of propellant left when its operational life has ended, the spacecraft leaves the libration point orbit on an unstable invariant manifold to bring itself closer to the Earth and Moon. e total trajeory is modeled in the coupled circular restried three-body problem, and some preliminary study of the use of solar radiation pressure is also provided. e concept of survivability and event maps is introduced to obtain suitable conditions that can be targeted such that the spacecraft impas, or is weakly captured by, the Moon. Weak capture at the Moon is studied by method of these maps. Some results for planar Lyapunov orbits at L1 and L2 are given, as well as some results for the operational orbit of SOHO.
is paper examines the design of transfers from the Sun-Earth libration orbits, at the L1 and L2 points, towards the Moon using natural dynamics in order to assess the feasibility of future disposal or lifetime extension operations. With an eye to the probably small quantity of propellant left when its operational life has ended, the spacecraft leaves the libration point orbit on an unstable invariant manifold to bring itself closer to the Earth and Moon. e total trajeory is modeled in the coupled circular restried three-body problem, and some preliminary study of the use of solar radiation pressure is also provided. e concept of survivability and event maps is introduced to obtain suitable conditions that can be targeted such that the spacecraft impas, or is weakly captured by, the Moon. Weak capture at the Moon is studied by method of these maps. Some results for planar Lyapunov orbits at L1 and L2 are given, as well as some results for the operational orbit of SOHO.
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