Primary electric propulsion for future space missions

Abstract

The paper presents data and a methodology to allow preliminary definition of electric propulsion systems. The elements comprising the thrust system are described parametrically. As an example, thruster performance is presented as a function of specific impulse and propellant type. Two power management and control (PMAC) approaches are considered to illustrate the use of the methodology. Power source characteristics are disregarded in the system description. One PMAC concept assumes a dc power input to the thrust system and all thruster power conditioned in a conventional manner; the other PMAC approach assumes an ac power source.