poliastro2.math.thrust

Description

This internal subpackage implements low-level routines for thrust maneuvers.

Modules

  • change_argp: Internal routines for changing the argument of perigee.

  • change_a_inc: Internal implementations for modifying semi-major axis and inclination.

  • change_ecc_inc: Internal routines for combined eccentricity and inclination adjustments.

  • change_ecc_quasioptimal: Internal quasi-optimal methods for eccentricity change.

poliastro2.math.thrust.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:

  • k (float) – Gravitational parameter (km**3 / s**2)

  • a (float) – Semi-major axis (km)

  • ecc (float) – Eccentricity

  • argp_0 (float) – Initial argument of periapsis (rad)

  • argp_f (float) – Final argument of periapsis (rad)

  • f (float) – Magnitude of constant acceleration (km / s**2)

Returns:

  • a_d (function)

  • delta_V (numpy.ndarray)

  • t_f (float)

Modules

change_a_inc

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

Guidance law from the model.

change_ecc_inc

Simultaneous eccentricity and inclination changes.

change_ecc_quasioptimal