CCSDS_OPM_VERS = 2.0
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 = GCRF
TIME_SYSTEM = GPS
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 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 = EME2000
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]
MAN_EPOCH_IGNITION = 2000-06-05T18:59:51.0
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]