GET /udl/statevector/history
Changed onService operation to dynamically query historical data by a variety of query parameters not specified in this API documentation. See the queryhelp operation (/udl/<datatype>/queryhelp) for more details on valid/required query parameter information.
Request
- Base URLhttps://unifieddatalibrary.com
- URLhttps://unifieddatalibrary.com/udl/statevector/history
- Authnone declared
Query parameters
optional, fields for retrieval. When omitted, ALL fields are assumed. See the queryhelp operation (/udl/<datatype>/queryhelp) for more details on valid query fields that can be selected.
Time of validity for state vector in ISO 8601 UTC datetime format, with microsecond precision. (YYYY-MM-DDTHH:MM:SS.ssssssZ)
Response
OK
Unique identifier of the record, auto-generated by the system.
Classification marking of the data in IC/CAPCO Portion-marked format.
Time of validity for state vector in ISO 8601 UTC datetime format, with microsecond precision.
The pedigree of state vector, or methods used for its generation to include state update/orbit determination, propagation from another state, or a state from a calibration satellite (e.g. ORBIT_UPDATE, PROPAGATION, CALIBRATION, CONJUNCTION, FLIGHT_PLAN).
Unique identifier of the satellite on-orbit object, if correlated. For the public catalog, the idOnOrbit is typically the satellite number as a string, but may be a UUID for analyst or other unknown or untracked satellites.
Satellite/Catalog number of the target OnOrbit object.
Optional identifier provided by state vector source to indicate the target onorbit object of this state vector. This may be an internal identifier and not necessarily map to a valid satellite number.
Unique identifier of the OD solution record that produced this state vector. This ID can be used to obtain additional information on an OrbitDetermination object using the 'get by ID' operation (e.g. /udl/orbitdetermination/{id}). For example, the OrbitDetermination with idOrbitDetermination = abc would be queries as /udl/orbitdetermination/abc.
Time when message was generated in ISO 8601 UTC format with microsecond precision.
Boolean indicating this state vector was unable to be correlated to a known object. This flag should only be set to true by data providers after an attempt to correlate to an OnOrbit object was made and failed. If unable to correlate, the 'origObjectId' field may be populated with an internal data provider specific identifier.
Cartesian X position of the target, in kilometers, in the specified referenceFrame. If referenceFrame is null then J2K should be assumed.
Cartesian Y position of the target, in kilometers, in the specified referenceFrame. If referenceFrame is null then J2K should be assumed.
Cartesian Z position of the target, in kilometers, in the specified referenceFrame. If referenceFrame is null then J2K should be assumed.
Cartesian X velocity of target, in kilometers/second, in the specified referenceFrame. If referenceFrame is null then J2K should be assumed.
Cartesian Y velocity of target, in kilometers/second, in the specified referenceFrame. If referenceFrame is null then J2K should be assumed.
Cartesian Z velocity of target, in kilometers/second, in the specified referenceFrame. If referenceFrame is null then J2K should be assumed.
Cartesian X acceleration of target, in kilometers/second^2, in the specified referenceFrame. If referenceFrame is null then J2K should be assumed.
Cartesian Y acceleration of target, in kilometers/second^2, in the specified referenceFrame. If referenceFrame is null then J2K should be assumed.
Cartesian Z acceleration of target, in kilometers/second^2, in the specified referenceFrame. If referenceFrame is null then J2K should be assumed.
The reference frame of the cartesian orbital states. If the referenceFrame is null it is assumed to be J2000.
Covariance matrix, in kilometer and second based units, in the specified covReferenceFrame. If the covReferenceFrame is null it is assumed to be J2000. The array values (1-21) represent the lower triangular half of the position-velocity covariance matrix. The size of the covariance matrix is dynamic, depending on whether the covariance for position only or position & velocity. The covariance elements are position dependent within the array with values ordered as follows:
x y z x' y' z'
x 1
y 2 3
z 4 5 6
x' 7 8 9 10
y' 11 12 13 14 15
z' 16 17 18 19 20 21
The cov array should contain only the lower left triangle values from top left down to bottom right, in order.
If additional covariance terms are included for DRAG, SRP, and/or THRUST, the matrix can be extended with the following order of elements:
x y z x' y' z' DRG SRP THR
DRG 22 23 24 25 26 27 28
SRP 29 30 31 32 33 34 35 36
THR 37 38 39 40 41 42 43 44 45
The reference frame of the covariance matrix elements. If the covReferenceFrame is null it is assumed to be J2000.
The method used to generate the covariance during the orbit determination (OD) that produced the state vector, or whether an arbitrary, non-calculated default value was used (CALCULATED, DEFAULT).
