poliastro.core.thrust.change_argp

Module Contents

Functions

delta_V(V, ecc, argp_0, argp_f, f, A)	Compute required increment of velocity.
extra_quantities(k, a, ecc, argp_0, argp_f, f, A=0.0)	Extra quantities given by the model.
change_argp(k, a, ecc, argp_0, argp_f, f)	Guidance law from the model.

poliastro.core.thrust.change_argp.delta_V(V, ecc, argp_0, argp_f, f, A)

Compute required increment of velocity.

poliastro.core.thrust.change_argp.extra_quantities(k, a, ecc, argp_0, argp_f, f, A=0.0)

Extra quantities given by the model.

poliastro.core.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

• 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)