TY - JOUR

T1 - Design of low energy escape trajectory and delta-V reduction

AU - Tanaka, Yu

AU - Yoshimura, Hiroaki

AU - Kawakatsu, Yasuhiro

N1 - Funding Information:
H.Y. is partially supported by JSPS Grant-in-Aid for Scientific Research (17H01097), JST CREST Grant Number JPMJCR1914, the MEXT “Top Global University Project” and Waseda University (SR 2019C-176, SR 2019Q-020) and the Organization for University Research Initiatives.

PY - 2019

Y1 - 2019

N2 - In this paper, we propose a new method of designing efficient escape trajectories from a gravity field of a planet. In particular, we study to design escape trajectories from the Martian moon Phobos with these processes in the context of the three-dimensional Sun-Mars-Spacecraft Circular Restricted Three-Body Problem (CR3BP). Our method consists of two design steps for realizing low-energy transit trajectories. The first step is to design reference trajectories escaping from a vicinity of Phobos. In this step, we use a halo orbit as a hub, and numerically propagate trajectories which is along both stable and unstable manifolds. Each stable and unstable invariant manifold asymptotically approaches to a halo orbit forward and backward in time respectively. Therefore, it is possible to systematically design transit trajectories passing through the vicinity of the halo orbit with some lower energy using the properties of the invariant manifolds. The second step is to modify such designed trajectories to reduce its thrust (?V) of departing for practical missions. Therefore, we apply a method called differential correction to renew trajectories by iterating analytical approximations. We target to states of a spacecraft whose ?V is to be lower, and the number of thrusting a spacecraft is reduced in order to improve its mission operability. Finally, we illustrate that we can obtain the efficient escaping trajectories from the Mars vicinity.

AB - In this paper, we propose a new method of designing efficient escape trajectories from a gravity field of a planet. In particular, we study to design escape trajectories from the Martian moon Phobos with these processes in the context of the three-dimensional Sun-Mars-Spacecraft Circular Restricted Three-Body Problem (CR3BP). Our method consists of two design steps for realizing low-energy transit trajectories. The first step is to design reference trajectories escaping from a vicinity of Phobos. In this step, we use a halo orbit as a hub, and numerically propagate trajectories which is along both stable and unstable manifolds. Each stable and unstable invariant manifold asymptotically approaches to a halo orbit forward and backward in time respectively. Therefore, it is possible to systematically design transit trajectories passing through the vicinity of the halo orbit with some lower energy using the properties of the invariant manifolds. The second step is to modify such designed trajectories to reduce its thrust (?V) of departing for practical missions. Therefore, we apply a method called differential correction to renew trajectories by iterating analytical approximations. We target to states of a spacecraft whose ?V is to be lower, and the number of thrusting a spacecraft is reduced in order to improve its mission operability. Finally, we illustrate that we can obtain the efficient escaping trajectories from the Mars vicinity.

KW - ?V reduction

KW - CR3BP

KW - Differential correction

KW - Invariant manifold

KW - Low-energy escape trajectory design

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M3 - Conference article

AN - SCOPUS:85079155941

VL - 2019-October

JO - Proceedings of the International Astronautical Congress, IAC

JF - Proceedings of the International Astronautical Congress, IAC

SN - 0074-1795

M1 - IAC-19_E2_1_6_x52655

T2 - 70th International Astronautical Congress, IAC 2019

Y2 - 21 October 2019 through 25 October 2019

ER -