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File Formats

The Consultative Committee for Space Data Systems (CCSDS) is a multi-national forum for the development of communications and data systems standards for spaceflight. CCSDS Recommendation Standards (Blue Books) define specific protocols and interfaces, including file format standards for describing Resident Space Objects (RSOs).

View CCSDS Blue Book Publications Website

Ephemeris Upload Formats​

AUTOMATIC is the preferred file format setting for an upload. Satcat detects the format from the file itself, so it is the right choice unless a file needs to be read as a specific format.

FormatNotes
OEMCCSDS Orbit Ephemeris Message. The primary format for exchanging ephemeris and covariance with Kayhan.
OCMCCSDS Orbit Comprehensive Message. Succeeds OEM as the CCSDS standard.
CALIPER18/19 SDS launch vehicle trajectory and covariance.
NASAAccepted. Defined in the 18 SDS Spaceflight Operator's handbook.
GOOEAccepted. Defined in the 18 SDS Spaceflight Operator's handbook.
UTCAccepted. Defined in the 18 SDS Spaceflight Operator's handbook.
MOD_ITCAccepted. Defined in the 18 SDS Spaceflight Operator's handbook.
STKAnsys STK ephemeris.

Download the Spaceflight Safety Handbook for Satellite Operators from Space-Track.org

Orbit Ephemeris Message (OEM)​

CCSDS OEM format is the primary format used for transmission of trajectory and covariance data between operators and Kayhan Space. The OEM file format data conforms to specific requirements, some of which are described here:

  • The order of the ephemeris data items is fixed
    • Epoch, X, Y, Z, X_DOT, Y_DOT, Z_DOT, X_DDOT, Y_DDOT, Z_DDOT
  • The above set of data must be contained on a single line
  • The epoch, position and velocity terms are mandatory

The full OEM specification can be found in the CCSDS Blue Book.

OEM Format Example
CCSDS_OEM_VERS      = 2.0
CREATION_DATE       = 2020-12-15T15:38:49.225
ORIGINATOR          = NONE

META_START
OBJECT_NAME         = CLOUDSAT
OBJECT_ID           = 29107
CENTER_NAME         = Earth
REF_FRAME           = EME2000
TIME_SYSTEM         = UTC
START_TIME          = 2020-12-15T00:00:00.000
STOP_TIME           = 2020-12-15T00:04:00.000
META_STOP

2020-12-15T00:00:00.000 3122.64037649000011 -4990.45786587000021 -3916.75557478000019    1.08772865495000   -4.14753007890000    6.15926256354000
2020-12-15T00:01:00.000 3181.52799254999991 -5229.02201325999977 -3539.48705998000059    0.87451084064000   -3.80189141424000    6.41211163702000
2020-12-15T00:02:00.000 3227.50864269000022 -5446.37293529999988 -3147.82158600999992    0.65764187955000   -3.44066000995000    6.63899379231000

COVARIANCE_START
EPOCH = 2020-12-15T00:00:00.000
COV_REF_FRAME = EME2000
3.11125239948540e-08
3.05332100221654e-09 4.22065366331391e-08
1.91488347500367e-08 -5.05183479388049e-08 8.91260119830244e-08
5.65158667231038e-12 3.05586865373066e-12 1.61288598580544e-12 2.39916702388562e-14
1.13672778417593e-12 2.55641104334951e-12 -9.39613111482829e-12 1.18293576687324e-14 1.41470877634445e-14
-5.76533288642128e-13 -2.65562940015304e-12 1.38692146152402e-11 4.72034064496763e-15 -2.83818383008073e-15 1.25133123791297e-14
EPOCH = 2020-12-15T00:01:00.000
COV_REF_FRAME = EME2000
3.17567176799718e-08
3.32437419051862e-09 4.24057768646188e-08
1.91358863774219e-08 -5.10240180121485e-08 9.04928802437245e-08
5.09608271785789e-12 3.34234474413842e-12 3.71350156780421e-13 2.36439520499879e-14
1.39741458103510e-12 8.56000885512545e-13 -5.74866253871860e-12 1.17013068858110e-14 1.35380301573490e-14
-1.77944970619585e-12 9.03094967529518e-13 8.77991679278633e-12 4.07353345582921e-15 -1.38990652946612e-15 1.25034523391769e-14
EPOCH = 2020-12-15T00:02:00.000
COV_REF_FRAME = EME2000
3.23377139987704e-08
3.60952934619480e-09 4.24350696250564e-08
1.89883124250752e-08 -5.11082343791222e-08 9.12051148059243e-08
4.60062575658043e-12 3.23303249118139e-12 -3.17881697153523e-13 2.33977779287646e-14
1.42059764281136e-12 -2.58588468684403e-13 -2.96254208827873e-12 1.14467327808721e-14 1.33822633582683e-14
-3.11806273559220e-12 4.91398479111300e-12 2.99370043747734e-12 3.55167640830622e-15 -2.50437747093092e-16 1.30925227856410e-14
COVARIANCE_STOP

