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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

Journal Article · · AIP Conference Proceedings
DOI:https://doi.org/10.1063/1.50046· OSTI ID:385461
 [1]
  1. NASA Lewis Research Center, 21000 Brookpark Road, Cleveland, Ohio 44135 (United States)

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.}

OSTI ID:
385461
Report Number(s):
CONF-960109-; ISSN 0094-243X; TRN: 9618M0067
Journal Information:
AIP Conference Proceedings, Vol. 361, 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