# 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 () – Initial orbit, containing all the information.

• ecc_f (float) – Final eccentricity.

• inc_f () – Final inclination.

• f () – Magnitude of constant acceleration.

Returns

a_d, delta_V, t_f

Return type

tuple (function, , )

References

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