Earth-Mars transfers through Moon Distant Retrograde Orbits

Davide Conte, Marilena Di Carlo, Koki Ho, David B. Spencer, Massimiliano Vasile

Research output: Contribution to journalArticle

6 Citations (Scopus)

Abstract

This paper focuses on the trajectory design which is relevant for missions that would exploit the use of asteroid mining in stable cis-lunar orbits to facilitate deep space missions, specifically human Mars exploration. Assuming that a refueling “gas station” is present at a given lunar Distant Retrograde Orbit (DRO), ways of departing from the Earth to Mars via that DRO are analyzed. Thus, the analysis and results presented in this paper add a new cis-lunar departure orbit for Earth-Mars missions. Porkchop plots depicting the required C3 at launch, v at arrival, Time of Flight (TOF), and total ΔV for various DRO departure and Mars arrival dates are created and compared with results obtained for low ΔV Low Earth Orbit (LEO) to Mars trajectories. The results show that propellant-optimal trajectories from LEO to Mars through a DRO have higher overall mission ΔV due to the additional stop at the DRO. However, they have lower Initial Mass in LEO (IMLEO) and thus lower gear ratio as well as lower TOF than direct LEO to Mars transfers. This results in a lower overall spacecraft dry mass that needs to be launched into space from Earth's surface.

Original languageEnglish (US)
Pages (from-to)372-379
Number of pages8
JournalActa Astronautica
Volume143
DOIs
StatePublished - Feb 2018

Fingerprint

Moon
Orbits
Earth (planet)
Trajectories
Asteroids
Propellants
Spacecraft
Gears

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

Conte, Davide ; Di Carlo, Marilena ; Ho, Koki ; Spencer, David B. ; Vasile, Massimiliano. / Earth-Mars transfers through Moon Distant Retrograde Orbits. In: Acta Astronautica. 2018 ; Vol. 143. pp. 372-379.
@article{1b294fb1522c40448205e9b87383ec47,
title = "Earth-Mars transfers through Moon Distant Retrograde Orbits",
abstract = "This paper focuses on the trajectory design which is relevant for missions that would exploit the use of asteroid mining in stable cis-lunar orbits to facilitate deep space missions, specifically human Mars exploration. Assuming that a refueling “gas station” is present at a given lunar Distant Retrograde Orbit (DRO), ways of departing from the Earth to Mars via that DRO are analyzed. Thus, the analysis and results presented in this paper add a new cis-lunar departure orbit for Earth-Mars missions. Porkchop plots depicting the required C3 at launch, v∞ at arrival, Time of Flight (TOF), and total ΔV for various DRO departure and Mars arrival dates are created and compared with results obtained for low ΔV Low Earth Orbit (LEO) to Mars trajectories. The results show that propellant-optimal trajectories from LEO to Mars through a DRO have higher overall mission ΔV due to the additional stop at the DRO. However, they have lower Initial Mass in LEO (IMLEO) and thus lower gear ratio as well as lower TOF than direct LEO to Mars transfers. This results in a lower overall spacecraft dry mass that needs to be launched into space from Earth's surface.",
author = "Davide Conte and {Di Carlo}, Marilena and Koki Ho and Spencer, {David B.} and Massimiliano Vasile",
year = "2018",
month = "2",
doi = "10.1016/j.actaastro.2017.12.007",
language = "English (US)",
volume = "143",
pages = "372--379",
journal = "Acta Astronautica",
issn = "0094-5765",
publisher = "Elsevier Limited",

}

Earth-Mars transfers through Moon Distant Retrograde Orbits. / Conte, Davide; Di Carlo, Marilena; Ho, Koki; Spencer, David B.; Vasile, Massimiliano.

In: Acta Astronautica, Vol. 143, 02.2018, p. 372-379.

Research output: Contribution to journalArticle

TY - JOUR

T1 - Earth-Mars transfers through Moon Distant Retrograde Orbits

AU - Conte, Davide

AU - Di Carlo, Marilena

AU - Ho, Koki

AU - Spencer, David B.

AU - Vasile, Massimiliano

PY - 2018/2

Y1 - 2018/2

N2 - This paper focuses on the trajectory design which is relevant for missions that would exploit the use of asteroid mining in stable cis-lunar orbits to facilitate deep space missions, specifically human Mars exploration. Assuming that a refueling “gas station” is present at a given lunar Distant Retrograde Orbit (DRO), ways of departing from the Earth to Mars via that DRO are analyzed. Thus, the analysis and results presented in this paper add a new cis-lunar departure orbit for Earth-Mars missions. Porkchop plots depicting the required C3 at launch, v∞ at arrival, Time of Flight (TOF), and total ΔV for various DRO departure and Mars arrival dates are created and compared with results obtained for low ΔV Low Earth Orbit (LEO) to Mars trajectories. The results show that propellant-optimal trajectories from LEO to Mars through a DRO have higher overall mission ΔV due to the additional stop at the DRO. However, they have lower Initial Mass in LEO (IMLEO) and thus lower gear ratio as well as lower TOF than direct LEO to Mars transfers. This results in a lower overall spacecraft dry mass that needs to be launched into space from Earth's surface.

AB - This paper focuses on the trajectory design which is relevant for missions that would exploit the use of asteroid mining in stable cis-lunar orbits to facilitate deep space missions, specifically human Mars exploration. Assuming that a refueling “gas station” is present at a given lunar Distant Retrograde Orbit (DRO), ways of departing from the Earth to Mars via that DRO are analyzed. Thus, the analysis and results presented in this paper add a new cis-lunar departure orbit for Earth-Mars missions. Porkchop plots depicting the required C3 at launch, v∞ at arrival, Time of Flight (TOF), and total ΔV for various DRO departure and Mars arrival dates are created and compared with results obtained for low ΔV Low Earth Orbit (LEO) to Mars trajectories. The results show that propellant-optimal trajectories from LEO to Mars through a DRO have higher overall mission ΔV due to the additional stop at the DRO. However, they have lower Initial Mass in LEO (IMLEO) and thus lower gear ratio as well as lower TOF than direct LEO to Mars transfers. This results in a lower overall spacecraft dry mass that needs to be launched into space from Earth's surface.

UR - http://www.scopus.com/inward/record.url?scp=85037523620&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85037523620&partnerID=8YFLogxK

U2 - 10.1016/j.actaastro.2017.12.007

DO - 10.1016/j.actaastro.2017.12.007

M3 - Article

AN - SCOPUS:85037523620

VL - 143

SP - 372

EP - 379

JO - Acta Astronautica

JF - Acta Astronautica

SN - 0094-5765

ER -