# poliastro.maneuver¶

Orbital maneuvers.

## Module Contents¶

### Classes¶

 Maneuver 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 the Maneuver 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).

_initialize(self, dts, dvs)
__getitem__(self, key)
classmethod impulse(cls, dv)

Single impulse at current time.

Parameters

dv (np.array) – Velocity components of the impulse.

classmethod hohmann(cls, orbit_i, r_f)

Compute a Hohmann transfer between two circular orbits.

Parameters
classmethod bielliptic(cls, orbit_i, r_b, r_f)

Compute a bielliptic transfer between two circular orbits.

Parameters
• orbit_i () – Initial orbit

• r_b (astropy.unit.Quantity) – Altitude of the intermediate orbit

• r_f (astropy.unit.Quantity) – Final altitude of the orbit

classmethod lambert(cls, orbit_i, orbit_f, method=lambert_izzo, short=True, **kwargs)

Computes Lambert maneuver between two different points.

Parameters
• orbit_i () – Initial orbit

• orbit_f () – Final orbit

• method (function) – Method for solving Lambert’s problem

• short (keyword, boolean) – Selects between short and long solution

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
• orbit () – Position and velocity of a body with respect to an attractor at a given time (epoch).

• max_delta_r () – Maximum satellite’s geocentric distance

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.