GET /udl/maneuver/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/maneuver/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.
Maneuver event start time in ISO 8601 UTC with microsecond precision. For maneuvers without start and end times, the start time is considered to be the maneuver event time. (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.
Satellite/Catalog number of the target on-orbit object.
The time that the report or alert of this maneuver was generated, in ISO 8601 UTC format.
Maneuver event start time in ISO 8601 UTC with microsecond precision. For maneuvers without start and end times, the start time is considered to be the maneuver event time.
Maneuver event end time in ISO 8601 UTC with microsecond precision.
The estimated total active burn time of a maneuver, in seconds. This includes the sum of all burns in numAccelPoints. Not to be confused with the total duration of the maneuver.
Maneuver orbit determination fit data end time in ISO 8601 UTC with microsecond precision.
Target maneuvering on-orbit object. 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.
Optional ID of the sensor that detected this maneuver (for example, if detected by passive RF anomalies).
Boolean indicating this maneuver 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 on-orbit object was made and failed. If unable to correlate, the 'origObjectId' field may be populated with an internal data provider specific identifier.
Uncertainty in the occurrence of this maneuver (0 - 1).
Optional purpose of the maneuver if known (e.g. North-South Station Keeping, East-West Station Keeping, Longitude Shift, Unknown).
Uncertainty in the characterization or purpose assessment of this maneuver (0 - 1).
Optional source-provided identifier for this maneuver event. In the case where multiple maneuver records are submitted for the same event, this field can be used to tie them together to the same event.
Identifier provided by source to indicate the target on-orbit object performing this maneuver. This may be an internal identifier and not necessarily a valid satellite number/ID.
Optional identifier provided by source to indicate the sensor identifier used to detect this event. This may be an internal identifier and not necessarily a valid sensor ID.
Status of this maneuver (CANCELLED, PLANNED, POSSIBLE, REDACTED, VERIFIED).
CANCELLED: A previously planned maneuver whose execution was cancelled.
PLANNED: A maneuver planned to take place at the eventStartTime.
POSSIBLE: A possible maneuver detected by observation of the spacecraft or by evaluation of the spacecraft orbit.
REDACTED: A redaction of a reported possible maneuver that has been determined to have not taken place after further observation/evaluation.
VERIFIED: A maneuver whose execution has been verified, either by the owner/operator or observation/evaluation.
Magnitude, in km, of the difference in the pre- and post-maneuver position vectors at the maneuver event time.
Magnitude, in km, of the difference in the pre- and post-maneuver position vectors in the direction of the pre-maneuver 'U' unit vector at the maneuver event time.
Magnitude, in km, of the difference in the pre- and post-maneuver position vectors in the direction of the pre-maneuver 'V' unit vector at the maneuver event time.
Magnitude, in km, of the difference in the pre- and post-maneuver position vectors in the direction of the pre-maneuver 'W' unit vector at the maneuver event time.
Magnitude, in km/sec, of the difference in the pre- and post-maneuver velocity vectors at the maneuver event time.
Magnitude, in km/sec, of the difference in the pre- and post-maneuver velocity vectors in the direction of the pre-maneuver 'U' unit vector at the maneuver event time.
Magnitude, in km/sec, of the difference in the pre- and post-maneuver velocity vectors in the direction of the pre-maneuver 'V' unit vector at the maneuver event time.
Magnitude, in km/sec, of the difference in the pre- and post-maneuver velocity vectors in the direction of the pre-maneuver 'W' unit vector at the maneuver event time.
Difference in mass before and after the maneuver, in kg.
Optional identifier of the element set for the pre-maneuver orbit.
Optional identifier of the state vector for the pre-maneuver trajectory of the spacecraft.
Pre-event X component of position in ECI space, in km.
Pre-event Y component of position in ECI space, in km.
Pre-event Z component of position in ECI space, in km.
Pre-event X component of velocity in ECI space, in km/sec.
Pre-event Y component of velocity in ECI space, in km/sec.
Pre-event Z component of velocity in ECI space, in km/sec.
Pre-event radiation pressure coefficient. The units of the radiation pressure coefficient vary depending on provider. Users should consult the data provider to verify the units of the radiation pressure coefficient.
Pre-event ballistic coefficient. The units of the ballistic coefficient vary depending on provider. Users should consult the data provider to verify the units of the ballistic coefficient.
