Supported File Formats
The Consultative Committee for Space Data Systems (CCSDS) is a multi-national forum for the development of communications & 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
Conjunction Events
Conjunction Data Messages
Conjunction Data Messages (CDMs) are sent to operators when future close approaches between operator assets and other RSOs are identified. Space-Track.org and other space sensor network data providers will continue to send CDMs until the event is resolved by mitigating actions or the event 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.
CDM Format Example
- KVN Format
- JSON Format
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
...
{
"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
Operational CDM Reports
Satcat Operations will generate additional CDMs based on operator data. These operational CDM reports follow the same file formats as third-party CDMs. Operators that upload their owner/operator ephemeris will be able to immediately see how their data affects the conjunction geometry and risk assessment, and download or share these reports as needed.
Learn more about Operational Data in Satcat
Orbit Data Messages
File formats that describe orbits are defined by the CCSDS Orbit Data Messages Blue Book. These data formats include definitions for state vectors, Keplerian and mean elements, and entire trajectories with or without acceleration and covariance.
Each ODM file format also includes a metadata section which describes the ODM version, creation date, and other important data. Please read the ODM Blue Book for the complete description of each format.
Download the CCSDS 502.0-B-3 ODM Blue Book
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
- OPM with State
- OPM with State, Keplerian Elements, and Covariance
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
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 = TOD
TIME_SYSTEM = UTC
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]
MEAN_ANOMALY = 41.922339 [deg]
GM = 398600.4415 [km**3/s**2]
COMMENT Spacecraft parameters
MASS = 1913.000000 [kg]
SOLAR_RAD_AREA = 10.000 [m**2]
SOLAR_RAD_COEFF = 1.300
DRAG_AREA = 10.000 [m**2]
DRAG_COEFF = 2.300
COV_REF_FRAME = RTN
CX_X = 3.331349476038534e-04 [km**2]
CY_X = 4.618927349220216e-04 [km**2]
CY_Y = 6.782421679971363e-04 [km**2]
CZ_X = -3.070007847730449e-04 [km**2]
CZ_Y = -4.221234189514228e-04 [km**2]
CZ_Z = 3.231931992380369e-04 [km**2]
CX_DOT_X = -3.349365033922630e-07 [km**2/s]
CX_DOT_Y = -4.686084221046758e-07 [km**2/s]
CX_DOT_Z = 2.484949578400095e-07 [km**2/s]
CX_DOT_X_DOT = 4.296022805587290e-10 [km**2/s**2]
CY_DOT_X = -2.211832501084875e-07 [km**2/s]
CY_DOT_Y = -2.864186892102733e-07 [km**2/s]
CY_DOT_Z = 1.798098699846038e-07 [km**2/s]
CY_DOT_X_DOT = 2.608899201686016e-10 [km**2/s**2]
CY_DOT_Y_DOT = 1.767514756338532e-10 [km**2/s**2]
CZ_DOT_X = -3.041346050686871e-07 [km**2/s]
CZ_DOT_Y = -4.989496988610662e-07 [km**2/s]
CZ_DOT_Z = 3.540310904497689e-07 [km**2/s]
CZ_DOT_X_DOT = 1.869263192954590e-10 [km**2/s**2]
CZ_DOT_Y_DOT = 1.008862586240695e-10 [km**2/s**2]
CZ_DOT_Z_DOT = 6.224444338635500e-10 [km**2/s**2]
USER_DEFINED_EARTH_MODEL = WGS-84
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
- OMM with Covariance
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
Orbit Ephemeris Message (OEM)
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
Additional requirements can be found in the CCSDS Blue Book.
OEM Format Example
- OEM with Covariance
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
Other Trajectory Formats
Kayhan Satcat Launch is a Launch Conjunction Assessment (LCA) service, and adheres to the LCA Handbook of operations.
Download the Launch Conjunction Assessment Handbook from Space-Track.org
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 V2.0 Elements
- CALIPER V2.0 Example
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)
CALIPER EPHEMERIS V2.0 COVARIANCE PTW
LAUNCH TIME: 2019 20 1105 35.986
0.000 -15614.190 9512.504 27201.506 -0.031674 -0.511889 -2.511603
0.033489 -0.042779 0.112008
-0.000589 0.000675 0.005907
258.619 -15621.660 9378.301 26541.559 -0.025764 -0.526209 -2.592410
0.033953 -0.045187 0.121013
-0.000573 0.000669 0.006007
510.329 -15627.212 9243.933 25878.882 -0.018003 -0.541701 -2.673392
0.034352 -0.047596 0.130522
-0.000543 0.000660 0.006000
Satcat Data Entry Forms
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 (positional uncertainty increases by ~1 km/day).
| Data Field | Description |
|---|---|
| Strict validation | Enable or disable strict validation of the TLE data |
| TLE data | Enter a valid TLE format string (See below for format example) |
| Identification | Optionally enter the asset'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 asset'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 Field | Description |
|---|---|
| Identification | Optionally enter the asset's NORAD ID and/or Common Name |
| State vector position | Enter three comma separated components of the position and the data units |
| State vector velocity | Enter three comma separated components of the velocity and the data units |
| Asset properties | Enter the object |
Asset properties
Enter the asset property values for accurate calculation of collision risk assessment and ephemeris propagation.
| Property | Units | Required |
|---|---|---|
| Mass | $kg$ | No |
| Hard Body Radius (HBR) | $m$ | Yes |
| 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