Quasi optimal eccentricity-only change, with formulas developed by Pollard.
Pollard, J. E. “Simplified Approach for Assessment of Low-Thrust Elliptical Orbit Transfers”, 1997.
Guidance law from the model.
change_ecc_quasioptimal(ss_0, ecc_f, f)¶
Guidance law from the model. Thrust is aligned with an inertially fixed direction perpendicular to the semimajor axis of the orbit.