poliastro.twobody.thrust.change_a_inc

Module Contents

Functions

change_a_inc(k, a_0, a_f, inc_0, inc_f, f)

Change semimajor axis and inclination.
poliastro.twobody.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 (Quantity) – Gravitational parameter.

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

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

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

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

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

Returns

a_d, delta_V, t_f

Return type

tuple (function, Quantity, Time)

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.