Ballistic Analysis of a Small Spacecraft Mission for Studying the Earth’s Magnetosphere

In this paper, a preliminary ballistic analysis for an Earth magnetosphere monitoring mission is conducted. Spacecraft mass and propulsion system characteristics are specified to satisfy current technological requirements. Low Earth, Sun-synchronous, and geosynchronous transfer orbits are considered as initial orbits. The target orbits are specified in accordance with scientific tasks. The fuel cost and transfer duration are estimated by two methods: an upper bound from the Lyapunov control method and a lower bound from energy-optimal control problem solution. The relationship between optimal longitudes of the ascending nodes for initial and target orbits is examined. The fuel cost estimates validate the feasibility of the mission based on small spacecraft and on the market low-thrust electric engines.