poliastro.twobody.thrust.change_inc_ecc

Simultaneous eccentricity and inclination changes.

References

  • Pollard, J. E. “Simplified Analysis of Low-Thrust Orbital Maneuvers”, 2000.

Module Contents

Functions

change_inc_ecc(ss_0, ecc_f, inc_f, f)

Guidance law from the model.

poliastro.twobody.thrust.change_inc_ecc.change_inc_ecc(ss_0, ecc_f, inc_f, f)

Guidance law from the model. Thrust is aligned with an inertially fixed direction perpendicular to the semimajor axis of the orbit.

Parameters
  • ss_0 (Orbit) – Initial orbit, containing all the information.

  • ecc_f (float) – Final eccentricity.

  • inc_f (float) – Final inclination.

  • f (float) – Magnitude of constant acceleration.