orbitalElements
Description
Examples
Retrieve Orbital Elements of Satellite
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
sat
— Satellite
scalar
Satellite object, specified as a scalar.
Output Arguments
elements
— Orbital elements
structure
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.
Two-Body Keplerian
— Two-Body Keplerian orbit propagator fields
structure
The orbital elements are defined in the Geocentric Celestial Reference Frame (GCRF).
Field | Description |
---|---|
SemiMajorAxis | Semimajor axis, in meters |
Eccentricity | Eccentricity |
Inclination | Inclination angle, in degrees |
RightAscensionOfAscendingNode | Right ascension of Ascending node, in degrees |
ArgumentOfPeriapsis | Argument of periapsis, in degrees |
TrueAnomaly | True anomaly at reference time, in degrees |
Period | Orbital period, in seconds |
Data Types: struct
SGP4 and SDP4
— SGP4 and SDP4 orbit propagator fields
structure
The orbital elements represent general perturbation mean elements.
Field | Description |
---|---|
MeanMotion | General perturbation mean motion, in degrees per second |
Eccentricity | Mean eccentricity |
Inclination | Mean inclination angle, in degrees |
RightAscensionOfAscendingNode | Mean right ascension of Ascending node, in degrees |
ArgumentOfPeriapsis | Mean argument of periapsis, in degrees |
MeanAnomaly | Mean mean anomaly at the reference time, in degrees |
Epoch | Epoch |
BStar | Drag term, in per EarthRadius |
Period | Mean orbital period, in seconds |
Data Types: struct
Ephemeris
— Ephemeris orbit propagator fields
structure
Field | Description |
---|---|
EphemerisStartTime | Ephemeris start time |
EphemerisStopTime | Ephemeris stop time |
PositionTimeTable | Position timetable |
VelocityTimeTable | Velocity timetable |
Data Types: struct
GPS
— GPS orbit propagator fields
structure
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.
Field | Description |
---|---|
PRN | Pseudorandom noise number |
SatelliteHealth | Satellite health |
GPSWeekNumber | GPS week number, with time of ephemeris. |
GPSTimeOfApplicability | Time of Applicability, in seconds |
SemiMajorAxis | Semimajor axis, in meters |
Eccentricity | Eccentricity |
Inclination | Inclination angle at reference time, in degrees |
GeographicLongitudeOfOrbitalPlane | Longitude of ascending node of orbit plane at weekly epoch, in degrees |
RateOfRightAscension | Reference rate of right ascension, in degrees per second |
ArgumentOfPerigee | Argument of perigee, in degrees |
MeanAnomaly | Mean anomaly at the reference time, in degrees |
Period | Orbital period, in seconds |
Data Types: struct
Galileo
— Galileo orbit propagator fields
structure
The orbital elements are derived from the RINEX Galileo navigation message, and defined in the Earth-Centered-Earth-Fixed (ECEF) frame.
Field | Description |
---|---|
SatelliteID | Satellite system number |
GALWeekNumber | GAL week number |
TimeofEphemeris | Time of ephemeris, in seconds |
SatelliteHealth | Satellite health |
SemiMajorAxis | Semimajor axis, in meters |
Eccentricity | Eccentricity |
Inclination | Inclination angle at reference time, in degrees |
GeographicLongitudeOfOrbitalPlane | Longitude of ascending node of orbit plane at weekly epoch, in degrees |
RateOfRightAscension | Reference rate of right ascension, in degrees per second |
ArgumentOfPerigee | Argument of perigee, in degrees |
MeanAnomaly | Mean anomaly at the reference time, in degrees |
Period | Orbital period, in seconds |
Data Types: struct
Data Types: struct
Version History
Introduced in R2021a
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