Orbit Comprehensive Message (OCM)​

OCM is a flexible format designed by CCSDS to succeed OEM as the universal standard for ephemeris data exchange. OCM adds support for many new features such as specific maneuver definitions, combining the functionality of several other previous CCSDS Orbit Data Message formats.

The full OCM specification can be found in the CCSDS Blue Book.

OCM Format Example
CCSDS_OCM_VERS = 3.0
CREATION_DATE = 2025-08-13T00:00:00.000000000
ORIGINATOR = KAYHAN

META_START
EPOCH_TZERO = 2024-10-07T00:00:00.000000000
OBJECT_NAME = TEST-01
INTERNATIONAL_DESIGNATOR = 2025-001A
CATALOG_NAME = SATCAT
OBJECT_DESIGNATOR = 12345
TIME_SYSTEM = UTC
START_TIME = 2024-10-07T00:00:00.000000000
STOP_TIME = 2024-10-07T00:09:00.000000000
META_STOP

TRAJ_START
CENTER_NAME = EARTH
TRAJ_REF_FRAME = EME2000
TRAJ_TYPE = CARTPV
TRAJ_UNITS=[km,km,km,km/s,km/s,km/s]
2024-10-07T00:00:00.000000000 2.3707592920000002E+03 -2.0199688599999999E+02 -6.4840026589999998E+03 6.3466807054999999E+00 -3.3701313103000001E+00 2.4212075303999998E+00
2024-10-07T00:01:00.000000000 2.7461306880000002E+03 -4.0361246100000000E+02 -6.3247499060000000E+03 6.1617715211000004E+00 -3.3482448909999998E+00 2.8853878372000001E+00
2024-10-07T00:02:00.000000000 3.1096014770000002E+03 -6.0347892999999999E+02 -6.1380102550000001E+03 5.9501105793000004E+00 -3.3118411620999999E+00 3.3371354754999998E+00
2024-10-07T00:03:00.000000000 3.4595927830000001E+03 -8.0072942399999999E+02 -5.9245881870000003E+03 5.7125891852999997E+00 -3.2610680868999999E+00 3.7745060627000000E+00
2024-10-07T00:04:00.000000000 3.7945825089999998E+03 -9.9450775699999997E+02 -5.6854031910000003E+03 5.4502084035999996E+00 -3.1961339114000000E+00 4.1956114571000001E+00
2024-10-07T00:05:00.000000000 4.1131118269999997E+03 -1.1839720330000000E+03 -5.4214861639999999E+03 5.1640758257000003E+00 -3.1173067357000002E+00 4.5986275165999997E+00
2024-10-07T00:06:00.000000000 4.4137916550000000E+03 -1.3682983409999999E+03 -5.1339751319999996E+03 4.8554016969999996E+00 -3.0249138066999999E+00 4.9818020599999997E+00
2024-10-07T00:07:00.000000000 4.6953079180000004E+03 -1.5466837900000000E+03 -4.8241115140000002E+03 4.5254956471999996E+00 -2.9193409014000000E+00 5.3434614872999999E+00
2024-10-07T00:08:00.000000000 4.9564285460000001E+03 -1.7183507210000000E+03 -4.4932339739999998E+03 4.1757608548000000E+00 -2.8010308332000000E+00 5.6820198419999999E+00
2024-10-07T00:09:00.000000000 5.1960081550000004E+03 -1.8825496000000001E+03 -4.1427737429999997E+03 3.8076897732999999E+00 -2.6704823043000001E+00 5.9959851172000000E+00
TRAJ_STOP

