Speaker
Ms
Kaori Onozaki
(Waseda university)
Description
We develop a low energy trajectory from the Earth to the Moon by extensively using the framework of tube dynamics. We assume that a spacecraft is under the influence of gravity of the Sun, the Earth as well as the Moon and also that the spacecraft and the planets move in the same plane. In this situation, we model the Sun-Earth-Moon-Spacecraft (S/C) 4 body system as a coupled PRC3B system with perturbations, where the Sun-Earth-S/C 3 body system with the Moon perturbation and the Earth-Moon-S/C 3 body system with the Sun perturbation may be coupled at an appropriate patch point. First, we consider various boundary conditions such that the spacecraft departs from the low Earth orbit (LEO) and arrives at the low lunar orbit (LLO). Then we want to find a low energy trajectory connected at a patch point, so that the trajectories from the LEO to the patch point and from the patch point to the LLO can be connected with less maneuver. To do this, we compute the Finite Time Lyapunov Exponent to detect stable and unstable invariant manifolds called “tubes” at a section and we construct the family of departure orbits in the Sun-Earth-spacecraft system with the Moon perturbation, which may be outside of the unstable manifolds associated with the Lyapunov orbit around L2. The family of arrival orbits is also obtained to be inside of the stable manifolds in the Earth-Moon-spacecraft system with the Sun perturbation. With a trajectory correction maneuver, then we obtain a low energy trajectory at the patch point. Finally, we will show that the proposed trajectory may be more efficient in the sense that the total maneuver is to be less than other trajectories such as the Hohmann trajectory.
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Primary author
Ms
Kaori Onozaki
(Waseda university)
Co-authors
Prof.
Hiroaki Yoshimura
(Waseda university)
Dr
Shane Ross
(Virginia Tech)
