Spaceborne Object States (spacekernel.state)

Base class for States

State

State Vector

StateVector(time, r, v[, frame])

Classical Orbital Elements (COE)

Conversion between anomalies

eca_from_mea(mea, ecc)	Compute the eccentric anomaly from the mean anomaly.
mea_from_eca(eca, ecc)	Compute the mean anomaly from the eccentric anomaly.
tra_from_eca(eca, ecc)	Compute the true anomaly from the eccentric anomaly.
eca_from_tra(tra, ecc)	Compute the eccentric anomaly from the true anomaly.
tra_from_mea(mea, ecc)	Compute the true anomaly from the mean anomaly.
mea_from_tra(tra, ecc)	Compute the mean anomaly from the true anomaly.

Conversion from/to SMA

orp_from_sma(sma[, GM])	Compute orbital period(s) from semimajor axis (or axes).
sma_from_orp(orp[, GM])	Compute semimajor axis (or axes) from orbital period(s).
mnm_from_sma(sma[, GM])	Compute mean motion(s) from semimajor axis (or axes).
sma_from_mnm(mnm[, GM])	Compute semimajor axis (or axes) from mean motion(s).