PHYS_START
DRAG_CONST_AREA = 10.0
DRAG_COEFF_NOM = 0.1
WET_MASS = 1000.0
SRP_CONST_AREA = 10.0
SOLAR_RAD_COEFF = 0.1
DV_REMAINING = 0.0
PHYS_STOP

COV_START
COV_REF_FRAME = EME2000
COV_TYPE = CARTPV
COV_ORDERING = FULL
COV_UNITS=[km,km,km,km/s,km/s,km/s]
2024-10-07T00:00:00.000000000 4.9669735776000003E-06 -1.8439084764000000E-06 2.6708403247000000E-06 1.8649141211999999E-06 -9.0786072590000000E-07 1.7880293602000000E-06 -1.8439084764000000E-06 -1.9912221219000000E-09 6.9474042258000004E-10 -1.7852566032000002E-11 1.7280799123000000E-12 1.3793133886000002E-11 2.6708403247000000E-06 6.9474042258000004E-10 -4.8330555119000001E-10 -4.4481554558000000E-10 3.8526239753999999E-13 1.8921710839999999E-12 1.8649141211999999E-06 -1.7852566032000002E-11 -4.4481554558000000E-10 4.7419610219000000E-09 -2.7156570636999998E-09 2.6284237907000000E-09 -9.0786072590000000E-07 1.7280799123000000E-12 3.8526239753999999E-13 -2.7156570636999998E-09 -1.4665403831000001E-12 1.3889805037999998E-13 1.7880293602000000E-06 1.3793133886000002E-11 1.8921710839999999E-12 2.6284237907000000E-09 1.3889805037999998E-13 6.0156142754000005E-12
2024-10-07T00:01:00.000000000 4.7100405725000002E-06 -1.7859279065000001E-06 2.6079286330999999E-06 2.1178919709000000E-06 -1.0831687858000000E-06 2.1108893248000000E-06 -1.7859279065000001E-06 -2.2279922399999999E-09 8.5683624015000001E-10 -3.3698565603999999E-10 1.9233187484000001E-12 1.6841077649000000E-10 2.6079286330999999E-06 8.5683624015000001E-10 -5.6333364717000004E-10 -3.4780156443999999E-10 3.6295464251999999E-13 1.9566676646000002E-12 2.1178919709000000E-06 -3.3698565603999999E-10 -3.4780156443999999E-10 4.4755707459999997E-09 -2.6433988223999999E-09 3.0223231442999999E-09 -1.0831687858000000E-06 1.9233187484000001E-12 3.6295464251999999E-13 -2.6433988223999999E-09 -1.7123329200000001E-12 2.8605767422999998E-13 2.1108893248000000E-06 1.6841077649000000E-10 1.9566676646000002E-12 3.0223231442999999E-09 2.8605767422999998E-13 5.8808514315000001E-12
2024-10-07T00:02:00.000000000 4.4273058657000002E-06 -1.7096303741999999E-06 2.5357808634999998E-06 2.3328834916000001E-06 -1.2461097175000000E-06 2.4756081744000002E-06 -1.7096303741999999E-06 -2.4280958204000001E-09 1.0113926084000001E-09 -6.9777004078000002E-10 2.1454689986000000E-12 3.1472606036999999E-10 2.5357808634999998E-06 1.0113926084000001E-09 -6.3472022658999998E-10 -2.2408540712000001E-10 3.2462106087999998E-13 2.0275882750000001E-12 2.3328834916000001E-06 -6.9777004078000002E-10 -2.2408540712000001E-10 4.1728739697000002E-09 -2.5469778559000001E-09 3.3765923276000000E-09 -1.2461097175000000E-06 2.1454689986000000E-12 3.2462106087999998E-13 -2.5469778559000001E-09 -1.9412978274000001E-12 4.3005957698999995E-13 2.4756081744000002E-06 3.1472606036999999E-10 2.0275882750000001E-12 3.3765923276000000E-09 4.3005957698999995E-13 5.7100660564000005E-12
