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¶
|
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
- Returns
a_d, delta_V, t_f
- Return type