Nuclear-electric propulsion - Manned Mars propulsion optionsNuclear-electric propulsion can significantly reduce the launch mass for manned Mars missions. By using high-specific-impulse (lsp) electric propulsion systems with advanced nuclear reactors, the total mass-to-orbit for a series of manned Mars flight is reduced. Propulsion technologies required for the manned Mars mission are described. Multi-megawatt Ion and Magneto-Plasma-Dynamic (MPD) propulsion thrusters, Power-Processing Units and nuclear power source are needed. Xenon (Xe)-Ion and MPD thruster performance are detailed. Mission analyses for several Mars mission options are addressed. Both MPD and Ion propulsion were investigated. A four-megawatt propulsion system power level was assumed. Mass comparisons for all-chemical oxygen/hydrogen propulsion missions and combined chemical and nuclear-electric propulsion Mars fleets are included. With fleets of small nuclear-electric vehicles, short trip times to Mars are also enabled.
Document ID
19900029504
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Palaszewski, Bryan (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Brophy, John (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)