Abstract
Using the theory developed by one of the authors in a previous paper, the authors discuss and present solutions for the low thrust orbital transfer in a large number of applications of practical interest: Some emerging topics of Mission Analysis have been addressed, such as the optimization of the deployment of a constellation with orbits at different RAANs, the introduction of constraints in the trajectory like the minimum perigee altitude, and the existence of many extremal solutions for the same problem. The authors have discussed and solved these problems including the J2 and eclipse effects.
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