boinor.core.thrust.change_a_inc

Functions

extra_quantities(k, a_0, a_f, inc_0, inc_f, f)	Extra quantities given by the Edelbaum (a, i) model.
beta(t, V_0, f, beta_0_parameter)	Compute yaw angle (β) as a function of time and the problem parameters.
beta_0(V_0, V_f, inc_0, inc_f)	Compute initial yaw angle (β) as a function of the problem parameters.
compute_parameters(k, a_0, a_f, inc_0, inc_f)	Compute parameters of the model.
delta_V(V_0, V_f, beta_0_parameter, inc_0, inc_f)	Compute required increment of velocity.
change_a_inc(k, a_0, a_f, inc_0, inc_f, f)	Change semimajor axis and inclination.

Module Contents

boinor.core.thrust.change_a_inc.extra_quantities(k, a_0, a_f, inc_0, inc_f, f)

Extra quantities given by the Edelbaum (a, i) model.

boinor.core.thrust.change_a_inc.beta(t, V_0, f, beta_0_parameter)

Compute yaw angle (β) as a function of time and the problem parameters.

boinor.core.thrust.change_a_inc.beta_0(V_0, V_f, inc_0, inc_f)

Compute initial yaw angle (β) as a function of the problem parameters.

boinor.core.thrust.change_a_inc.compute_parameters(k, a_0, a_f, inc_0, inc_f)

Compute parameters of the model.

boinor.core.thrust.change_a_inc.delta_V(V_0, V_f, beta_0_parameter, inc_0, inc_f)

Compute required increment of velocity.

boinor.core.thrust.change_a_inc.change_a_inc(k, a_0, a_f, inc_0, inc_f, f)

Change semimajor axis and inclination.

Guidance law from the Edelbaum/Kéchichian theory, optimal transfer between circular inclined orbits (a_0, i_0) –> (a_f, i_f), ecc = 0.

Parameters:

• k (float) – Gravitational parameter.

• a_0 (float) – Initial semimajor axis (km).

• a_f (float) – Final semimajor axis (km).

• inc_0 (float) – Initial inclination (rad).

• inc_f (float) – Final inclination (rad).

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

Returns:

• a_d (function)

• delta_V (numpy.ndarray)

• t_f (float)

Notes

Edelbaum theory [Ede61], reformulated by Kechichian [Kec97].