@spiceErrorCheck<EOL>def eqncpv(et, epoch, eqel, rapol, decpol):
et = ctypes.c_double(et)<EOL>epoch = ctypes.c_double(epoch)<EOL>eqel = stypes.toDoubleVector(eqel)<EOL>rapol = ctypes.c_double(rapol)<EOL>decpol = ctypes.c_double(decpol)<EOL>state = stypes.emptyDoubleVector(<NUM_LIT:6>)<EOL>libspice.eqncpv_c(et, epoch, eqel, rapol, decpol, state)<EOL>return stypes.cVectorToPython(state)<EOL>
Compute the state (position and velocity of an object whose
trajectory is described via equinoctial elements relative to some
fixed plane (usually the equatorial plane of some planet).

http://naif.jpl.nasa.gov/pub/naif/toolkit_docs/C/cspice/eqncpv_c.html

:param et: Epoch in seconds past J2000 to find state.
:type et: float
:param epoch: Epoch of elements in seconds past J2000.
:type epoch: float
:param eqel: Array of equinoctial elements
:type eqel: 9-Element Array of floats
:param rapol: Right Ascension of the pole of the reference plane.
:type rapol: float
:param decpol: Declination of the pole of the reference plane.
:type decpol: float
:return: State of the object described by eqel.
:rtype: 6-Element Array of floats