poliastro.twobody.thrust.change_argp

Argument of perigee change, with formulas developed by Pollard.

References

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

  • Pollard, J. E. “Evaluation of Low-Thrust Orbital Maneuvers”, 1998.

Module Contents

Functions

change_argp(k, a, ecc, argp_0, argp_f, f)

Guidance law from the model.

poliastro.twobody.thrust.change_argp.change_argp(k, a, ecc, argp_0, argp_f, f)

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

Parameters

f (float) – Magnitude of constant acceleration