TY - GEN
T1 - Escape trajectories for martian moons explorer using chemical and electric propulsion
AU - Horikawa, Makoto
AU - Saiki, Takanao
AU - Kawakatsu, Yasuhiro
AU - Yoshimura, Hiroaki
N1 - Funding Information:
M. H. and H. Y. are partially supported by JSPS Grant-in-Aid for Scientific Research (26400408, 16KT0024), Waseda University (SR 2014B-162, SR 2015B-183), and the MEXT “Top Global University Project” at Waseda University.
Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2016
Y1 - 2016
N2 - This work discusses on designing fast and efficient Mars escape trajectory for Martian Moons eXplorer in the three-body system using chemical and electric propulsion. Chemical propulsion is used for fast low-energy escape from Mars and electric propulsion is used to increase v-infinity and to re-encounter with Mars for a gravity assist. We propose a method called “all-three-body method" and we compare the new method with the patched three-and-two-body method, and a parametric study is carried out. Using electric propulsion soon after Mars escape injection done by chemical propulsion, the all-three-body method would consume less fuel than patched three-and-two-body method. Limiting the use of chemical propulsion could also increase the final spacecraft mass when electric propulsion is used within 10 days after impulsive maneuver.
AB - This work discusses on designing fast and efficient Mars escape trajectory for Martian Moons eXplorer in the three-body system using chemical and electric propulsion. Chemical propulsion is used for fast low-energy escape from Mars and electric propulsion is used to increase v-infinity and to re-encounter with Mars for a gravity assist. We propose a method called “all-three-body method" and we compare the new method with the patched three-and-two-body method, and a parametric study is carried out. Using electric propulsion soon after Mars escape injection done by chemical propulsion, the all-three-body method would consume less fuel than patched three-and-two-body method. Limiting the use of chemical propulsion could also increase the final spacecraft mass when electric propulsion is used within 10 days after impulsive maneuver.
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U2 - 10.2514/6.2016-5209
DO - 10.2514/6.2016-5209
M3 - Conference contribution
AN - SCOPUS:85088409379
SN - 9781624104459
T3 - AIAA/AAS Astrodynamics Specialist Conference, 2016
BT - AIAA/AAS Astrodynamics Specialist Conference, 2016
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA/AAS Astrodynamics Specialist Conference, 2016
Y2 - 13 September 2016 through 16 September 2016
ER -