poliastro.maneuver
¶
Orbital maneuvers.
Module Contents¶
Classes¶
Class to represent a Maneuver. |
- class poliastro.maneuver.Maneuver(*args)¶
Class to represent a Maneuver.
Each
Maneuver
consists on a list of impulses \(\Delta v_i\) (changes in velocity) each one applied at a certain instant \(t_i\). You can access them directly indexing theManeuver
object itself.>>> man = Maneuver((0 * u.s, [1, 0, 0] * u.km / u.s), ... (10 * u.s, [1, 0, 0] * u.km / u.s)) >>> man[0] (<Quantity 0. s>, <Quantity [1., 0., 0.] km / s>) >>> man.impulses[1] (<Quantity 10. s>, <Quantity [1., 0., 0.] km / s>)
- __repr__(self)¶
Return repr(self).
- __getitem__(self, key)¶
- classmethod impulse(cls, dv)¶
Single impulse at current time.
- Parameters
dv (numpy.ndarray) – Velocity components of the impulse.
- classmethod hohmann(cls, orbit_i, r_f)¶
Compute a Hohmann transfer between two circular orbits.
- Parameters
orbit_i (poliastro.twobody.orbit.Orbit) – Initial orbit
r_f (astropy.unit.Quantity) – Final orbital radius
- classmethod bielliptic(cls, orbit_i, r_b, r_f)¶
Compute a bielliptic transfer between two circular orbits.
- Parameters
orbit_i (poliastro.twobody.orbit.Orbit) – Initial orbit
r_b (astropy.unit.Quantity) – Altitude of the intermediate orbit
r_f (astropy.unit.Quantity) – Final orbital radius
- classmethod lambert(cls, orbit_i, orbit_f, method=lambert_izzo, **kwargs)¶
Computes Lambert maneuver between two different points.
- Parameters
orbit_i (Orbit) – Initial orbit
orbit_f (Orbit) – Final orbit
method (function) – Method for solving Lambert’s problem
**kwargs – Extra kwargs for Lambert method.
- get_total_time(self)¶
Returns total time of the maneuver.
- get_total_cost(self)¶
Returns total cost of the maneuver.
- classmethod correct_pericenter(cls, orbit, max_delta_r)¶
Returns a Maneuver with the time before burning and the velocity vector in direction of the burn.
- Parameters
- Returns
maneuver – Maneuver with the maximum time before we do an orbit-adjustment burn to restore the perigee to its nominal value and the velocity vector of the spacecraft to achieve the desired correction.
- Return type
- Raises
If the correction maneuver is not implemented for the attractor.
if the eccentricity is greater than 0.001.