Small velocity changes using a SEP spacecraft

Abstract

The Solar Electric Propulsion (SEP) system is designed to deliver large payloads using extended thrusting periods. However, for certain classes of missions, it would be desirable to also use the low thrust propulsion system to impart the small velocity changes typically required to control an orbit in the vicinity of the target body. This paper examines the characteristics and capabilities of using an example SEP system to apply small velocity changes in arbitrary directions. Formulas are developed and examples presented for the rotation and translation which results when the ion thrusters are used to make large turns about all three of the spacecraft axes. This data is then used to propose various techniques for achieving arbitrary velocity changes. While still in a formative stage, the results may be useful in both the design of SEP spacecraft and formulation of future missions.