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.
[1]
Sanders Rosenberg.
Concepts in lunar resource utilization
,
1991
.
[2]
J. J. Martin,et al.
Large-Scale Liquid Hydrogen Testing of Variable Density Multilayer Insulation with a Foam Substrate
,
2001
.
[3]
Eric A. Hurlbert,et al.
Lunar lander and return propulsion system trade study
,
1993
.
[4]
Raymond S. Baker,et al.
Advanced Space Storable Propellants for Outer Planet Exploration
,
2004
.
[5]
Thomas J. Mueller,et al.
A summary of the Space Storable Rocket Technology Program
,
1995
.
[6]
Todd Neill,et al.
Durability Demonstration of Small High Performance Rocket Thrusters for RLV Applications
,
1999
.
[7]
Andrew Crocker,et al.
System sensitivity studies of a LOX/methane expander cycle rocket engine
,
1998
.
[8]
R. Zubrin,et al.
Progress in the development of Mars in situ propellant production systems
,
1999
.
[9]
Robert Zubrin,et al.
Progress in Mars ISRU technology
,
2002
.