A comparison of chemical propulsion, nuclear thermal propulsion, and multimegawatt electric propulsion for Mars missionsVarious propulsion systems are considered for a split-mission piloted exploration of Mars in terms of reducing total initial mass in low earth orbit (IMLEO) as well as trip time. Aerobraked nuclear thermal propulsion (NTP), multimegawatt (MMW) nuclear electric propulsion (NEP), and MMW solar electric propulsion (SEP) are discussed and compared to a baseline aerobraked chemical propulsion system. NTP offers low IMLEO, MMW NEP allows both low IMLEO and a short trip time, and both nuclear systems offer better mission characteristics than the chemical system. The MMW SEP is concluded to be less efficient in spite of a lower IMLEO because of the system's higher specific mass and nonconstant power production. It is recommended that MMW NEP and SEP systems be considered for application to Mars cargo missions. The NEP system is concluded to be the most effective propulsion configuration for piloted Mars missions and lunar base missions.
Document ID
19910059577
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Frisbee, Robert H. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Blandino, John J. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Leifer, Stephanie D. (JPL Pasadena, CA, United States)