The covariance matrix values represent the lower triangular half of the covariance matrix in terms of equinoctial elements. The size of the covariance matrix is dynamic. The values are outputted in order across each row, i.e.:
1 2 3 4 5
6 7 8 9 10
: : : : :
: : : : :
51 52 53 54 55
: : : : :
: : : : :
The ordering of values is as follows:
Af Ag L N Chi Psi B BDOT AGOM T C1 C2 ...
Af 1
Ag 2 3
L 4 5 6
N 7 8 9 10
Chi 11 12 13 14 15
Psi 16 17 18 19 20 21
B 22 23 24 25 26 27 28
BDOT 29 30 31 32 33 34 35 36
AGOM 37 38 39 40 41 42 43 44 45
T 46 47 48 49 50 51 52 53 54 55
C1 56 57 58 59 60 61 62 63 64 65 66
C2 67 68 69 70 71 72 73 74 75 76 77 78
:
:
where C1, C2, etc, are the "consider parameters" that may be added to the covariance matrix. The covariance matrix will be as large as the last element/model parameter needed. In other words, if the DC solved for all 6 elements plus AGOM, the covariance matrix will be 9x9 (and the rows for B and BDOT will be all zeros). If the covariance matrix is unavailable, the size will be set to 0x0, and no data will follow. The cov field should contain only the lower left triangle values from top left down to bottom right, in order.
Cartesian X position of the target, in kilometers, in the specified alt1ReferenceFrame. Alternate reference frames are optional and are intended to allow a data source to provide an equivalent vector in a different cartesian frame than the primary vector.
Cartesian Y position of the target, in kilometers, in the specified alt1ReferenceFrame. Alternate reference frames are optional and are intended to allow a data source to provide an equivalent vector in a different cartesian frame than the primary vector.
Cartesian Z position of the target, in kilometers, in the specified alt1ReferenceFrame. Alternate reference frames are optional and are intended to allow a data source to provide an equivalent vector in a different cartesian frame than the primary vector.
Cartesian X velocity of the target, in kilometers/second, in the specified alt1ReferenceFrame. Alternate reference frames are optional and are intended to allow a data source to provide an equivalent vector in a different cartesian frame than the primary vector.
Cartesian Y velocity of the target, in kilometers/second, in the specified alt1ReferenceFrame. Alternate reference frames are optional and are intended to allow a data source to provide an equivalent vector in a different cartesian frame than the primary vector.
Cartesian Z velocity of the target, in kilometers/second, in the specified alt1ReferenceFrame. Alternate reference frames are optional and are intended to allow a data source to provide an equivalent vector in a different cartesian frame than the primary vector.
The reference frame of the alternate1 (Alt1) cartesian orbital state.
Cartesian X position of the target, in kilometers, in the specified alt2ReferenceFrame. Alternate reference frames are optional and are intended to allow a data source to provide an equivalent vector in a different cartesian frame than the primary vector.
Cartesian Y position of the target, in kilometers, in the specified alt2ReferenceFrame. Alternate reference frames are optional and are intended to allow a data source to provide an equivalent vector in a different cartesian frame than the primary vector.
Cartesian Z position of the target, in kilometers, in the specified alt2ReferenceFrame. Alternate reference frames are optional and are intended to allow a data source to provide an equivalent vector in a different cartesian frame than the primary vector.
Cartesian X velocity of the target, in kilometers/second, in the specified alt2ReferenceFrame. Alternate reference frames are optional and are intended to allow a data source to provide an equivalent vector in a different cartesian frame than the primary vector.
Cartesian Y velocity of the target, in kilometers/second, in the specified alt2ReferenceFrame. Alternate reference frames are optional and are intended to allow a data source to provide an equivalent vector in a different cartesian frame than the primary vector.
Cartesian Z velocity of the target, in kilometers/second, in the specified alt2ReferenceFrame. Alternate reference frames are optional and are intended to allow a data source to provide an equivalent vector in a different cartesian frame than the primary vector.
The reference frame of the alternate2 (Alt2) cartesian orbital state.
One sigma position uncertainty, in kilometers.
One sigma velocity uncertainty, in kilometers/second.
The mass of the object, in kilograms.
The actual area of the object at it's largest cross-section, expressed in meters^2.
Area-to-mass ratio coefficient for solar radiation pressure.
Area-to-mass ratio coefficient for atmospheric ballistic drag (m2/kg).
The effective area of the object exposed to atmospheric drag, expressed in meters^2.
Epoch revolution number.
Geopotential model used for this vector (e.g. EGM-96, WGS-84, WGS-72, JGM-2, or GEM-T3), including mm degree zonals, nn degree/order tesserals. E.g. EGM-96 24Z,24T.
The Drag Model used for this vector (e.g. HARRIS-PRIESTER, JAC70, JBH09, MSIS90, NONE, etc.).
Boolean indicating use of lunar/solar perturbations for this vector.
