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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Specific energy. |
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Eccentricity vector. |
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Elapsed time since latest perifocal passage. |
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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 |
Eccentricity for frozen orbits when the inclination is critical. |
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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.energy(k, r, v)¶
Specific energy.
- poliastro.twobody.elements.eccentricity_vector(k, r, v)¶
Eccentricity vector.
- poliastro.twobody.elements.t_p(nu, ecc, k, r_p)¶
Elapsed time since latest perifocal passage.
- poliastro.twobody.elements.heliosynchronous(k, R, J2, n_sunsync, a=None, ecc=None, inc=None)¶
- 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.
- poliastro.twobody.elements.coe2rv(k, p, ecc, inc, raan, argp, nu)¶
- poliastro.twobody.elements.coe2rv_many(k_arr, p_arr, ecc_arr, inc_arr, raan_arr, argp_arr, nu_arr)¶