2024-10-07T00:03:00.000000000 4.1235167713000000E-06 -1.6162286742999999E-06 2.4555161694999999E-06 2.5056569589000000E-06 -1.3937650904000000E-06 2.8767891509000000E-06 -1.6162286742999999E-06 -2.5875315622000001E-09 1.1556945234999999E-09 -1.0953512838999999E-09 2.3929915240000000E-12 4.5008801877000002E-10 2.4555161694999999E-06 1.1556945234999999E-09 -6.9623810217999995E-10 -7.5135534845000001E-11 2.6986905030999997E-13 2.1042747341999999E-12 2.5056569589000000E-06 -1.0953512838999999E-09 -7.5135534845000001E-11 3.8382803624999996E-09 -2.4276480026000001E-09 3.6849729634000001E-09 -1.3937650904000000E-06 2.3929915240000000E-12 2.6986905030999997E-13 -2.4276480026000001E-09 -2.1493659632000002E-12 5.6868417228999995E-13 2.8767891509000000E-06 4.5008801877000002E-10 2.1042747341999999E-12 3.6849729634000001E-09 5.6868417228999995E-13 5.5040632652000005E-12
2024-10-07T00:04:00.000000000 3.8038609364000002E-06 -1.5072520534999999E-06 2.3683999948999999E-06 2.6326168283999999E-06 -1.5234265398000001E-06 3.3083356096000001E-06 -1.5072520534999999E-06 -2.7028054537999998E-09 1.2871070622999999E-09 -1.5241650650000000E-09 2.6637988754000002E-12 5.7193621605999999E-10 2.3683999948999999E-06 1.2871070622999999E-09 -7.4677232989000001E-10 9.7145263875000009E-11 1.9857082736999999E-13 2.1860112776000001E-12 2.6326168283999999E-06 -1.5241650650000000E-09 9.7145263875000009E-11 3.4768354024999999E-09 -2.2870623648000000E-09 3.9417535862999996E-09 -1.5234265398000001E-06 2.6637988754000002E-12 1.9857082736999999E-13 -2.2870623648000000E-09 -2.3323285767999999E-12 6.9955891202999993E-13 3.3083356096000001E-06 5.7193621605999999E-10 2.1860112776000001E-12 3.9417535862999996E-09 6.9955891202999993E-13 5.2643063129999997E-12
2024-10-07T00:05:00.000000000 3.4738938992000000E-06 -1.3845294743999999E-06 2.2758287832999998E-06 2.7108817687999998E-06 -1.6326465800999999E-06 3.7635328357000001E-06 -1.3845294743999999E-06 -2.7710140638000001E-09 1.4031242600000000E-09 -1.9779803570000002E-09 2.9551840797000001E-12 6.7784932054000001E-10 2.2758287832999998E-06 1.4031242600000000E-09 -7.8533771382000003E-10 2.9042547501999999E-10 1.1091929784000000E-13 2.2720099337000002E-12 2.7108817687999998E-06 -1.9779803570000002E-09 2.9042547501999999E-10 3.0941797904999999E-09 -2.1272687806000002E-09 4.1418831745999998E-09 -1.6326465800999999E-06 2.9551840797000001E-12 1.1091929784000000E-13 -2.1272687806000002E-09 -2.4859422055000001E-12 8.2019904568999989E-13 3.7635328357000001E-06 6.7784932054000001E-10 2.2720099337000002E-12 4.1418831745999998E-09 8.2019904568999989E-13 4.9930128881000000E-12
2024-10-07T00:06:00.000000000 3.1394559453999998E-06 -1.2501662795000000E-06 2.1793121079999999E-06 2.7383550444000002E-06 -1.7192877381000001E-06 4.2351448938000002E-06 -1.2501662795000000E-06 -2.7899355375999999E-09 1.5014243569999999E-09 -2.4499671329999998E-09 3.2637843471000002E-12 7.6559926065000001E-10 2.1793121079999999E-06 1.5014243569999999E-09 -8.1109795786000004E-10 5.0196078881999997E-10 7.4767667337000006E-15 2.3613949423000002E-12 2.7383550444000002E-06 -2.4499671329999998E-09 5.0196078881999997E-10 2.6965017051999999E-09 -1.9507013595000001E-09 4.2810962810000002E-09 -1.7192877381000001E-06 3.2637843471000002E-12 7.4767667337000006E-15 -1.9507013595000001E-09 -2.6060744149000001E-12 9.2806245691999993E-13 4.2351448938000002E-06 7.6559926065000001E-10 2.3613949423000002E-12 4.2810962810000002E-09 9.2806245691999993E-13 4.6932445450000003E-12
