poliastro.twobody.thrust.change_a_inc

Module Contents

Functions

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

Guidance law from the Edelbaum/Kéchichian theory, optimal transfer between circular inclined orbits

poliastro.twobody.thrust.change_a_inc.change_a_inc(k, a_0, a_f, inc_0, inc_f, f)
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.

  • a_f (float) – Final semimajor axis.

  • inc_0 (float) – Initial inclination.

  • inc_f (float) – Final inclination.

  • f (float) – Magnitude of constant acceleration

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.