poliastro2.core.actions.thrust.change_ecc_inc

poliastro2.core.actions.thrust.change_ecc_inc(orb_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:

• orb_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.