poliastro.twobody.thrust.change_ecc_inc

Module Contents

Functions

change_ecc_inc(ss_0, ecc_f, inc_f, f)

Simultaneous eccentricity and inclination changes. Guidance law from the model. Thrust is aligned with an inertially fixed direction perpendicular to the semimajor axis of the orbit.
poliastro.twobody.thrust.change_ecc_inc.change_ecc_inc(ss_0, ecc_f, inc_f, f)

Simultaneous eccentricity and inclination changes. Guidance law from the model. Thrust is aligned with an inertially fixed direction perpendicular to the semimajor axis of the orbit.

Parameters

  • ss_0 (Orbit) – Initial orbit, containing all the information.

  • ecc_f (float) – Final eccentricity.

  • inc_f (Quantity) – Final inclination.

  • f (Quantity) – Magnitude of constant acceleration.

Returns

a_d, delta_V, t_f

Return type

tuple (function, Quantity, Time)

References

  • Pollard, J. E. “Simplified Analysis of Low-Thrust Orbital Maneuvers”, 2000.