CCSDS_OPM_VERS    = 3.0

COMMENT  Generated by GSOC, R. Kiehling
COMMENT  Current intermediate orbit IO2 and maneuver planning data

CREATION_DATE     = 2000-06-03T05:33:00.000
ORIGINATOR        = GSOC

OBJECT_NAME       = EUTELSAT W4
OBJECT_ID         = 2000-028A
CENTER_NAME       = EARTH
REF_FRAME         = ZZRF
REF_FRAME_EPOCH   = 2019-09-09T00:00:00.0
TIME_SYSTEM       = TAI

COMMENT  State Vector
EPOCH             = 2006-06-03T00:00:00.000
X                 =   6655.9942        [km]
Y                 = -40218.5751        [km]
Z                 =    -82.9177        [km]
X_DOT             =      3.11548208    [km/s]
Y_DOT             =      0.47042605    [km/s]
Z_DOT             =     -0.00101495    [km/s]

COMMENT  Keplerian elements
SEMI_MAJOR_AXIS   =   41399.5123       [km]
ECCENTRICITY      =       0.020842611
INCLINATION       =       0.117746     [deg]
RA_OF_ASC_NODE    =      17.604721     [deg]
ARG_OF_PERICENTER =     218.242943     [deg]
TRUE_ANOMALY      =      41.922339     [deg]
GM                =  398600.4415       [km**3/s**2]

COMMENT  Spacecraft parameters
MASS              =    1913.000        [kg]
SOLAR_RAD_AREA    =      10.000        [m**2]
SOLAR_RAD_COEFF   =       1.300
DRAG_AREA         =      10.000        [m**2]
DRAG_COEFF        =       2.300

COMMENT covariance comment 1
COMMENT covariance comment 2
COV_REF_FRAME = ZZRF
CX_X = 3.331349476038534e-04
CY_X = 4.618927349220216e-04
CY_Y = 6.782421679971363e-04
CZ_X = -3.070007847730449e-04
CZ_Y = -4.221234189514228e-04
CZ_Z = 3.231931992380369e-04
CX_DOT_X = -3.349365033922630e-07
CX_DOT_Y = -4.686084221046758e-07
CX_DOT_Z = 2.484949578400095e-07
CX_DOT_X_DOT = 4.296022805587290e-10
CY_DOT_X = -2.211832501084875e-07
CY_DOT_Y = -2.864186892102733e-07
CY_DOT_Z = 1.798098699846038e-07
CY_DOT_X_DOT = 2.608899201686016e-10
CY_DOT_Y_DOT = 1.767514756338532e-10
CZ_DOT_X = -3.041346050686871e-07
CZ_DOT_Y = -4.989496988610662e-07
CZ_DOT_Z = 3.540310904497689e-07
CZ_DOT_X_DOT = 1.869263192954590e-10
CZ_DOT_Y_DOT = 1.008862586240695e-10
CZ_DOT_Z_DOT = 6.224444338635500e-10

COMMENT  2 planned maneuvers

COMMENT  First maneuver: AMF-3
COMMENT  Non-impulsive, thrust direction fixed in inertial frame
MAN_EPOCH_IGNITION =    2000-06-03T09:00:34.1
MAN_DURATION      =     132.60         [s]
MAN_DELTA_MASS    =     -18.418        [kg]
MAN_REF_FRAME     =       J2000
MAN_DV_1          =      -0.02325700   [km/s]
MAN_DV_2          =       0.01683160   [km/s]
MAN_DV_3          =      -0.00893444   [km/s]

COMMENT  Second maneuver: first station acquisition maneuver
COMMENT  impulsive, thrust direction fixed in RTN frame
MAN_EPOCH_IGNITION = 2000-06-05T18:59:21.0
MAN_DURATION      =       0.00         [s]
MAN_DELTA_MASS    =      -1.469        [kg]
MAN_REF_FRAME     =       RTN
MAN_DV_1          =       0.00101500   [km/s]
MAN_DV_2          =      -0.00187300   [km/s]
MAN_DV_3          =       0.00000000   [km/s]