2024-10-07T00:07:00.000000000 2.8065801026999999E-06 -1.1065146431000001E-06 2.0804525906000000E-06 2.7137848203000002E-06 -1.7815684991999999E-06 4.7155242112000004E-06 -1.1065146431000001E-06 -2.7580947773999998E-09 1.5799217732000000E-09 -2.9327730953000000E-09 3.5855324748000002E-12 8.3320035624999999E-10 2.0804525906000000E-06 1.5799217732000000E-09 -8.2338389257999997E-10 7.2861677185999998E-10 -1.1078356685000000E-13 2.4531898286000002E-12 2.7137848203000002E-06 -2.9327730953000000E-09 7.2861677185999998E-10 2.2904430932000000E-09 -1.7601563708000001E-09 4.3560227178999999E-09 -1.7815684991999999E-06 3.5855324748000002E-12 -1.1078356685000000E-13 -1.7601563708000001E-09 -2.6888330046999999E-12 1.0206184045000001E-12 4.7155242112000004E-06 8.3320035624999999E-10 2.4531898286000002E-12 4.3560227178999999E-09 1.0206184045000001E-12 4.3689316880000002E-12
2024-10-07T00:08:00.000000000 2.4813888760000000E-06 -9.5613645784999994E-07 1.9809226232000001E-06 2.6368121232000001E-06 -1.8181055466999999E-06 5.1967376924000000E-06 -9.5613645784999994E-07 -2.6748590574000001E-09 1.6368282998000000E-09 -3.4186385408000001E-09 3.9157202746000000E-12 8.7897024712999997E-10 1.9809226232000001E-06 1.6368282998000000E-09 -8.2171444284000002E-10 9.6690837247000008E-10 -2.4246156954000000E-13 2.5463078501999998E-12 2.6368121232000001E-06 -3.4186385408000001E-09 9.6690837247000008E-10 1.8830306326999998E-09 -1.5587665237000000E-09 4.3643085546000003E-09 -1.8181055466999999E-06 3.9157202746000000E-12 -2.4246156954000000E-13 -1.5587665237000000E-09 -2.7307777461000002E-12 1.0954330949000000E-12 5.1967376924000000E-06 8.7897024712999997E-10 2.5463078501999998E-12 4.3643085546000003E-09 1.0954330949000000E-12 4.0249095569000004E-12
2024-10-07T00:09:00.000000000 2.1699857442999999E-06 -8.0176077670999997E-07 1.8824393037000000E-06 2.5080036915999999E-06 -1.8279497223999999E-06 5.6707013568999996E-06 -8.0176077670999997E-07 -2.5404858910000000E-09 1.6707020983000000E-09 -3.8995143304999996E-09 4.2490242575000002E-12 9.0157733408000003E-10 1.8824393037000000E-06 1.6707020983000000E-09 -8.0581378493999998E-10 1.2130454422000000E-09 -3.8572489476999997E-13 2.6395502447999999E-12 2.5080036915999999E-06 -3.8995143304999996E-09 1.2130454422000000E-09 1.4815448557000000E-09 -1.3499538157000000E-09 4.3047062605000001E-09 -1.8279497223999999E-06 4.2490242575000002E-12 -3.8572489476999997E-13 -1.3499538157000000E-09 -2.7290671402000001E-12 1.1502600004000000E-12 5.6707013568999996E-06 9.0157733408000003E-10 2.6395502447999999E-12 4.3047062605000001E-09 1.1502600004000000E-12 3.6668564366000004E-12
COV_STOP

