Systems analysis of Mars solar electric propulsion vehiclesMission performance, mass, initial power, and cost are determined for solar electric propulsion vehicles across a range of payload masses, reference powers, and mission trajectories. Thick radiation shielding is added to arrays using indium phosphide or III-V multijunction solar cells to reduce the damage incurred through the radiation belts. Special assessments of power management and distribution systems, atmospheric drag, and energy storage are made. It is determined that atmospheric drag is of no great concern and that the energy storage used in countering drag is unnecessary. A scheme to package the arrays, masts, and ion thrusters into a single fairing is presented.
Document ID
19910025553
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hickman, J. M. (NASA Lewis Research Center Cleveland, OH, United States)
Curtis, H. B. (NASA Lewis Research Center Cleveland, OH, United States)
Kenny, B. H. (NASA Lewis Research Center Cleveland, OH, United States)
Sefcik, R. J. (NASA Lewis Research Center Cleveland, OH, United States)