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tleread

Read data from two-line element (TLE) file

Since R2023b

    Description

    example

    tleStruct = tleread(tleFile) reads the data from a two-line element (TLE) file, tleFile. The function outputs a vector of structures containing data from the input TLE file in tleStruct. You can then use the propagateOrbit function to calculate the position and velocity using tleStruct.

    If the TLE file contains multiple entries for the same catalog number, the function outputs only the data corresponding to the latest epoch (defined for each TLE set).

    Examples

    collapse all

    Read data from the TLE file, 'leoSatelliteConstellation.tle', and calculate the position and velocity from the TLE structure file, tleStruct.

    Read the data from the TLE file 'leoSatelliteConstellation.tle', which is on the MATLAB® path and provided with Aerospace Toolbox.

    tleStruct = tleread('leoSatelliteConstellation.tle')
    tleStruct = 
      40×1 struct array with fields:
        Name
        SatelliteCatalogNumber
        Epoch
        BStar
        RightAscensionOfAscendingNode
        Eccentricity
        Inclination
        ArgumentOfPeriapsis
        MeanAnomaly
        MeanMotion

    Calculate the position and velocity corresponding to the input time using the TLE data defined in tleStruct.

    [r,v] = propagateOrbit(datetime(2022, 1, 3, 12, 0, 0),tleStruct)
    r(:,:,1) =
       1.0e+06 *
       -4.3726
        1.2106
       -5.6292
    r(:,:,2) =
       1.0e+06 *
        2.8278
        3.3101
        5.7417
    r(:,:,3) =
       1.0e+06 *
       -1.6252
        6.4804
        2.7661
    r(:,:,4) =
       1.0e+06 *
       -6.4733
        3.1872
       -0.4959
    r(:,:,5) =
       1.0e+06 *
       -6.5300
       -1.8740
       -2.5197
    r(:,:,6) =
       1.0e+06 *
        4.2696
       -2.9549
        5.0050
    r(:,:,7) =
       1.0e+06 *
       -4.3207
       -0.2621
       -5.8029
    r(:,:,8) =
       1.0e+06 *
       -0.4354
        6.3188
        3.5007
    r(:,:,9) =
       1.0e+06 *
        3.1625
       -4.6176
       -4.5565
    r(:,:,10) =
       1.0e+06 *
       -6.4680
       -0.5957
       -3.1486
    r(:,:,11) =
       1.0e+06 *
       -5.0509
       -4.3876
       -2.7586
    r(:,:,12) =
       1.0e+06 *
       -4.5717
        4.3305
        3.5445
    r(:,:,13) =
       1.0e+06 *
       -4.8265
        0.2134
        5.3573
    r(:,:,14) =
       1.0e+06 *
        3.3022
       -3.9510
       -5.0798
    r(:,:,15) =
       1.0e+06 *
       -6.4064
       -2.3789
       -2.3156
    r(:,:,16) =
       1.0e+06 *
        4.9215
       -1.5755
       -5.0658
    r(:,:,17) =
       1.0e+06 *
       -4.2865
        0.5024
        5.7884
    r(:,:,18) =
       1.0e+06 *
       -4.1508
       -5.3584
       -2.5396
    r(:,:,19) =
       1.0e+06 *
        0.8586
       -4.2505
       -5.8000
    r(:,:,20) =
       1.0e+06 *
        1.6331
       -3.9315
       -5.8582
    r(:,:,21) =
       1.0e+06 *
       -3.4834
       -2.7205
        5.7141
    r(:,:,22) =
       1.0e+06 *
       -0.3378
       -5.8660
        4.1801
    r(:,:,23) =
       1.0e+06 *
       -2.3699
       -5.9500
       -3.3499
    r(:,:,24) =
       1.0e+06 *
       -3.5223
       -3.3199
        5.3567
    r(:,:,25) =
       1.0e+06 *
        5.8316
       -2.5668
       -3.4419
    r(:,:,26) =
       1.0e+06 *
        0.5307
       -4.0214
        5.9809
    r(:,:,27) =
       1.0e+06 *
       -2.5070
       -3.5297
        5.7770
    r(:,:,28) =
       1.0e+06 *
        5.2806
       -1.5994
       -4.6575
    r(:,:,29) =
       1.0e+06 *
       -6.7516
       -2.5075
        0.5515
    r(:,:,30) =
       1.0e+06 *
       -4.7709
        2.9142
       -4.5849
    r(:,:,31) =
       1.0e+06 *
       -3.5965
        2.7142
       -5.6577
    r(:,:,32) =
       1.0e+06 *
       -3.5367
       -2.2889
        5.8683
    r(:,:,33) =
       1.0e+06 *
       -7.2201
        0.2849
        0.1373
    r(:,:,34) =
       1.0e+06 *
       -4.9627
       -1.2222
       -5.1376
    r(:,:,35) =
       1.0e+06 *
        0.6899
       -4.5016
