poliastro.twobody.elements
¶
Module Contents¶
Functions¶
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Circular velocity for a given body (k) and semimajor axis (a). |
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Mean motion given body (k) and semimajor axis (a). |
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Period given body (k) and semimajor axis (a). |
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Limit true anomaly for hyperbolic orbits. |
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Cccentricity for frozen orbits when the argument of perigee is critical. |
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Inclination for frozen orbits |
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Eccentricity for frozen orbits when the inclination is critical. |
Attributes¶
- poliastro.twobody.elements.u_kms¶
- poliastro.twobody.elements.u_km3s2¶
- poliastro.twobody.elements.circular_velocity(k, a)¶
Circular velocity for a given body (k) and semimajor axis (a).
- poliastro.twobody.elements.mean_motion(k, a)¶
Mean motion given body (k) and semimajor axis (a).
- poliastro.twobody.elements.period(k, a)¶
Period given body (k) and semimajor axis (a).
- poliastro.twobody.elements.hyp_nu_limit(ecc, r_max_ratio=np.inf)¶
Limit true anomaly for hyperbolic orbits.
- poliastro.twobody.elements.get_eccentricity_critical_argp(R, J2, J3, a, inc)¶
Cccentricity for frozen orbits when the argument of perigee is critical.
- poliastro.twobody.elements.get_inclination_critical_argp(R, J2, J3, a, ecc)¶
Inclination for frozen orbits when the argument of perigee is critical and the eccentricity is given.
- poliastro.twobody.elements.get_eccentricity_critical_inc(ecc=None)¶
Eccentricity for frozen orbits when the inclination is critical.
If ecc is None we set an arbitrary value which is the Moon eccentricity because it seems reasonable.
- Parameters
ecc (Quantity, optional) – Eccentricity, default to None.