poliastro.twobody.thrust.change_ecc_quasioptimal

Quasi optimal eccentricity-only change, with formulas developed by Pollard.

References

  • Pollard, J. E. “Simplified Approach for Assessment of Low-Thrust Elliptical Orbit Transfers”, 1997.

Module Contents

Functions

change_ecc_quasioptimal(orb_0, ecc_f, f)

Guidance law from the model.
poliastro.twobody.thrust.change_ecc_quasioptimal.change_ecc_quasioptimal(orb_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.

Parameters

  • orb_0 (Orbit) – Initial orbit, containing all the information.

  • ecc_f (float) – Final eccentricity.

  • f (float) – Magnitude of constant acceleration