TY - GEN
T1 - Escape trajectory for the martian moon sample return mission using tube dynamics
AU - Takemura, Kazutoshi
AU - Kawakatsu, Yasuhiro
AU - Yoshimura, Hiroaki
N1 - Funding Information:
This study was partially supported by the Japan Society for the Promotion of Science Grant-in-Aid for Scientific Research (16KT0024), Waseda University (SR 2017K-167), and the MEXT “Top Global University Project" at Waseda University.
Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - We study trajectory design for a spacecraft escaping from Mars in the context of spatial restricted three-body problem (SR3BP) by using tube dynamics. First, we compute the halo and quasi-halo orbits around L1of Sun-Mars system together with the associated invariant manifolds. Then we investigate whether the spacecraft with a certain energy is inside of the tube to connect the manifold with the Phobos orbit. We also perform grid search with the SR3BP with the same energy as the invariant manifold. Comparing numerical results between grid search and the tube dynamics, we show how to determine the propriety for the escape trajectory by using the tube dynamics. Consequently we clarify the way to judge whether the spacecrafts can escape or not in the spatial problem.
AB - We study trajectory design for a spacecraft escaping from Mars in the context of spatial restricted three-body problem (SR3BP) by using tube dynamics. First, we compute the halo and quasi-halo orbits around L1of Sun-Mars system together with the associated invariant manifolds. Then we investigate whether the spacecraft with a certain energy is inside of the tube to connect the manifold with the Phobos orbit. We also perform grid search with the SR3BP with the same energy as the invariant manifold. Comparing numerical results between grid search and the tube dynamics, we show how to determine the propriety for the escape trajectory by using the tube dynamics. Consequently we clarify the way to judge whether the spacecrafts can escape or not in the spatial problem.
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U2 - 10.2514/6.2018-1688
DO - 10.2514/6.2018-1688
M3 - Conference contribution
AN - SCOPUS:85141570551
SN - 9781624105333
T3 - Space Flight Mechanics Meeting, 2018
BT - Space Flight Mechanics Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - Space Flight Mechanics Meeting, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -