Abstract
A Field Emission Electric Propulsion (FEEP) system for nano-satellite propulsion is discussed. The feasibility of the technology is considered, taking into account both the nano-satellite and the FEEP thruster. In order to meet short-term nano-satellite applications, the emphasis is to understand performance capabilities of the total system in a LEO mission. This is achieved by considering the available technology, development and cost of launch for nano-satellite(s) as well as FEEP propulsion system requirements in order to meet those demands. FEEP propellant (Cesium and Rubidium) contamination is identified as one of the major problems with this propulsion system.
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