hapsira.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, ecc, inc])
hyp_nu_limit(ecc[, r_max_ratio])	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])	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, ...)

Attributes

u_kms
u_km3s2

hapsira.twobody.elements.u_kms

hapsira.twobody.elements.u_km3s2

hapsira.twobody.elements.circular_velocity(k, a)

Circular velocity for a given body (k) and semimajor axis (a).

hapsira.twobody.elements.mean_motion(k, a)

Mean motion given body (k) and semimajor axis (a).

hapsira.twobody.elements.period(k, a)

Period given body (k) and semimajor axis (a).

hapsira.twobody.elements.energy(k, r, v)

Specific energy.

hapsira.twobody.elements.eccentricity_vector(k, r, v)

Eccentricity vector.

hapsira.twobody.elements.t_p(nu, ecc, k, r_p)

Elapsed time since latest perifocal passage.

hapsira.twobody.elements.heliosynchronous(k, R, J2, n_sunsync, a=None, ecc=None, inc=None)

hapsira.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.

hapsira.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.

hapsira.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.

hapsira.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.

hapsira.twobody.elements.coe2rv(k, p, ecc, inc, raan, argp, nu)

hapsira.twobody.elements.coe2rv_many(k_arr, p_arr, ecc_arr, inc_arr, raan_arr, argp_arr, nu_arr)