Abstract

Using chemical and nuclear electric propulsion for the exploration of the Martian moons will be investigated. Both oxygen/hydrogen chemical propulsion and nuclear electric propulsion with 500 kilowatt electric (kWe) to 10 megawatt electric (MWe) reactors will be assessed. The initial masses, propellant masses, and trip times for a variety of space vehicle payload masses will be compared. For high energy orbital transfer, the nuclear electric propulsion vehicles required a small fraction of the propellant mass over oxygen/hydrogen orbital transfer vehicles (OTVs). The moons, Phobos and Deimos, may hold resources for refueling future space vehicles. In-situ resource utilization (ISRU) can be a powerful method of reducing Earth dependence on space vehicle propellants, liquid water, and breathing gases. Historical studies have identified the potential of water in carbonaceous chondrites on the moons. The moon-derived propellants OTVs that move payloads between the moons and to other important operational Mars orbits. Also, the propellants have been suggested to support reusable Mars landers. To extract the water, the mined mass, its volume and the mining time were estimated. The water mass fraction may be as low as 2x10−4. Very large masses were needed to be extracted for up to 100 MT of water.

Highlights

  • The Martian moons may be an important part of future Mars local planetary exploration and exploitation [1–11]

  • Vehicle mass scaling equations, and summaries of these analyses are presented; Mass scaling equations were developed for the O2/H2 chemical propulsion and the nuclear electric propulsion systems [14]

  • A range of payload masses were included in the comparative orbital transfer cases: 1, 10 and 50 metric tons (MT)

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Summary

Introduction

The Martian moons may be an important part of future Mars local planetary exploration and exploitation [1–11]. The moons have orbits that are relatively close to Mars, making them potential spacecraft berthing stations. Both oxygen/ hydrogen (O2/H2) chemical propulsion and nuclear electric propulsion (NEP) orbital transfer vehicles were assessed. Their initial mass, propellant mass, and trip times were computed for several orbital transfer missions and orbital locations. The moons may be sites of future in-situ resource utilization (ISRU), where metals and water may be wrested. The mining options for Phobos were assessed, showing the potential availability of water.

Orbital transfer delta-V
Propulsion options
Advanced propulsion options
Chemical propulsion OTV sizing
NEP OTV sizing
Phobos and Deimos payload missions
OTV mass comparisons
Martian moons and ISRU - water mining
Findings
Conclusions

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