        5.5907
    r(:,:,36) =
       1.0e+06 *
        4.0468
        2.2131
       -5.5739
    r(:,:,37) =
       1.0e+06 *
       -5.3549
       -4.8576
       -0.1584
    r(:,:,38) =
       1.0e+06 *
        6.0404
       -1.8887
        3.4976
    r(:,:,39) =
       1.0e+06 *
        5.4127
        1.6086
        4.5006
    r(:,:,40) =
       1.0e+06 *
       -6.4090
        1.6928
       -2.9143
    v(:,:,1) =
       1.0e+03 *
        0.4943
       -7.1498
       -1.9149
    v(:,:,2) =
       1.0e+03 *
       -4.0192
        6.0766
       -1.5144
    v(:,:,3) =
       1.0e+03 *
       -4.9766
        1.0605
       -5.4091
    v(:,:,4) =
       1.0e+03 *
       -1.4616
       -3.9252
       -6.1322
    v(:,:,5) =
       1.0e+03 *
        3.2088
       -3.7044
       -5.5631
    v(:,:,6) =
       1.0e+03 *
        0.9341
        6.6797
        3.1401
    v(:,:,7) =
       1.0e+03 *
        1.8369
       -7.1027
       -1.0508
    v(:,:,8) =
       1.0e+03 *
       -5.0858
        2.3556
       -4.8638
    v(:,:,9) =
       1.0e+03 *
        6.3179
        0.5077
        3.8802
    v(:,:,10) =
       1.0e+03 *
        2.9293
       -4.4690
       -5.1661
    v(:,:,11) =
       1.0e+03 *
        4.6556
       -1.9379
       -5.4413
    v(:,:,12) =
       1.0e+03 *
       -5.3740
       -1.6816
       -4.8478
    v(:,:,13) =
       1.0e+03 *
       -3.2646
       -6.1068
       -2.7019
    v(:,:,14) =
       1.0e+03 *
        6.5709
        1.5692
        3.0633
    v(:,:,15) =
       1.0e+03 *
        3.3442
       -3.5794
       -5.5948
    v(:,:,16) =
       1.0e+03 *
        4.7665
        4.7091
        3.1755
    v(:,:,17) =
       1.0e+03 *
       -2.5062
       -6.8824
       -1.2637
    v(:,:,18) =
       1.0e+03 *
        4.8713
       -1.1945
       -5.4657
    v(:,:,19) =
       1.0e+03 *
        6.7905
        2.7845
       -1.0447
    v(:,:,20) =
       1.0e+03 *
        6.4822
        3.5498
       -0.5660
    v(:,:,21) =
       1.0e+03 *
        2.5726
       -6.7711
       -1.6434
    v(:,:,22) =
       1.0e+03 *
        4.9552
       -3.4072
       -4.3792
    v(:,:,23) =
       1.0e+03 *
        5.5151
        0.5805
       -4.9428
    v(:,:,24) =
       1.0e+03 *
        2.2327
       -6.5935
       -2.6017
    v(:,:,25) =
       1.0e+03 *
       -0.5055
        5.4920
       -4.9559
    v(:,:,26) =
       1.0e+03 *
        7.3355
        1.1602
        0.1376
    v(:,:,27) =
       1.0e+03 *
        6.8592
       -2.4664
        1.4629
    v(:,:,28) =
       1.0e+03 *
       -1.4396
        6.2341
       -3.7779
    v(:,:,29) =
       1.0e+03 *
        1.8985
       -3.7666
        6.1154
    v(:,:,30) =
       1.0e+03 *
       -5.5694
       -3.0137
        3.8774
    v(:,:,31) =
       1.0e+03 *
       -6.0027
       -3.8907
        1.9583
    v(:,:,32) =
       1.0e+03 *
        4.3350
       -6.0269
        0.2515
    v(:,:,33) =
       1.0e+03 *
       -0.0514
       -4.3235
        6.0454
    v(:,:,34) =
       1.0e+03 *
       -1.5791
       -6.5457
        3.0929
    v(:,:,35) =
       1.0e+03 *
        7.1302
       -1.1357
       -1.7937
    v(:,:,36) =
       1.0e+03 *
       -5.2628
        4.8689
       -1.8870
    v(:,:,37) =
       1.0e+03 *
        2.8075
       -3.2824
        6.0458
    v(:,:,38) =
       1.0e+03 *
        4.0290
        3.9657
       -4.8152
    v(:,:,39) =
       1.0e+03 *
        1.4390
        6.1548
       -3.9152
    v(:,:,40) =
       1.0e+03 *
       -3.4278
       -4.0127
        5.2093

    Input Arguments

    collapse all

    TLE 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. For more information on TLE files, see Two Line Element (TLE) Files.

    Example: 'leoSatelliteConstellation.tle'

    Data Types: char | string

    Output Arguments

    collapse all

    TLE structures extracted from tleFile, returned as a vector of structs. To calculate the position and velocity using two-line-element (TLE) data, use this file as input to the propagateOrbit function. For more information on TLE-file structures, see Two Line Element (TLE) Files.

    Version History

    Introduced in R2023b