Human exploration and settlement of the Moon using LUNOX-augmented NTR propulsion

Details Human exploration and settlement of the Moon using LUNOX-augmented NTR propulsion Human exploration and settlement of the Moon using LUNOX-augmented NTR propulsion

Oct 1995

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1995stin...9612354b&link_type=abstract

Presented at the 12th Symposium on Space Nuclear Power and Propulsion, Albuquerque, NM, 8-12 Jan. 1995; cosponsored by BMDO, NAS

Computer Science

Performance

Brayton Cycle, Liquid Rocket Propellants, Low Earth Orbits, Lunar Orbits, Moon, Nuclear Rocket Engines, Propulsion, Supersonic Combustion Ramjet Engines, Afterburning, Launch Vehicles, Liquid Hydrogen, Liquid Oxygen, Mass Transfer, Payloads, Thrust-Weight Ratio

Scientific paper

An innovative trimodal nuclear thermal rocket (NTR) concept is described which combines conventional liquid hydrogen (LH2)-cooled NTR, Brayton cycle power generation and supersonic combustion ramjet (scramjet) technologies. Known as the liquid oxygen (LOX) augmented NTR (LANTR), this concept utilizes the large divergent section of the NTR nozzle as an 'afterburner' into which LOX is injected and supersonically combusted with nuclear preheated hydrogen emerging from the LANTR's choked sonic throat--'scramjet propulsion in reverse.' By varying the oxygen-to-hydrogen mixture ratio (MR), the LANTR can operate over a wide range of thrust and specific impulse (Isp) values while the reactor core power level remains relatively constant. As the MR varies from zero to seven, the thrust-to-weight ratio for a 15 thousand pound force (klbf) NTR increases by approximately 440%--from 3 to 13--while the Isp decreases by only approximately 45%--from 940 to 515 seconds. This thrust augmentation feature of the LANTR means that 'big engine' performance can be obtained using smaller more affordable, easier to test NTR engines. 'Reoxidizing' the bipropellant LANTR system in low lunar orbit (LLO) with high density 'lunar-derived' LOX (LUNOX) enables a reusable, reduced size and mass lunar transfer vehicle (LTV) which can be deployed and resupplied using two 66 t-class Shuttle-derived launch vehicles. The reusable LANTR can also transport 200 to 300% more payload on each piloted round trip mission than an expendable 'all LH2' NTR system. As initial outposts grow to eventual lunar settlements and LUNOX production capacity increases, the LANTR concept can also enable a rapid 'commuter' shuttle capable of 36 to 24 hour 'one way' trips to the Moon and back with reasonable size vehicles and initial mass in low Earth orbit (IMLEO) requirements.

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