poliastro.twobody.elements

Module Contents

Functions

circular_velocity(k, a)	Circular velocity for a given body (k) and semimajor axis (a).
mean_motion(k, a)	Mean motion given body (k) and semimajor axis (a).
period(k, a)	Period given body (k) and semimajor axis (a).
energy(k, r, v)	Specific energy.
eccentricity_vector(k, r, v)	Eccentricity vector.
t_p(nu, ecc, k, r_p)	Elapsed time since latest perifocal passage.
heliosynchronous(k, R, J2, n_sunsync, a=None, ecc=None, inc=None)
hyp_nu_limit(ecc, r_max_ratio=np.inf)	Limit true anomaly for hyperbolic orbits.
get_eccentricity_critical_argp(R, J2, J3, a, inc)	Cccentricity for frozen orbits when the argument of perigee is critical.
get_inclination_critical_argp(R, J2, J3, a, ecc)	Inclination for frozen orbits
get_eccentricity_critical_inc(ecc=None)	Eccentricity for frozen orbits when the inclination is critical.
coe2rv(k, p, ecc, inc, raan, argp, nu)
coe2rv_many(k_arr, p_arr, ecc_arr, inc_arr, raan_arr, argp_arr, nu_arr)

Attributes

u_kms
u_km3s2

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.

Parameters

• ecc (Quantity) – Eccentricity, should be larger than 1.

• r_max_ratio (float, optional) – Value of \(r_{\text{max}} / p\) for this angle, default to infinity.

poliastro.twobody.elements.get_eccentricity_critical_argp(R, J2, J3, a, inc)

Cccentricity for frozen orbits when the argument of perigee is critical.

Parameters

• R (Quantity) – Planet radius.

• J2 (Quantity) – Planet J2 coefficient.

• J3 (Quantity) – Planet J3 coefficient.

• a (Quantity) – Orbit’s semimajor axis

• inc (Quantity) – Inclination.

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.

Parameters

• R (Quantity) – Planet radius.

• J2 (Quantity) – Planet J2 coefficient.

• J3 (Quantity) – Planet J3 coefficient.

• a (Quantity) – Semimajor axis.

• ecc (Quantity) – Eccentricity.

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)