poliastro2.math.thrust.change_argp

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)