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Advanced electrostatic ion thruster for space propulsion

T. D. Masek, Duncan MacPherson, W. Gelon, S. Kami, R. L. Poeschel, J. W. Ward

Abstract

The suitability of the baseline 30 cm thruster for future space missions was examined. Preliminary design concepts for several advanced thrusters were developed to assess the potential practical difficulties of a new design. Useful methodologies were produced for assessing both planetary and earth orbit missions. Payload performance as a function of propulsion system technology level and cost sensitivity to propulsion system technology level are among the topics assessed. A 50 cm diameter thruster designed to operate with a beam voltage of about 2400 V is suggested to satisfy most of the requirements of future space missions.

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Key concepts: Ion thruster, In-space propulsion technologies, Propulsion, Payload (computing), Aerospace engineering, Electrically powered spacecraft propulsion, Spacecraft propulsion, Spacecraft