Loading satellite TLE data into MATLAB using satellite function

Question

John Nolan 2024-7-18，17:55

0
链接

此问题的直接链接

https://ww2.mathworks.cn/matlabcentral/answers/2138556-loading-satellite-tle-data-into-matlab-using-satellite-function

移动：Sam Chak about 1 hour 前

Using TLE data from an online database, MATLAB throws the error "The specified initial conditions will cause the orbit of 'STARLINK-2438' to intersect the Earth's surface." when using this function:

clc
clearvars
close all
format long
G = 3.986004418e14;
% Create a satellite scenario and add ground stations from latitudes and longitudes.
startTime = datetime(2024,7,18,13,00,41);
stopTime = startTime + days(1);
sampleTime = 60*1;
sc = satelliteScenario(startTime,stopTime,sampleTime);
sat = satellite(sc,'test_tle.txt')

The TLE data in "test_tle.txt" is as follows:

STARLINK-2438

1 48103U 21027M 24199.52200852 .27610719 12343-4 29456-2 0 9995

2 48103 53.0228 234.3624 0004658 334.7729 174.1970 16.36724891183121

when manually importing the values into the function, I dont receive the error:

% Mean Motion Line2 Field 8
semiMajorAxis = (G)^(1/3)/((2*pi*(16.36724891183121)/86400)^(2/3)); % ref : https://space.stackexchange.com/questions/18289/how-to-get-semi-major-axis-from-tle
% Eccentricity Line2 Field 5
eccentricity = 0.0004658;
% Inclination Line2 Field 3
inclination = 53.0228;
% Right Ascension of the asending node Line2 Field 4
rightAscensionOfAscendingNode = 234.3624;
% Argument of perigee Line2 Field 6
argumentOfPeriapsis = 334.7729;
% Mean Anomaly Line2 Field 7
trueAnomaly = 174.1970;
sat = satellite(sc,semiMajorAxis,eccentricity,inclination, ...
    rightAscensionOfAscendingNode,argumentOfPeriapsis,trueAnomaly);

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sun about 5 hours 前

I have the same problem and I don't know if the blogger has already solved it?

John Nolan about 4 hours 前

The text files are taken directly from a online database. Whats strange is that only some of the satellites in the textfile trigger the error, not all of them do it.

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