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Title: Options for human {open_quote}{open_quote}return to the moon{close_quote}{close_quote} using tomorrow{close_quote}s SSTO, ISRU, and LOX-augmented NTR technologies

Abstract

The feasibility of conducting human missions to the Moon is examined assuming the use of three {open_quote}{open_quote}high leverage{close_quote}{close_quote} technologies: (1) a single-stage-to-orbit (SSTO) launch vehicle, (2) {open_quote}{open_quote}{ital in}-{ital situ}{close_quote}{close_quote} {ital resource} {ital utilization} (ISRU){emdash}specifically {open_quote}{open_quote}lunar-derived{close_quote}{close_quote} liquid oxygen (LUNOX), and (3) LOX-augmented nuclear thermal rocket (LANTR) propulsion. Lunar transportation system elements consisting of a LANTR-powered lunar transfer vehicle (LTV) and a chemical propulsion lunar landing/Earth return vehicle (LERV) are configured to fit within the {open_quote}{open_quote}compact{close_quote}{close_quote} dimensions of the SSTO cargo bay (diameter: 4.6 m/length: 9.0 m) while satisfying an initial mass in low Earth orbit (IMLEO) limit of {approximately}60 t (3 SSTO launches). Using {approximately}8 t of LUNOX to {open_quote}{open_quote}reoxidize{close_quote}{close_quote} the LERV for a {open_quote}{open_quote}direct return{close_quote}{close_quote} flight to Earth reduces its size and mass allowing delivery to LEO on a single 20 t SSTO launch. Similarly, the LANTR engine{close_quote}s ability to operate at any oxygen/hydrogen mixture ratio from 0 to 7 with high specific impulse ({approximately}940 to 515 s) is exploited to reduce hydrogen tank volume, thereby improving packaging of the LANTR LTV{close_quote}s {open_quote}{open_quote}propulsion{close_quote}{close_quote} and {open_quote}{open_quote}propellant modules{close_quote}{close_quote}. Expendable and reusable, piloted and cargo missions and vehicle designs are presented along with estimates of LUNOX production required to support the different missionmore » modes. {copyright} {ital 1996 American Institute of Physics.}« less

Authors:
 [1]
  1. NASA Lewis Research Center, 21000 Brookpark Road, Cleveland, Ohio 44135 (United States)
Publication Date:
OSTI Identifier:
385461
Report Number(s):
CONF-960109-
Journal ID: APCPCS; ISSN 0094-243X; TRN: 9618M0067
Resource Type:
Journal Article
Journal Name:
AIP Conference Proceedings
Additional Journal Information:
Journal Volume: 361; Journal Issue: 1; Conference: STAIF 96: space technology and applications international forum, Albuquerque, NM (United States), 7-11 Jan 1996; Other Information: PBD: Mar 1996
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING NOT INCLUDED IN OTHER CATEGORIES; MOON; SPACE TRANSPORT; SPACE VEHICLES; LAUNCHING; PROPELLANTS; PROPULSION SYSTEMS; OXYGEN; HYDROGEN

Citation Formats

Borowski, S K. Options for human {open_quote}{open_quote}return to the moon{close_quote}{close_quote} using tomorrow{close_quote}s SSTO, ISRU, and LOX-augmented NTR technologies. United States: N. p., 1996. Web. doi:10.1063/1.50046.
Borowski, S K. Options for human {open_quote}{open_quote}return to the moon{close_quote}{close_quote} using tomorrow{close_quote}s SSTO, ISRU, and LOX-augmented NTR technologies. United States. https://doi.org/10.1063/1.50046
Borowski, S K. 1996. "Options for human {open_quote}{open_quote}return to the moon{close_quote}{close_quote} using tomorrow{close_quote}s SSTO, ISRU, and LOX-augmented NTR technologies". United States. https://doi.org/10.1063/1.50046.
@article{osti_385461,
title = {Options for human {open_quote}{open_quote}return to the moon{close_quote}{close_quote} using tomorrow{close_quote}s SSTO, ISRU, and LOX-augmented NTR technologies},
author = {Borowski, S K},
abstractNote = {The feasibility of conducting human missions to the Moon is examined assuming the use of three {open_quote}{open_quote}high leverage{close_quote}{close_quote} technologies: (1) a single-stage-to-orbit (SSTO) launch vehicle, (2) {open_quote}{open_quote}{ital in}-{ital situ}{close_quote}{close_quote} {ital resource} {ital utilization} (ISRU){emdash}specifically {open_quote}{open_quote}lunar-derived{close_quote}{close_quote} liquid oxygen (LUNOX), and (3) LOX-augmented nuclear thermal rocket (LANTR) propulsion. Lunar transportation system elements consisting of a LANTR-powered lunar transfer vehicle (LTV) and a chemical propulsion lunar landing/Earth return vehicle (LERV) are configured to fit within the {open_quote}{open_quote}compact{close_quote}{close_quote} dimensions of the SSTO cargo bay (diameter: 4.6 m/length: 9.0 m) while satisfying an initial mass in low Earth orbit (IMLEO) limit of {approximately}60 t (3 SSTO launches). Using {approximately}8 t of LUNOX to {open_quote}{open_quote}reoxidize{close_quote}{close_quote} the LERV for a {open_quote}{open_quote}direct return{close_quote}{close_quote} flight to Earth reduces its size and mass allowing delivery to LEO on a single 20 t SSTO launch. Similarly, the LANTR engine{close_quote}s ability to operate at any oxygen/hydrogen mixture ratio from 0 to 7 with high specific impulse ({approximately}940 to 515 s) is exploited to reduce hydrogen tank volume, thereby improving packaging of the LANTR LTV{close_quote}s {open_quote}{open_quote}propulsion{close_quote}{close_quote} and {open_quote}{open_quote}propellant modules{close_quote}{close_quote}. Expendable and reusable, piloted and cargo missions and vehicle designs are presented along with estimates of LUNOX production required to support the different mission modes. {copyright} {ital 1996 American Institute of Physics.}},
doi = {10.1063/1.50046},
url = {https://www.osti.gov/biblio/385461}, journal = {AIP Conference Proceedings},
number = 1,
volume = 361,
place = {United States},
year = {Fri Mar 01 00:00:00 EST 1996},
month = {Fri Mar 01 00:00:00 EST 1996}
}