orbitalElements

R2026b

Orbital elements of satellites in scenario

collapse all in page

    Syntax

    elements = orbitalElements(sat)

    Description

    elements = orbitalElements(sat) returns the orbital elements of the specified satellite sat.

    example

    Examples

    collapse all

    Open Live Script

    Create a satellite scenario object.

    sc = satelliteScenario;

    Add a satellite to the scenario.

    tleFile = "eccentricOrbitSatellite.tle";
sat1 = satellite(sc,tleFile);

    Retrieve the orbital elements of sat1.

    elements1 = orbitalElements(sat1)
    elements1 = struct with fields:
                       MeanMotion: 0.0083
                     Eccentricity: 0.7415
                      Inclination: 60.0000
    RightAscensionOfAscendingNode: 30.0000
              ArgumentOfPeriapsis: 280
                      MeanAnomaly: 289.4697
                           Period: 43200
                            Epoch: 05-May-2020 13:51:55
                            BStar: 0

    Add a satellite from Keplerian elements to the scenario.

    semiMajorAxis = 6878137;                               % meters
eccentricity = 0;
inclination = 20;                                      % degrees
rightAscensionOfAscendingNode = 0;                     % degrees
argumentOfPeriapsis = 0;                               % degrees
trueAnomaly = 0;                                       % degrees
sat2 = satellite(sc,semiMajorAxis,eccentricity, ...
       inclination,rightAscensionOfAscendingNode, ...
       argumentOfPeriapsis,trueAnomaly, ...
       "OrbitPropagator","two-body-keplerian", ...
       "Name","Sat2");

    Retrieve the orbital elements of sat2.

    elements2 = orbitalElements(sat2)
    elements2 = struct with fields:
                    SemiMajorAxis: 6878137
                     Eccentricity: 0
                      Inclination: 20
    RightAscensionOfAscendingNode: 0
              ArgumentOfPeriapsis: 0
                      TrueAnomaly: 0
                           Period: 5.6770e+03

    Input Arguments

    collapse all

    Satellite object, specified as a scalar.

    Since R2026b

    Reference celestial body for orbital elements, specified as "Earth" or "Moon". The default value is the CentralBody property of the satellite. When ReferenceCelestialBody equals "Moon", the elements are computed using the gravitational parameter of the Moon.

    Dependencies

    When ReferenceCelestialBody equals "Moon", the OrbitPropagator property of the satellite must equal "two-body-keplerian", "ephemeris", or "numerical". Otherwise, the function returns an error.

    In addition, the Moon must have been added to the satellite scenario as a central body. Otherwise, the function returns an error.

    Data Types: string

    Output Arguments

    collapse all

    Orbital elements of the input sat, returned as a structure. The fields of the structure depend on the value of the OrbitPropagator property of the satelliteScenario object.

    For more information on orbital elements, see Orbital Elements.

    The orbital elements are defined in the International Celestial Reference Frame (ICRF).

    FieldDescription
    SemiMajorAxisSemimajor axis, in meters
    EccentricityEccentricity
    InclinationInclination angle, in degrees. The inclination is defined with respect to ICRF as the angle between the orbital plane and the ICRF xy plane.
    RightAscensionOfAscendingNodeRight ascension of Ascending node, in degrees
    ArgumentOfPeriapsisArgument of periapsis, in degrees
    TrueAnomalyTrue anomaly at reference time, in degrees
    PeriodOrbital period, in seconds. Returns Inf for parabolic and hyperbolic trajectories (eccentricity >= 1).

    Data Types: struct

    The orbital elements represent general perturbation mean elements.

    FieldDescription
    MeanMotionGeneral perturbation mean motion, in degrees per second
    EccentricityMean eccentricity
    InclinationMean inclination angle, in degrees
    RightAscensionOfAscendingNodeMean right ascension of Ascending node, in degrees
    ArgumentOfPeriapsisMean argument of periapsis, in degrees
    MeanAnomalyMean mean anomaly at the reference time, in degrees
    EpochEpoch
    BStarDrag term, in per EarthRadius
    PeriodMean orbital period, in seconds

    Data Types: struct

    FieldDescription
    EphemerisStartTimeEphemeris start time
    EphemerisStopTimeEphemeris stop time
    PositionTimeTablePosition timetable
    VelocityTimeTableVelocity timetable

    Data Types: struct

    The orbital elements are derived from the SEM almanac file or RINEX GPS navigation message, and defined in the Earth-Centered-Earth-Fixed (ECEF) frame.

    FieldDescription
    PRNPseudorandom noise number
    SatelliteHealthSatellite health
    GPSWeekNumberGPS week number, with time of ephemeris.
    GPSTimeOfApplicabilityTime of Applicability, in seconds
    SemiMajorAxisSemimajor axis, in meters
    EccentricityEccentricity
    InclinationInclination angle at reference time, in degrees
    GeographicLongitudeOfOrbitalPlaneLongitude of ascending node of orbit plane at weekly epoch, in degrees
    RateOfRightAscensionReference rate of right ascension, in degrees per second
    ArgumentOfPerigeeArgument of perigee, in degrees
    MeanAnomalyMean anomaly at the reference time, in degrees
    PeriodOrbital period, in seconds

    Data Types: struct

    The orbital elements are derived from the RINEX Galileo navigation message, and defined in the Earth-Centered-Earth-Fixed (ECEF) frame.

    FieldDescription
    SatelliteIDSatellite system number
    GALWeekNumberGAL week number
    TimeofEphemerisTime of ephemeris, in seconds
    SatelliteHealthSatellite health
    SemiMajorAxisSemimajor axis, in meters
    EccentricityEccentricity
    InclinationInclination angle at reference time, in degrees
    GeographicLongitudeOfOrbitalPlaneLongitude of ascending node of orbit plane at weekly epoch, in degrees
    RateOfRightAscensionReference rate of right ascension, in degrees per second
    ArgumentOfPerigeeArgument of perigee, in degrees
    MeanAnomalyMean anomaly at the reference time, in degrees
    PeriodOrbital period, in seconds

    Data Types: struct

    Data Types: struct

    Version History

    Introduced in R2021a

    expand all

    Version History

    Introduced in R2021a

    expand all

    See Also

    Objects

    Functions

    Topics