Low-thrust trajectory design for a low-cost multiple asteroid rendezvous and sample return mission

H. Yamakawa, Y. Kawakatsu, Mutsuko Morimoto, M. Abe, H. Yano

Research output: Contribution to conferencePaper

2 Citations (Scopus)

Abstract

Sample return missions to multiple near-Earth asteroids are investigated assuming solar electric propulsion as propulsive means. The aim of the mission is to collect the soil samples from multiple asteroids and to return them to the Earth. The objective of the trajectory design is not only to maximize the number of the target asteroids and the payload mass of the spacecraft, but also to make the flight time up to the Earth return as short as possible for quick science return. Two options are studied for the orbital sequence. The first scenario introduces Earth gravity-assist after each asteroid rendezvous in order to return the reentry capsule as fast as possible as well as to reflect the result of the sample analysis for the following mission scenario. The other trajectory option is designed without Earth gravity assists.

Original languageEnglish
Pages6597-6604
Number of pages8
Publication statusPublished - 2004 Dec 1
Externally publishedYes
EventInternational Astronautical Federation - 55th International Astronautical Congress 2004 - Vancouver, Canada
Duration: 2004 Oct 42004 Oct 8

Conference

ConferenceInternational Astronautical Federation - 55th International Astronautical Congress 2004
CountryCanada
CityVancouver
Period04/10/404/10/8

Fingerprint

sample return missions
low thrust
rendezvous
Asteroids
asteroids
asteroid
thrust
Earth (planet)
trajectory
Trajectories
trajectories
cost
Costs
Gravitation
solar electric propulsion
gravity
gravitation
flight time
Electric propulsion
reentry

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

Yamakawa, H., Kawakatsu, Y., Morimoto, M., Abe, M., & Yano, H. (2004). Low-thrust trajectory design for a low-cost multiple asteroid rendezvous and sample return mission. 6597-6604. Paper presented at International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, Canada.

Low-thrust trajectory design for a low-cost multiple asteroid rendezvous and sample return mission. / Yamakawa, H.; Kawakatsu, Y.; Morimoto, Mutsuko; Abe, M.; Yano, H.

2004. 6597-6604 Paper presented at International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, Canada.

Research output: Contribution to conferencePaper

Yamakawa, H, Kawakatsu, Y, Morimoto, M, Abe, M & Yano, H 2004, 'Low-thrust trajectory design for a low-cost multiple asteroid rendezvous and sample return mission', Paper presented at International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, Canada, 04/10/4 - 04/10/8 pp. 6597-6604.
Yamakawa H, Kawakatsu Y, Morimoto M, Abe M, Yano H. Low-thrust trajectory design for a low-cost multiple asteroid rendezvous and sample return mission. 2004. Paper presented at International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, Canada.
Yamakawa, H. ; Kawakatsu, Y. ; Morimoto, Mutsuko ; Abe, M. ; Yano, H. / Low-thrust trajectory design for a low-cost multiple asteroid rendezvous and sample return mission. Paper presented at International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, Canada.8 p.
@conference{64f8386e5c484b628655311117f8a1c5,
title = "Low-thrust trajectory design for a low-cost multiple asteroid rendezvous and sample return mission",
abstract = "Sample return missions to multiple near-Earth asteroids are investigated assuming solar electric propulsion as propulsive means. The aim of the mission is to collect the soil samples from multiple asteroids and to return them to the Earth. The objective of the trajectory design is not only to maximize the number of the target asteroids and the payload mass of the spacecraft, but also to make the flight time up to the Earth return as short as possible for quick science return. Two options are studied for the orbital sequence. The first scenario introduces Earth gravity-assist after each asteroid rendezvous in order to return the reentry capsule as fast as possible as well as to reflect the result of the sample analysis for the following mission scenario. The other trajectory option is designed without Earth gravity assists.",
author = "H. Yamakawa and Y. Kawakatsu and Mutsuko Morimoto and M. Abe and H. Yano",
year = "2004",
month = "12",
day = "1",
language = "English",
pages = "6597--6604",
note = "International Astronautical Federation - 55th International Astronautical Congress 2004 ; Conference date: 04-10-2004 Through 08-10-2004",

}

TY - CONF

T1 - Low-thrust trajectory design for a low-cost multiple asteroid rendezvous and sample return mission

AU - Yamakawa, H.

AU - Kawakatsu, Y.

AU - Morimoto, Mutsuko

AU - Abe, M.

AU - Yano, H.

PY - 2004/12/1

Y1 - 2004/12/1

N2 - Sample return missions to multiple near-Earth asteroids are investigated assuming solar electric propulsion as propulsive means. The aim of the mission is to collect the soil samples from multiple asteroids and to return them to the Earth. The objective of the trajectory design is not only to maximize the number of the target asteroids and the payload mass of the spacecraft, but also to make the flight time up to the Earth return as short as possible for quick science return. Two options are studied for the orbital sequence. The first scenario introduces Earth gravity-assist after each asteroid rendezvous in order to return the reentry capsule as fast as possible as well as to reflect the result of the sample analysis for the following mission scenario. The other trajectory option is designed without Earth gravity assists.

AB - Sample return missions to multiple near-Earth asteroids are investigated assuming solar electric propulsion as propulsive means. The aim of the mission is to collect the soil samples from multiple asteroids and to return them to the Earth. The objective of the trajectory design is not only to maximize the number of the target asteroids and the payload mass of the spacecraft, but also to make the flight time up to the Earth return as short as possible for quick science return. Two options are studied for the orbital sequence. The first scenario introduces Earth gravity-assist after each asteroid rendezvous in order to return the reentry capsule as fast as possible as well as to reflect the result of the sample analysis for the following mission scenario. The other trajectory option is designed without Earth gravity assists.

UR - http://www.scopus.com/inward/record.url?scp=34249081107&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=34249081107&partnerID=8YFLogxK

M3 - Paper

AN - SCOPUS:34249081107

SP - 6597

EP - 6604

ER -