MAN_START
COMMENT UNKNOWN
MAN_ID = 1
MAN_BASIS = PLANNED
MAN_DEVICE_ID = ALL
MAN_PURPOSE = SK
MAN_REF_FRAME = RSW_INERTIAL
DC_TYPE = CONTINUOUS
MAN_COMPOSITION=TIME_ABSOLUTE,MAN_DURA,DELTA_MASS,DV_X,DV_Y,DV_Z,DV_MAG_SIGMA,DV_DIR_SIGMA
MAN_UNITS=[s,kg,km/s,km/s,km/s,%,deg]
2024-10-07T00:05:24.000 600 0 0 0 2.69306e-05 0 0
MAN_STOP

PERT_START
ATMOSPHERIC_MODEL = NRLMSISE00
GRAVITY_MODEL = EGM-08: 8D 8O
N_BODY_PERTURBATIONS=MOON,SUN
PERT_STOP

CALIPER V2.0​

CALIPER Trajectory Covariance V2.0 is a specific format used by launch providers to transmit launch vehicle stage trajectories and covariance to 18/19 SDS. This format is defined by 18/19 SDS directly for use with their SuperCOMBO/CALIPER systems.

CALIPER V2.0 Format Examples
CALIPER EPHEMERIS V2.0 COVARIANCE UVW (or PTW)
LAUNCH TIME:  yyyy ddd hhmm ss.sss...
TimeSinceLaunchInSeconds X  Y  Z  Vx  Vy  Vz
PosCov(1,1) PosCov(2,1)  PosCov(2,2)
PosCov(3,1) PosCov(3,2)  PosCov(3,3)

Propagation Input​

An OPM or OMM is not an ephemeris. Satcat propagates it to produce one, which is then screened like any other ephemeris.

Orbit Parameter Message (OPM)​

The OPM file format is used to describe any of the following data:

  • State vector (Required)
  • Spacecraft parameters (Required if maneuvers are included)
  • Osculating Keplerian elements
  • Maneuver parameters
  • Covariance matrix of position and velocity
  • User-defined parameters
OPM Format Example
CCSDS_OPM_VERS      = 3.0
CREATION_DATE       = 2022-11-06T09:23:57
ORIGINATOR          = JAXA

COMMENT               GEOCENTRIC, CARTESIAN, EARTH FIXED
OBJECT_NAME         = OSPREY 5
OBJECT_ID           = 1998-999A
CENTER_NAME         = EARTH
REF_FRAME           = ITRF2000
TIME_SYSTEM         = UTC

EPOCH               = 2022-12-18T14:28:15.1172
X                   = 6503.514000
Y                   = 1239.647000
Z                   = -717.490000
X_DOT               =   -0.873160
Y_DOT               =    8.740420
Z_DOT               =   -4.191076
MASS                = 3000.000000
SOLAR_RAD_AREA      =   18.770000
SOLAR_RAD_COEFF     =    1.000000
DRAG_AREA           =   18.770000
DRAG_COEFF          =    2.500000

Orbit Mean-Elements Message (OMM)​

The OMM file format may be used to describe any of the following data:

  • Mean Keplerian elements (Required)
  • Spacecraft parameters
  • TLE-related parameters
  • Covariance matrix of position and velocity
  • User-defined parameters
OMM Format Example
CCSDS_OMM_VERS              = 2.0
CREATION_DATE               = 2007-06-05T16:00:00
ORIGINATOR                  = NOAA/USA