Pre-event spacecraft apogee (measured from Earth center), in kilometers.
Pre-event spacecraft perigee (measured from Earth center), in kilometers.
Pre-event spacecraft orbital inclination, in degrees. 0-180.
Pre-event spacecraft eccentricity.
Pre-event spacecraft orbital period, in minutes.
Pre-event spacecraft Right Ascension of the Ascending Node (RAAN), in degrees.
Pre-event spacecraft orbital Semi-Major Axis (SMA), in kilometers.
Pre-event spacecraft WGS-84 GEO belt longitude, represented as -180 to 180 degrees (negative values west of Prime Meridian).
Pre-event GEO drift rate of the spacecraft, in degrees per day. Negative values indicate westward drift.
Pre-event standard deviation, in kilometers, of spacecraft position in the 'U' unit vector direction.
Pre-event standard deviation, in kilometers, of spacecraft position in the 'V' unit vector direction.
Pre-event standard deviation, in kilometers, of spacecraft position in the 'W' unit vector direction.
Optional identifier of the element set for the post-maneuver orbit.
Optional identifier of the state vector for the post-maneuver trajectory of the spacecraft.
Post-event X component of position in ECI space, in km.
Post-event Y component of position in ECI space, in km.
Post-event Z component of position in ECI space, in km.
Post-event X component of velocity in ECI space, in km/sec.
Post-event Y component of velocity in ECI space, in km/sec.
Post-event Z component of velocity in ECI space, in km/sec.
Post-event radiation pressure coefficient. The units of the radiation pressure coefficient vary depending on provider. Users should consult the data provider to verify the units of the radiation pressure coefficient.
Post-event ballistic coefficient. The units of the ballistic coefficient vary depending on provider. Users should consult the data provider to verify the units of the ballistic coefficient.
Post-event spacecraft apogee (measured from Earth center), in kilometers.
Post-event spacecraft perigee (measured from Earth center), in kilometers.
Post-event spacecraft orbital inclination, in degrees. 0-180.
Post-event spacecraft eccentricity.
Post-event spacecraft orbital period, in minutes.
Post-event spacecraft Right Ascension of the Ascending Node (RAAN), in degrees.
Post-event spacecraft Semi-Major Axis (SMA), in kilometers.
Post-event spacecraft WGS-84 GEO belt longitude, represented as -180 to 180 degrees (negative values west of Prime Meridian).
Post-event GEO drift rate of the spacecraft, in degrees per day. Negative values indicate westward drift.
Post-event standard deviation, in kilometers, of spacecraft position in the 'U' unit vector direction.
Post-event standard deviation, in kilometers, of spacecraft position in the 'V' unit vector direction.
Post-event standard deviation, in kilometers, of spacecraft position in the 'W' unit vector direction.
Optional maneuver cross-track/radial/in-track covariance array, in meter and second based units, in the following order: CR_R, CI_R, CI_I, CC_R, CC_I, CC_C, CT_R, CT_I, CT_C, CT_T.
Estimated mass of the object following the maneuver, in kg.
Estimated area of the object following the maneuver, in meters squared.
Number of observations used to generate the maneuver data.
Description and notes of the maneuver.
Optional source-provided and searchable metadata or descriptor of the data.
Name of the state model used to generate the maneuver data.
Version of the state model used to generate the maneuver data.
The total number of estimated acceleration points during the maneuver.
Array of elapsed times, in seconds from maneuver start time, at which each acceleration point is estimated. Number of elements must match the numAccelPoints.
Array of estimated acceleration values, in meters per second squared. Number of elements must match the numAccelPoints.
Array of the 1-sigma uncertainties in estimated accelerations, in meters per second squared. Number of elements must match the numAccelPoints.
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.
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 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 (elsets, state vectors, etc) UUIDs used to build this maneuver. See the associated sourcedDataTypes array for the specific types of data for the positionally corresponding UUIDs in this array (the two arrays must match in size).
Optional array of UDL data types used to build this maneuver (e.g. EO, RADAR, RF, DOA, ELSET, SV). See the associated sourcedData array for the specific UUIDs of data for the positionally corresponding data types in this array (the two arrays must match in size).
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.
Changes
- info
added the optional property
//to the response with the status - 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
added the new
ECR/ECEFenum value to the//response property for the response status
- warning
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