Abstract
The present study globally searches for low-thrust transfers to the Moon in the planar, circular, restricted, three-body problem. To reduce the dimensionality of parameters for determining initial costates, we narrow down candidates of solutions to those satisfying the necessary conditions for optimality based on the indirect method and use an analogy with the two-body dynamics for the initial periodic orbit around the Earth. We obtain a wide range of Pareto solutions in terms of time of flight and mass consumption. Several solutions exploit resonant lunar gravity assists to reduce fuel consumption.
| Original language | English |
|---|---|
| Title of host publication | Spaceflight Mechanics 2016 |
| Publisher | Univelt Inc. |
| Pages | 415-433 |
| Number of pages | 19 |
| Volume | 158 |
| ISBN (Print) | 9780877036333 |
| Publication status | Published - 2016 |
| Event | 26th AAS/AIAA Space Flight Mechanics Meeting, 2016 - Napa, United States Duration: 2016 Feb 14 → 2016 Feb 18 |
Other
| Other | 26th AAS/AIAA Space Flight Mechanics Meeting, 2016 |
|---|---|
| Country | United States |
| City | Napa |
| Period | 16/2/14 → 16/2/18 |
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ASJC Scopus subject areas
- Aerospace Engineering
- Space and Planetary Science
Cite this
Global search for low-thrust transfers to the moon in the planar circular restricted three-body problem. / Oshima, Kenta; Campagnola, Stefano; Yanao, Tomohiro.
Spaceflight Mechanics 2016. Vol. 158 Univelt Inc., 2016. p. 415-433.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Global search for low-thrust transfers to the moon in the planar circular restricted three-body problem
AU - Oshima, Kenta
AU - Campagnola, Stefano
AU - Yanao, Tomohiro
PY - 2016
Y1 - 2016
N2 - The present study globally searches for low-thrust transfers to the Moon in the planar, circular, restricted, three-body problem. To reduce the dimensionality of parameters for determining initial costates, we narrow down candidates of solutions to those satisfying the necessary conditions for optimality based on the indirect method and use an analogy with the two-body dynamics for the initial periodic orbit around the Earth. We obtain a wide range of Pareto solutions in terms of time of flight and mass consumption. Several solutions exploit resonant lunar gravity assists to reduce fuel consumption.
AB - The present study globally searches for low-thrust transfers to the Moon in the planar, circular, restricted, three-body problem. To reduce the dimensionality of parameters for determining initial costates, we narrow down candidates of solutions to those satisfying the necessary conditions for optimality based on the indirect method and use an analogy with the two-body dynamics for the initial periodic orbit around the Earth. We obtain a wide range of Pareto solutions in terms of time of flight and mass consumption. Several solutions exploit resonant lunar gravity assists to reduce fuel consumption.
UR - http://www.scopus.com/inward/record.url?scp=85007379069&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85007379069&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:85007379069
SN - 9780877036333
VL - 158
SP - 415
EP - 433
BT - Spaceflight Mechanics 2016
PB - Univelt Inc.
ER -