poliastro.core.thrust.change_a_inc
¶
Module Contents¶
Functions¶
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Extra quantities given by the Edelbaum (a, i) model. |
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Compute yaw angle (β) as a function of time and the problem parameters. |
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Compute initial yaw angle (β) as a function of the problem parameters. |
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Compute parameters of the model. |
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Compute required increment of velocity. |
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Change semimajor axis and inclination. |
- poliastro.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.
- poliastro.core.thrust.change_a_inc.beta(t, V_0, f, beta_0)¶
Compute yaw angle (β) as a function of time and the problem parameters.
- poliastro.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.
- poliastro.core.thrust.change_a_inc.compute_parameters(k, a_0, a_f, inc_0, inc_f)¶
Compute parameters of the model.
- poliastro.core.thrust.change_a_inc.delta_V(V_0, V_f, beta_0, inc_0, inc_f)¶
Compute required increment of velocity.
- poliastro.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
- Returns
a_d (function)
delta_V (numpy.ndarray)
t_f (float)
Notes
Edelbaum theory, reformulated by Kéchichian.
References
Edelbaum, T. N. “Propulsion Requirements for Controllable Satellites”, 1961.
Kéchichian, J. A. “Reformulation of Edelbaum’s Low-Thrust Transfer Problem Using Optimal Control Theory”, 1997.