Parametric analysis of an ion propulsion system for performing large inclination changes in low Earth circular orbits

An analytical model has been constructed for an ion propulsion system which performs large changes in the inclination of a satellite in low-earth orbit. A thrusting strategy and the top-level propulsion system design are also presented. The analytical model enables the derivation of requirements for Delta V, propellant, and power. A parametric trade study is presented which explores the relationship of duty cycle and specific impulse to power and propellant requirements. The primary result of this study is a determination of which propulsion system parameters have the greatest effect on overall system performance. It is found that the power processing unit design is the main driver in determining available satellite payload.<>