Comparison of Propulsion Options for a Lunar Lander Ascent Stage
Abstract
The propulsion system for the ascent stage of a lunar lander will be required to meet some unusual requirements, including extreme thermal environments and difficult safety objectives. This paper presents the results of an initial study of candidate propulsion options for the ascent stage. The study considered pump-fed and pressure-fed engines using eight propellant types: LOX/hydrogen, LOX/methane, LOX/ethanol, LOX/kerosene, LOX/monomethyl hydrazine (MMH), LOX/silane, nitrogen tetroxide/MMH, and chlorine pentafluoride/hydrazine. The delta-V and thrust to weight requirements for the stage were determined via trajectory simulation. Thermal analysis determined that passive storage of liquid hydrogen and oxygen is feasible for mission durations of a few months. A trade study comparison concluded that pump-fed engines were preferred over pressure-fed engines, and that LOX/LH 2, LOX/ethanol, and N2O4/MMH were the most promising propellant options. Silane and chlorine pentafluoride were found to be impractical, with few desirable systemlevel characteristics and do not merit further consideration.
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It is still possible to produce methane on the Moon due to solar wind depositing carbon and other volatiles.
“However, is it noted that it is still possible to produce methane on the Moon due to solar wind depositing carbon and other volatiles [56].”
Of the three fuels, LH2 has the costliest storage requirements, needing to be kept around 23 K; methane needs around 100 K; ethanol can be stored from 150 K to 350 K.
“Of the 3 fuels mentioned, LH2 has the costliest storage requirements, needing to be kept around 23 K, whereas methane needs to be kept around 100 K (still below the lowest lunar night temperatures), and ethanol can be stored from 150 K to 350 K [56].”
LOX/LH2 boasts the highest Isp out of the three, with LOX/methane second and LOX/ethanol trailing, but use of LOX/LH2 in any lander or ascent vehicle increases complexity dramatically due to complex handling requirements.
“Further, LOX/LH2 boasts the highest Isp out of the three, with LOX/methane coming in second and LOX/ethanol trailing, but it is noted that the use of LOX/LH2 in any kind of lander or ascent vehicle increases the complexity dramatically due to complex handling requirements [56].”
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Keller, R. J., Porter, W., Goli, K., Rosenthal, R., Butler, N., & Jones, J. A. (2021) · Life · doi:10.3390/life11080844 · Cited by 23 · see citing works
“However, is it noted that it is still possible to produce methane on the Moon due to solar wind depositing carbon and other volatiles [56].”
Background
- Authors
- Hopkins, J.
- Affiliations
- Lockheed Martin (United States) (US)
- Corresponding author
- Hopkins, Joshua
- Venue
- Space 2005
- Published
- 2005-06-18
- OpenAlex
- W2162451005
- Cited by
- 4
- References
- 13
- Citations by year
- 2021: 1
- FWCI
- 2.06
- Type
- conference paper
- Language
- en
- Open access
- closed
- Topics
- Physical Sciences › Engineering › Aerospace Engineering › Rocket and propulsion systems research
- Physical Sciences › Engineering › Aerospace Engineering › Spacecraft and Cryogenic Technologies
- Physical Sciences › Engineering › Aerospace Engineering › Spacecraft Design and Technology
- Keywords
- propulsion system selection, cryogenic propellants, monomethylhydrazine, silane, liquid hydrogen storage, thermal analysis, delta-v requirements, thrust-to-weight ratio, trade studies
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