Earth-Mars trajectories for multiple solar-powered spacecraft configurations were generated using Hall and ion propulsion systems utilizing the Direct Trajectory Optimization Method. Payload and power trades versus trip time were examined. Performance was compared for purely interplanetary flight and interplanetary flight with estimated spiral in to Mars orbit. Evaluating current ion and Hall thruster technologies, similar payload masses were delivered by each at equivalent trip times, but with the Hall thruster operating at a power level 10 kilowatts, on average, less than the ion thruster. The power difference for equivalent payload delivered should result in a significant cost savings.
Comparison of Electric Propulsion Systems for Mars Exploration
2003
12 pages
Report
No indication
English
Extraterrestrial Exploration , Electric & Ion Propulsion , Mars exploration , Earth-mars trajectories , Electric propulsion , Solar powered aircraft , Spacecraft configurations , Ion engines , Interplanetary flight , Hall thrusters , Propulsion system performance , Specific impulse , Mars missions , Cost reduction
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