학술논문
Propellant production from the Martian atmosphere
Document Type
Report
Author
Source
Journal of Propulsion and Power. 8(4, Ju)
Subject
Language
English
ISSN
0748-4658
Abstract
Results are presented from a calculation of the specific impulses that can be generated through the combustion of cryogenic CO and O2 over a range of fuel/oxidizer ratios, chamber pressures, nozzle expansion ratios, freestream pressures representative of Mars, and the limiting conditions of equilibrium and frozen nozzle flow. For an expansion ratio of 80 and 100-atm. chamber pressure, a specific impulse of 298 sec was obtained; this is comparable to the best solid rocket propellants.