Abstract:This paper researches the fuel-optimal geocentric orbit transfer problem using a low-thrust, electric propulsion. First, the transfer trajectory is divided into N burn-coast arcs via introducing (N−1) intermediate orbits between the initial and the target orbits. By restricting the time duration of each burn, the changes in orbital states caused by one time of ignition can be represented by a discrete velocity impulse; therefore, a considerable large N, a great many optimization variables, and a months and rev… Show more
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