Abstract
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.
| Original language | English |
|---|---|
| Title of host publication | Space Flight Mechanics Meeting |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| Edition | 210009 |
| ISBN (Print) | 9781624105333 |
| DOIs | |
| Publication status | Published - 2018 Jan 1 |
| Event | Space Flight Mechanics Meeting, 2018 - Kissimmee, United States Duration: 2018 Jan 8 → 2018 Jan 12 |
Other
| Other | Space Flight Mechanics Meeting, 2018 |
|---|---|
| Country | United States |
| City | Kissimmee |
| Period | 18/1/8 → 18/1/12 |
Fingerprint
ASJC Scopus subject areas
- Aerospace Engineering
Cite this
Escape trajectory for the martian moon sample return mission using tube dynamics. / Takemura, Kazutoshi; Kawakatsu, Yasuhiro; Yoshimura, Hiroaki.
Space Flight Mechanics Meeting. 210009. ed. American Institute of Aeronautics and Astronautics Inc, AIAA, 2018.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Escape trajectory for the martian moon sample return mission using tube dynamics
AU - Takemura, Kazutoshi
AU - Kawakatsu, Yasuhiro
AU - Yoshimura, Hiroaki
PY - 2018/1/1
Y1 - 2018/1/1
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.
UR - http://www.scopus.com/inward/record.url?scp=85044375845&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85044375845&partnerID=8YFLogxK
U2 - 10.2514/6.2018-1688
DO - 10.2514/6.2018-1688
M3 - Conference contribution
AN - SCOPUS:85044375845
SN - 9781624105333
BT - Space Flight Mechanics Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
ER -