Mission analysis for Earth to Mars-Phobos distant Retrograde Orbits. (October 2018)

• Record Type: Journal Article
• Authors: Conte, Davide; Spencer, David B.
• Is Part Of: Acta astronautica. Volume 151(2018)
• Page Start: 761
• Page End: 771
• Publication Date: 2018-10
• Subjects: Phobos -- Mars -- Mars missions -- Distant retrograde orbit -- Earth-mars-phobos trajectories; Astronautics -- Periodicals; Outer space -- Exploration -- Periodicals; Astronautics; Periodicals; 629.405
• DOI: 10.1016/j.actaastro.2018.06.049
• Languages: English
• ISSNs: 0094-5765

Abstract

Abstract: This paper focuses on the trajectory design for missions destined to explore Mars and/or Phobos departing from Low Earth Orbit (LEO) and arriving into a Mars-Phobos Distant Retrograde Orbit (DRO). Lunar DROs are also briefly explored as an alternative departure location. A Mars-Phobos DRO is a relatively stable environment which would make both the surfaces of Mars and Phobos available for a reasonable propellant expenditure. This paper presents the methodology used to compute LEO to Mars-Phobos DRO trajectories and results regarding required C 3 at launch, v ∞ at arrival, Time-of-Flight ( T O F ), and total Δ V for various Mars-Phobos DROs using full ephemeris planetary data. The results show that propellant-optimal trajectories from LEO to a specified Mars-Phobos DRO could be used as a staging location between Mars and Phobos. Assuming that refueling is available at the targeted DRO, LEO to Low Mars Orbits (LMO) trajectories would have higher total Δ V due to the additional stop at the Mars-Phobos DRO. However, the aformentioned trajectories would have lower Initial Mass in LEO (IMLEO) and thus a lower gear ratio thanks to the added "pit stop" located at the given DRO. This results in a lower overall spacecraft dry mass that needs to be launched into space from Earth's surface. Highlights: Mars-Phobos DROs are explored as arrival destinations in cis-martian space. Trajectory design for Earth to Mars-Phobos DROs are presented. The design methodology is detailed in the paper and numerical examples are provided. Lunar DROs are also explored as possible departure locations. Propellant-optimal solutions for lunar DROs to Mars-Phobos DROs transfers are given.