OBJECT_NAME                 = GOES 9
OBJECT_ID                   = 1995-025A
CENTER_NAME                 = EARTH
REF_FRAME                   = TEME
TIME_SYSTEM                 = UTC
MEAN_ELEMENT_THEORY         = SGP/SGP4

EPOCH                       = 2007-06-04T10:34:41.4264
MEAN_MOTION                 = 1.00273272
ECCENTRICITY                = 0.0005013
INCLINATION                 = 3.0539
RA_OF_ASC_NODE              = 81.7939
ARG_OF_PERICENTER           = 249.2363
MEAN_ANOMALY                = 150.1602
GM                          = 398600.8
EPHEMERIS_TYPE              = 0
CLASSIFICATION_TYPE         = U
NORAD_CAT_ID                = 23581
ELEMENT_SET_NO              = 0925
REV_AT_EPOCH                = 4316
BSTAR                       = 0.0001
MEAN_MOTION_DOT             = -0.00000113
MEAN_MOTION_DDOT            = 0.0

COV_REF_FRAME               = TEME
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

Conjunction Data Messages​

Conjunction Data Messages (CDMs) are sent to operators when future close approaches between an operator's RSOs and other objects are identified. Space-Track.org and other space sensor network data providers will continue to send CDMs until the conjunction event is resolved by mitigating actions or its TCA passes.

CDMs are defined using Key=Value Notation (KVN) files, however Kayhan Space services also allow CDM uploads to be in JSON-format KVN files. CDMs that Satcat generates from operator-supplied ephemeris use these same formats.

CDM Format Example
CONSTELLATION = Kayhan Space Corp
CDM_ID = 5XXXXXXXX
INSERT_EPOCH = 2023-01-01T00:00:00
CCSDS_CDM_VERS = 1.0
CREATION_DATE = 2023-01-01T00:00:00.000000
ORIGINATOR = CSpOC
...

Download the CCSDS 508.0-B-1 CDM Blue Book

See Operational Data for what an Operational CDM contains and when it is shared.

Manual Data Entry​

Satcat services allow for manual entry of orbit data such as state vectors or TLE format.

TLE Manual Entry​

TLEs are used for SGP4 analytic methods of propagation. TLEs are not recommended for operational spaceflight safety due to their lower accuracy. A common rule of thumb puts positional uncertainty growth at roughly 1 km per day.

Data FieldDescription
Strict validationEnable or disable strict validation of the TLE data
TLE dataEnter a valid TLE format string
IdentificationOptionally enter the RSO's NORAD ID and/or Common Name

TLE format specification​

Below is an example of a three line TLE, where the header line displays the RSO's Common Name.

ISS (ZARYA)
1 25544U 98067A   04236.56031392  .00020137  00000-0  16538-3 0  9993
2 25544  51.6335 344.7760 0007976 126.2523 325.9359 15.70406856328906

View TLE Format Specification on Space-Track.org

State Vector Manual Entry​

State vectors describe a spacecraft at one moment in time, and are typically derived from orbit determination processes.

Data FieldDescription
IdentificationOptionally enter the RSO's NORAD ID and/or Common Name
State vector positionEnter three comma separated components of the position and the data units
State vector velocityEnter three comma separated components of the velocity and the data units
RSO propertiesEnter the RSO's mass, hard body radius, and SRP and drag parameters

RSO properties​

These values are used to compute collision risk and propagate the ephemeris. A property left empty is taken from the RSO's saved parameters.

PropertyUnitsRequired
Mass$kg$No
Hard Body Radius (HBR)$m$No
SRP Area
Coefficient of Reflectivity		$m^2$
--		No
Drag Area
Coefficient of Drag		$m^2$
--		No

Covariance matrix data entry​

Optionally enter the covariance matrix values for the state. Choose the appropriate reference frame and units, and select whether the matrix was entered as lower triangular or the full NxN matrix.

View Supported Reference Frames Documentation

Export Formats​

Ephemeris can be exported as OEM, OCM, NASA, or ORIGINAL, which returns the file exactly as uploaded. CDMs can be exported as JSON, KVN, or XML.