PDS_VERSION_ID               = PDS3
RECORD_TYPE                  = STREAM
DATA_RECORDS                 = 126
INSTRUMENT_NAME              = "MARS EXPRESS ORBITER RADIO SCIENCE"
TARGET_NAME                  = MARS
DATA_SET_ID                  =  "MEX-M-MRS-1/2/3-PRM-0132-V1.0"
MISSION_NAME                 = "MARS EXPRESS"
INSTRUMENT_HOST_NAME         = "MARS EXPRESS"
INSTRUMENT_HOST_ID           = "MEX"
STANDARD_DATA_PRODUCT_ID     = LSK
SOURCE_PRODUCT_ID            = "naif0007.tls"
PRODUCT_ID                   = "M00NAIFL02_TLS_042181538_00.AUX"
START_TIME                   = 1972-01-01T00:00:00
STOP_TIME                    = 2010-12-31T23:59:59
PRODUCT_CREATION_TIME        =  2005-11-02T18:18:10.000
PRODUCER_ID                  = "NAIF"
^SPICE_KERNEL                = "M00NAIFL02_TLS_042181538_00.AUX"
OBJECT                       = SPICE_KERNEL
  INTERCHANGE_FORMAT           = ASCII
  KERNEL_TYPE                  = LEAPSECONDS
  DESCRIPTION                  = "
    The Leapseconds Kernel (LSK) is an ASCII file, the contents of which
    may be used to compute the time difference DELTA_ET, which is the
    increment to be applied to UTC to give ET, or

                         ET - UTC                         (1)

    The difference between UTC and TAI, DELTA_AT, or

                        TAI - UTC                         (2)

    is always an integral number of seconds.  The value of DELTA_AT was 10
    seconds in January 1972, and increases (or decreases) by one each time
    a leap second is declared.  Combining (1) and (2) gives  DELTA_ET
    equal to
                        ET - (TAI - DELTA_AT)     or      (3)
                        (ET - TAI) + DELTA_AT

    The difference (ET - TAI) is periodic, and is equal to

                         DELTA_T_A  + K sin E             (4)

    where DELTA_T_A and K are constant, and E is the eccentric anomaly of
    the heliocentric orbit of the Earth-Moon barycenter.  This expression,
    (4), which ignores small-period fluctuations, is accurate to about
    0.000030 seconds.

    The eccentric anomaly E is given by

                        M + EB sin M                      (5)

    where M is the mean anomaly, which in turn is given by

                        M0  +  M1*t                       (6)

    where t is the number of ephemeris seconds past J2000.

    In order to compute DELTA_ET, the following items are necessary.  These
    are tabulated in the Leapseconds Kernel File.

            DELTA_TA
            K
            EB
            M0
            M1
            DELTA_AT

    The file is created by the JPL Navigation and Ancillary Information
    Facility (NAIF) and is updated as needed (e.g., when a new leapsecond
    is added).  More information about the Leapseconds Kernel File, the NAIF
    Toolkit (for using these files), and NAIF itself can be found at
                      http://pds-naif.jpl.nasa.gov/                  "

END_OBJECT                   = SPICE_KERNEL
END