Abstract Electric propulsion has emerged as a cost-effective solution to a wide range of satellite applications. Robust development of the near-Earth infrastructure that will enable Mars exploration can also rely upon solar-electric powered vehicles. Some of these options will be discussed as well. The POWOW concept is a solar-electric propelled spacecraft capable of significant cargo and short trip times for traveling to Mars. When used for Mars missions, it would enter areosynchronous orbit (Mars GEO equivalent) and beam power to surface installations via lasers. The concept has been developed with industrial partner expertise in high efficiency solar cells, advanced concentrator modules, innovative arrays, and high power electric propulsion systems. The previous spacecraft design providing 898 kW using technologies expected to be available in 2003 produced areal power densities approaching 350 W/m2 at 80 °C operating temperatures and wing level specific powers of over 350 W/kg were projected. Because of the high power in this satellite, high voltage operation (up to 1000 V) new work on the effects of hypervelocity impact on test modules operated at these voltages is included here. Electric propulsion options have been refined and focus only on high power Hall thrusters of new as well as conventional designs.