Main Content

ommread

Read data from orbit mean-elements message (OMM) file

Since R2024a

collapse all in page

    Syntax

    ommStruct = ommread(ommFile)

    Description

    example

    ommStruct = ommread(ommFile) reads the data from an orbit mean-elements message (OMM) file, ommFile. The function outputs a vector of structures containing data from the input OMM file in tleStruct. You can then use the propagateOrbit function to calculate the position and velocity using ommStruct.

    If the OMM file contains multiple entries for the same catalog number, the function outputs only the data corresponding to the latest epoch, which is defined for each OMM set.

    Examples

    collapse all

    Read data from the OMM file 'eccentricOrbitSatellite.xml' and calculate the position and velocity of the satellite at 12:00:00 on May 10, 2020.

    Read the data from the OMM file 'eccentricOrbitSatellite.xml', which is on the MATLAB® path. The file is provided with Aerospace Toolbox.

    ommStruct = ommread('eccentricOrbitSatellite.xml')
    ommStruct = 
  struct with fields:

                             Name: "Satellite 41"
           SatelliteCatalogNumber: 20041
                            Epoch: 05-May-2020 13:51:55
                            BStar: 0
    RightAscensionOfAscendingNode: 30
                     Eccentricity: 0.7415
                      Inclination: 60
              ArgumentOfPeriapsis: 280
                      MeanAnomaly: 289.4697
                       MeanMotion: 0.0083

    Calculate the position and velocity corresponding to the input time using the OMM data defined in ommStruct.

    [r,v] = propagateOrbit(datetime(2020, 5, 10, 12, 0, 0),ommStruct);

    Input Arguments

    collapse all

    OMM file, specified as a character vector or a string scalar. The file must exist in the current folder or in a folder on the MATLAB path, or the argument must include a full or relative path to a file. You can then use the propagateOrbit function to calculate the position and velocity of one or more spacecraft over time using the orbits defined in ommStruct. This function supports the .xml and .json OMM file formats. For more information on OMM files, see Orbit Mean-Elements Message (OMM) File.

    Example: 'eccentricOrbitSatellite.xml'

    Data Types: char | string

    Output Arguments

    collapse all

    OMM structures extracted from ommFile, returned as a vector of structures. To calculate the position and velocity of one or more spacecraft over time using Orbit Mean-Elements Message (OMM) data, use this vector of structures as an input to the propagateOrbit function.

    For more information on OMM file structures, see Orbit Mean-Elements Message (OMM) File. If the OMM file contains multiple entries for the same catalog number, the function outputs only the data corresponding to the latest epoch, which is defined for each OMM set.

    Version History

    Introduced in R2024a

    See Also

    | |

    Topics