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Orbit Extrapolation API (1.3.1)

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License: Exotrail

Orbit Extrapolation API

TLE extrapolation

Extrapolate a TLE using simplified perturbations models (sgp4/sdp4). Detected events and so-called ephemeris e.g. orbital elements over time can be outputted

Authorizations:
BearerAuth
Request Body schema: application/json
targetDate
required
string <date-time>

timescale UTC

required
object (TLE)

NORAD two-line element set

object (OrbitalEventRequest)

Select several orbital events that can be logged during the extrapolation

object (StationEventRequest)

Log passes over a set of ground stations

object (MeanOrbitEphemerisRequest)

Options for exporting mean orbital elements in an inertial frame. Note that the export frame can be defined from the configuration context

object (OsculatingOrbitEphemerisRequest)

Options for exporting osculating orbital elements in an inertial frame. Note that the export frame can be defined from the configuration context

object (PositionVelocityEphemerisRequest)

Options for exporting position velocity ephemeris in an inertial or non inertial frame

object (GeodeticEphemerisRequest)

Options for exporting the geodetic coordinates of the sub-satellite point as a function of time

object (ReferenceFramesConfiguration)

Configuration of reference frames and model options that are used throughout the simulation

Responses

Request samples

Content type
application/json
{
  • "targetDate": "2024-01-01T00:00:00Z",
  • "tle": {
    },
  • "orbitalEventsRequest": {
    },
  • "stationEventRequest": {
    },
  • "meanOrbitEphemerisRequest": {
    },
  • "osculatingOrbitEphemerisRequest": {
    },
  • "positionVelocityEphemerisRequest": {
    },
  • "geodeticEphemerisRequest": {
    },
  • "referenceFramesConfiguration": {
    }
}

Response samples

Content type
application/json
{
  • "osculatingOrbitEphemeris": {
    },
  • "meanOrbitEphemeris": {
    },
  • "geodeticEphemeris": {
    },
  • "positionVelocityEphemeris": {
    },
  • "orbitalEventLogs": [
    ],
  • "stationEventLogs": [
    ],
  • "fieldOfViewEventLogs": [
    ],
  • "closestApproachEventLogs": [
    ]
}

Numerical extrapolation

Special perturbation extrapolation. The initial orbital condition is propagated with a full numerical framework i.e. integrator and force models, which can be tuned to achieve high fidelity. Detected events and so-called ephemeris e.g. orbital elements over time can be outputted

Authorizations:
BearerAuth
Request Body schema: application/json
targetDate
required
string <date-time>

timescale UTC

required
object (Orbit)

Orbit representation by either parameters (Cartesian coordinates or orbital elements) or a TLE

object (OrbitalCovarianceMatrix)

Covariance matrix expressed either in terms of position and velocity or orbital elements

object (AttitudeSequence)

Sequence of attitude laws

object (SpaceObject)

An orbiting body

object (BatteryModel)

Battery model

object (ReferenceFramesConfiguration)

Configuration of reference frames and model options that are used throughout the simulation

object (PerturbationsConfiguration)

Perturbation force models configuration

object (ManeuverSchedule)

Time schedule for propulsion maneuvers

required
object (IntegratorConfiguration)

Configuration for variable- and fixed-step integrators

Array of objects (EventGenerationRequest)
Array of objects (EphemerisGenerationRequest)
object

References to the data to be used during the computation

Responses

Request samples

Content type
application/json
{
  • "targetDate": "2024-01-01T00:00:00Z",
  • "initialOrbit": {
    },
  • "initialCovarianceMatrix": {
    },
  • "attitudeSequence": {
    },
  • "spaceObject": {
    },
  • "batteryModel": {
    },
  • "referenceFramesConfiguration": {
    },
  • "perturbationsConfiguration": {
    },
  • "maneuverSchedule": {
    },
  • "integratorConfiguration": {
    },
  • "eventGenerationRequests": [
    ],
  • "ephemerisGenerationRequests": [
    ],
  • "data": {
    }
}

Response samples

Content type
application/json
{
  • "attitudeEphemeris": {
    },
  • "batteryPowerEphemeris": {
    },
  • "thrustVectorEphemeris": {
    },
  • "massEphemeris": {
    },
  • "osculatingOrbitEphemeris": {
    },
  • "meanOrbitEphemeris": {
    },
  • "geodeticEphemeris": {
    },
  • "positionVelocityEphemeris": {
    },
  • "cartesianCovarianceEphemeris": {
    },
  • "orbitalCovarianceEphemeris": {
    },
  • "orbitalEventLogs": [
    ],
  • "stationEventLogs": [
    ],
  • "fieldOfViewEventLogs": [
    ],
  • "closestApproachEventLogs": [
    ],
  • "data": {
    }
}