CCSDS_OCM_VERS    = 3.0
CREATION_DATE     = 1998-11-06T09:23:57
ORIGINATOR        = ESOC

META_START
TIME_SYSTEM       = UTC
EPOCH_TZERO       = 1998-12-18T14:28:15.1172
META_STOP

TRAJ_START
COMMENT ORBIT EPHEMERIS INCORPORATING DEPLOYMENTS AND MANEUVERS (BELOW)
COMMENT intervening data records omitted after DT=20.0
TRAJ_REF_FRAME    = TOD
TRAJ_FRAME_EPOCH  = 1998-12-18T14:28:15.1172
TRAJ_TYPE         = CARTPVA
TRAJ_UNITS        = [ km, km, km, km/s, km/s, km/s, km/s**2, km/s**2, km/s**2 ]
0.000000 2789.6 -280.0 -1746.8 4.73 -2.50 -1.04 0.008 0.001 -0.159
10.000000 2783.4 -308.1 -1877.1 5.19 -2.42 -2.00 0.008 0.001 0.001
20.000000 2776.0 -336.9 -2008.7 5.64 -2.34 -1.95 0.008 0.001 0.159
1998-12-18T14:36:35.1172 2164.375 1115.811 -688.131 -3.53328 -2.88452 0.88535 0.0 0.0 0.0
TRAJ_STOP

PHYS_START
COMMENT S/C Physical Characteristics:
DRAG_CONST_AREA   = 10.00 [m**2]
DRAG_COEFF_NOM    = 2.300
WET_MASS          = 100.0 [kg]
SRP_CONST_AREA    = 4.00
SOLAR_RAD_COEFF   = 1.300
PHYS_STOP

MAN_START
COMMENT           = Ten 1kg objects deployed from 200kg host over 100 s timespan
COMMENT           = 20 deg off of back-track direction
MAN_ID            = CUBESAT_DEPLOY
MAN_BASIS         = CANDIDATE
MAN_DEVICE_ID     = DEPLOY
MAN_PURPOSE       = DEPLOY
MAN_REF_FRAME     = RSW_ROTATING
MAN_COMPOSITION   = TIME_RELATIVE, DEPLOY_ID, DEPLOY_DV_X, DEPLOY_DV_Y, DEPLOY_DV_Z, DEPLOY_MASS, DEPLOY_DV_SIGMA, DEPLOY_DV_RATIO, DEPLOY_DV_CDA
MAN_UNITS         = [n/a, km/s, km/s, km/s, kg, %, n/a, m**2]
500.0 CUBESAT_10  2.8773E-4 -9.3969E-4  1.8491E-4 -1.0 5.0 -0.005025 0.033
510.0 CUBESAT_11  1.4208E-4 -9.3969E-4  3.1111E-4 -1.0 5.0 -0.005051 0.033
520.0 CUBESAT_12 -4.8670E-5 -9.3969E-4  3.3854E-4 -1.0 5.0 -0.005076 0.033
530.0 CUBESAT_13 -2.2398E-4 -9.3969E-4  2.5848E-4 -1.0 5.0 -0.005102 0.033
540.0 CUBESAT_14 -3.2817E-4 -9.3969E-4  9.6360E-5 -1.0 5.0 -0.005128 0.033
550.0 CUBESAT_15 -3.2817E-4 -9.3969E-4 -9.6360E-5 -1.0 5.0 -0.005154 0.033
560.0 CUBESAT_16 -2.2398E-4 -9.3969E-4 -2.5848E-4 -1.0 5.0 -0.005181 0.033
570.0 CUBESAT_17 -4.8670E-5 -9.3969E-4 -3.3854E-4 -1.0 5.0 -0.005208 0.033
580.0 CUBESAT_18  1.4208E-4 -9.3969E-4 -3.1111E-4 -1.0 5.0 -0.005236 0.033
590.0 CUBESAT_19  2.8773E-4 -9.3969E-4 -1.8491E-4 -1.0 5.0 -0.005263 0.033
MAN_STOP

MAN_START
COMMENT           = 100 s of 0.5N +in-track thrust w/effic η=0.95, Isp=300s, 5% 1-sigma error
MAN_ID            = E_W_20160305B
MAN_BASIS         = CANDIDATE
MAN_DEVICE_ID     = THR_01
MAN_PURPOSE       = ORBIT
MAN_REF_FRAME     = RSW_ROTATING
MAN_COMPOSITION   = TIME_ABSOLUTE, TIME_RELATIVE, MAN_DURA, THR_X, THR_Y, THR_Z, THR_MAG_SIGMA, THR_DIR_SIGMA, THR_INTERP, THR_ISP, THR_EFFIC
MAN_UNITS         = [s, N, N, N, %, deg, n/a, s, n/a]
1998-12-18T14:36:35.1172 500.0 100.0 0.0 0.5 0.0 5.0 1.0 ON 300.0 0.95
MAN_STOP

PERT_START
COMMENT  Perturbations specification
GM                = 398600.4415 [km**3/s**2]
PERT_STOP

OD_START
COMMENT           = Orbit Determination information
OD_ID             = OOD #10059
OD_PREV_ID        = OOD #10058
OD_METHOD         = SF: ODTK
OD_EPOCH          = 2001-11-06T11:17:33
OBS_USED          = 0273
TRACKS_USED       = 091
OD_STOP
