Computer Science – Performance
Scientific paper
Sep 1992
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992jpnt.confu...6c&link_type=abstract
Presented at the 28th Joint Propulsion Conference and Exhibit, Nashville, TN, 6-8 Jul. 1992; sponsored by AIAA, SAE, ASME, and A
Computer Science
Performance
Ascent Trajectories, Chemical Equilibrium, Combustion, Gas Injection, Mars Atmosphere, Propellants, Rocket Engines, Space Exploration, Argon, Carbon Dioxide, Combustion Chambers, Flight Characteristics, Nitrogen, Pressure Ratio
Scientific paper
A Mars ascent vehicle is limited in performance by the propellant which can be brought from Earth. In some cases the vehicle performance can be improved by injecting inert gas into the engine, if the inert gas is available as an in-situ resource and does not have to be brought from Earth. Carbon dioxide, nitrogen, and argon are constituents of the Martian atmosphere which could be separated by compressing the atmosphere, without any chemical processing step. The effect of inert gas injection on rocket engine performance was analyzed with a numerical combustion code that calculated chemical equilibrium for engines of varying combustion chamber pressure, expansion ratio, oxidizer/fuel ratio, and inert injection fraction. Results of this analysis were applied to several candidate missions to determine how the required mass of return propellant needed in low Earth orbit could be decreased using inert propellant injection.
Colvin James E.
Landis Geoffrey A.
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