Boolean indicating use of solar radiation pressure perturbations for this vector.
The effective area of the object exposed to solar radiation pressure, expressed in meters^2.
Boolean indicating use of solid earth tide perturbations for this vector.
Boolean indicating use of in-track thrust perturbations for this vector.
First derivative of drag/ballistic coefficient (m2/kg-s).
Model parameter value for energy dissipation rate (EDR) (w/kg).
Model parameter value for thrust acceleration (m/s2).
Model parameter value for center of mass offset (m).
The start of the time interval containing the time of the last accepted observation, in ISO 8601 UTC format with microsecond precision. For an exact observation time, the firstObTime and lastObTime are the same.
The end of the time interval containing the time of the last accepted observation, in ISO 8601 UTC format with microsecond precision. For an exact observation time, the firstObTime and lastObTime are the same.
The number of observations available for the OD of the object.
The number of observations accepted for the OD of the object.
The number of sensor tracks available for the OD of the object.
The number of sensor tracks accepted for the OD of the object.
The recommended OD time span calculated for the object, expressed in days.
The actual time span used for the OD of the object, expressed in days.
The percentage of residuals accepted in the OD of the object.
F10 (10.7 cm) solar flux value.
F10 (10.7 cm) solar flux 81-day average value.
Average solar flux geomagnetic index.
TAI (Temps Atomique International) minus UTC (Universal Time Coordinates) offset in seconds.
Universal Time-1 (UT1) minus UTC offset, in seconds.
Rate of change of UT1 (milliseconds/day) - first derivative of ut1Utc.
Polar Wander Motion X (arc seconds).
Polar Wander Motion Y (arc seconds).
Number of terms used in the IAU 1980 nutation model (4, 50, or 106).
Time of the next leap second after epoch in ISO 8601 UTC time. If the next leap second is not known, the time of the previous leap second is used.
Integrator Mode.
Type of partial derivatives used (ANALYTIC, FULL NUM, or FAST NUM).
Integrator step mode (AUTO, TIME, or S).
Boolean indicating use of fixed step size for this vector.
Initial step size selection (AUTO or MANUAL).
Initial integration step size (seconds).
Integrator error control.
Array containing the standard deviation of error in target object position, U, V and W direction respectively (km).
Array containing the standard deviation of error in target object velocity, U, V and W direction respectively (km/sec).
The Weighted Root Mean Squared (RMS) of the differential correction on the target object that produced this vector. WRMS is a quality indicator of the state vector update, with a value of 1.00 being optimal. WRMS applies to Batch Least Squares (BLS) processes.
Start time at which this state vector was the 'current' state vector for its satellite.
End time at which this state vector was no longer the 'current' state vector for its satellite.
Optional URI location in the document repository of the raw file parsed by the system to produce this record. To download the raw file, prepend https://udl-hostname/scs/download?id= to this value.
Source of the data.
Originating system or organization which produced the data, if different from the source. The origin may be different than the source if the source was a mediating system which forwarded the data on behalf of the origin system. If null, the source may be assumed to be the origin.
Indicator of whether the data is REAL, TEST, EXERCISE, or SIMULATED data:
REAL: Data collected or produced that pertains to real-world objects, events, and analysis.
TEST: Specific datasets used to evaluate compliance with specifications and requirements, and for validating technical, functional, and performance characteristics.
EXERCISE: Data pertaining to a government or military exercise. The data may include both real and simulated data.
SIMULATED: Synthetic data generated by a model to mimic real-world datasets.
Optional array of provider/source specific tags for this data, where each element is no longer than 32 characters, used for implementing data owner conditional access controls to restrict access to the data. Should be left null by data providers unless conditional access controls are coordinated with the UDL team.
Optional algorithm used to produce this record.
Optional array of UDL data (observation) UUIDs used to build this state vector. See the associated sourcedDataTypes array for the specific types of observations for the positionally corresponding UUIDs in this array (the two arrays must match in size).
Optional array of UDL observation data types used to build this state vector (e.g. EO, RADAR, RF, DOA). See the associated sourcedData array for the specific UUIDs of observations for the positionally corresponding data types in this array (the two arrays must match in size).
Time the row was created in the database, auto-populated by the system.
Application user who created the row in the database, auto-populated by the system.
Optional source-provided and searchable metadata or descriptor of the data.
Mission center or organization performing this vector creation.
Optional identifier to track a commercial or marketplace transaction executed to produce this data.
The originating source network on which this record was created, auto-populated by the system.
The source data library from which this record was received. This could be a remote or tactical UDL or another data library. If null, the record should be assumed to have originated from the primary Enterprise UDL.
Changes
- info
added the optional property
/to the response with the status
- info
- warning
added the new
ECR/ECEFenum value to the/response property for the response status
- warning
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