The reason why you haven't found a method is because it doesn't make sense physically.
TLE are data format that condense information about a satellite, such as the epoch of launch, the catalogue number and other designators.
You also have properties depending on the effects of perturbations on the orbit (B*). In LEO, perturbations are mainly due to drag, which strictly depends on the satellite intrinsic properties, such as the area-to-mass ratio.
An other parameter included in TLEs is the number of revolutions that the satellite has performed since insertion into orbit.
All these features makes it impossibile to construct TLE that make sense for fictitious satellites that don't exist in reality.
If you really want to generate some TLE, you could extrapolate the orbital parameters from the simulations and fill in blank the other characteristic, but I am relatively sure you won't find a working function for that.
If you are okay with dealing with fake TLE, you can use the following to generate them.
Feel free to modify the parameters as you prefer.
% Constellation from openExample('aero/ModelGalileoConstellAsWalkerDeltaConstellExample'):
sc = satelliteScenario;
sat = walkerDelta(sc, 29599.8e3, 56, 24, 3, 1, ArgumentOfLatitude=15, Name="Galileo");
% Initialise:
N = length(sat);
TLE = cell(N,1);
% Loop over satellites to extract TLEs:
for j = 1 : N
TLE{j} = getTLE(sc.Satellites(j));
end
% Generate TLE from satellite:
function TLE = getTLE(satellite)
%% Line 1:
% ID:
ID = num2str(satellite.ID, '%05.f');
% Time:
now = datetime;
currentYear = year(now);
yearStart = [num2str(currentYear) '-01-01'];
yearDigits = yearStart(3:4);
currentEpoch = convertTo(now, 'epochtime', 'Epoch', yearStart) / 86400;
epoch = num2str(currentEpoch, '%012.08f');
% Rocket launch:
RocketLaunches2022 = 180;
launchNumber = num2str(round((RocketLaunches2022 * currentEpoch) / 360), '%03.f');
% Line 1:
lineData = ['1 ' ID 'S ' yearDigits launchNumber 'A ' yearDigits epoch ' +.00000000 +00000-0 +00000-0 0 000'];
firstLine = [lineData checksum(lineData)];
%% Line 2:
% Orbital data:
i = num2str(satellite.orbitalElements.Inclination, '%08.04f');
OM = num2str(satellite.orbitalElements.RightAscensionOfAscendingNode, '%08.04f');
e = num2str(satellite.orbitalElements.Eccentricity * 1e7, '%07.f');
om = num2str(satellite.orbitalElements.ArgumentOfPeriapsis, '%08.04f');
th = num2str(satellite.orbitalElements.TrueAnomaly, '%08.04f');
n = num2str(86400 / satellite.orbitalElements.Period, '%011.08f');
% Line 2:
lineData = ['2 ' ID ' ' i ' ' OM ' ' e ' ' om ' ' th ' ' n '00000'];
secondLine = [lineData checksum(lineData)];
TLE = [firstLine;secondLine];
end
% Compute checksum for last line digit:
function cs = checksum(line)
digits = strrep(line, '-', '1');
signs = {'+','A','S',' ','0','.'};
for j = 1 : length(signs)
digits = erase(digits, signs{j});
end
sum = 0;
for j = 1 : length(digits)
sum = sum + str2num(digits(j));
end
sum = num2str(sum);
cs = sum(end);
end
Result:
TLE{N/2 + 1}
ans =
2×69 char array
'1 00013S 23055A 23109.00000000 +.00000000 +00000-0 +00000-0 0 0007'
'2 00013 056.0000 120.0000 0000000 000.0000 210.0000 01.70478493000006'
