Nuclear propulsion system options for Mars missionsThis paper focuses on the use of a nuclear thermal rocket to accomplish a variety of space missions with emphasis on the manned Mars mission. The particle-bed-reactor type nuclear engine was chosen as the baseline engine because of its perceived versatility over other nuclear propulsion systems in conducting a wide variety of tasks. This study indicates that the particle-bed-reactor engine with its high engine thrust-to-weight ratio (about 20) and high specific impulse (about 950 to 1050 sec) offers distinct advantages over the larger and heavier NERVA-type nuclear engines.
Document ID
19920055983
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Emrich, William J., Jr. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Young, Archie C. (NASA Marshall Space Flight Center Huntsville, AL, United States)