astrodynx.dE

astrodynx.dE(E, e)

Returns the derivative of Kepler’s equation for elliptical orbits with respect to the eccentric anomaly.

Parameters:

• E (ArrayLike) – Eccentric anomaly.

• e (ArrayLike) – Eccentricity of the orbit, 0 <= e < 1.

Return type:

Array

Returns:

The derivative of Kepler’s equation for elliptical orbits with respect to the eccentric anomaly.

Notes

The derivative of Kepler’s equation for elliptical orbits with respect to the eccentric anomaly is:

\[ dE = 1 - e \cos E \]

where \(E\) is the eccentric anomaly and \(e\) is the eccentricity.