``Bimodal'' NTR and LANTR propulsion for human missions to Mars/Phobos

Details ``Bimodal'' NTR and LANTR propulsion for human missions to Mars/Phobos ``Bimodal'' NTR and LANTR propulsion for human missions to Mars/Phobos

Jan 1999

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1999aipc..458.1261b&link_type=abstract

Space technology and applications international forum -1999. AIP Conference Proceedings, Volume 458, pp. 1261-1268 (1999).

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Spaceborne And Space Research Instruments, Apparatus, And Components, Propulsion Reactors

Scientific paper

The nuclear thermal rocket (NTR) is one of the leading propulsion options for future human missions to Mars due to its high specific impulse (Isp ~850-1000 s) and attractive engine thrust-to-weight ratio (~3-10). Because only a miniscule amount of enriched uranium-235 fuel is consumed in a NTR during the primary propulsion maneuvers of a typical Mars mission, engines configured for both propulsive thrust and modest power generation (referred to as ``bimodal'' operation) provide the basis for a robust, ``power-rich'' stage enabling propulsive Mars capture and reuse capability. A family of modular ``bimodal'' NTR (BNTR) vehicles are described which utilize a common ``core'' stage powered by three 66.7 kN (~15 klbf) BNTRs that produce 50 kWe of total electrical power for crew life support, an active refrigeration/reliquification system for long term, ``zero-boiloff'' liquid hydrogen (LH2) storage, and high data rate communications. Compared to other propulsion options, a Mars mission architecture using BNTR transfer vehicles requires fewer transportation system elements which reduces mission mass, cost and risk because of simplified space operations. For difficult Mars options, such as a Phobos rendezvous and sample return mission, volume (not mass) constraints limit the performance of the ``all LH2'' BNTR stage. The use of ``LOX-augmented'' NTR (LANTR) engines, operating at a modest oxygen-to-hydrogen (O/H) mixture ratio (MR) of 0.5, helps to increase ``bulk'' propellant density and total thrust during the trans-Mars injection (TMI) burn. On all subsequent burns, the bimodal LANTR engines operate on LH2 only (MR=0) to maximize vehicle performance while staying within the mass limits of two ~80 t ``Magnum'' heavy lift launch vehicles (HLLVs).

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