@spiceErrorCheck<EOL>def spkaps(targ, et, ref, abcorr, stobs, accobs):
targ = ctypes.c_int(targ)<EOL>et = ctypes.c_double(et)<EOL>ref = stypes.stringToCharP(ref)<EOL>abcorr = stypes.stringToCharP(abcorr)<EOL>stobs = stypes.toDoubleVector(stobs)<EOL>accobs = stypes.toDoubleVector(accobs)<EOL>starg = stypes.emptyDoubleVector(<NUM_LIT:6>)<EOL>lt = ctypes.c_double()<EOL>dlt = ctypes.c_double()<EOL>libspice.spkaps_c(targ, et, ref, abcorr, stobs, accobs, starg,<EOL>ctypes.byref(lt), ctypes.byref(dlt))<EOL>return stypes.cVectorToPython(starg), lt.value, dlt.value<EOL>
Given the state and acceleration of an observer relative to the
solar system barycenter, return the state (position and velocity)
of a target body relative to the observer, optionally corrected
for light time and stellar aberration. All input and output
vectors are expressed relative to an inertial reference frame.

This routine supersedes :func:`spkapp`.

SPICE users normally should call the high-level API routines
:func:`spkezr` or :func:`spkez` rather than this routine.
http://naif.jpl.nasa.gov/pub/naif/toolkit_docs/C/cspice/spkaps_c.html

:param targ: Target body.
:type targ: int
:param et: Observer epoch.
:type et: float
:param ref: Inertial reference frame of output state.
:type ref: str
:param abcorr: Aberration correction flag.
:type abcorr: str
:param stobs: State of the observer relative to the SSB.
:type stobs: 6-Element Array of floats
:param accobs: Acceleration of the observer relative to the SSB.
:type accobs: 6-Element Array of floats
:return:
         State of target,
         One way light time between observer and target,
         Derivative of light time with respect to time.
:rtype: tuple