Using space manifold dynamics to deploy a small satellite constellation around the Moon |
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Authors: | Riccardo Marson Mauro Pontani Ettore Perozzi Paolo Teofilatto |
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Institution: | 1.Telespazio S.p.A.,Rome,Italy;2.Università di Roma, “La Sapienza”,Rome,Italy;3.Space Academy Foundation,Rome,Italy |
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Abstract: | The possibility of communicating with the far side of the Moon is essential for keeping a continuous radio link with lunar
orbiting spacecraft, as well as with manned or unmanned surface facilities in locations characterized by poor coverage from
Earth. If the exploration and the exploitation of the Moon must be sustainable in the medium/long term, we need to develop
the capability to realize and service such facilities at an affordable cost. Minimizing the spacecraft mass and the number
of launches is a driving parameter to this end. The aim of this study is to show how Space Manifold Dynamics can be profitably
applied in order to launch three small spacecraft onboard the same launch vehicle and send them to different orbits around
the Moon with no significant difference in the Delta-V budgets. Internal manifold transfers are considered to minimize also
the transfer time. The approach used is the following: we used the linearized solution of the equations of motion in the Circular
Restricted Three Body Problem to determine a first–guess state vector associated with the Weak Stability Boundary regions,
either around the collinear Lagrangian point L1 or around the Moon. The resulting vector is then used as initial state in
a numerical backward-integration sequence that outputs a trajectory on a manifold. The dynamical model used in the numerical
integration is four-body and non-circular, i.e. the perturbations of the Sun and the lunar orbital eccentricity are accounted
for. The trajectory found in this way is used as the principal segment of the lunar transfer. After separation, with minor
maneuvers each satellite is injected into different orbits that lead to ballistic capture around the Moon. Finally, one or
more circularization maneuvers are needed in order to achieve the final circular orbits. The whole mission profile, from launch
to insertion into the final lunar orbits, is modeled numerically with the commercial software STK. |
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