new .slx with a preload script and TLE

InitialiseJ2.m

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+%Initialise J2
+
+clc
+clear
+
+mu    = 398600.4415;          % Earth’s gravitational parameter [km^3/s^2]
+R_earth = 6378.137 ;          % Earth radius [km]
+J2 = 0.0010836;
+we = 360*(1 + 1/365.25)/(3600*24);      % Earth's rotation [deg/s]
+fname = 'STUDSAT2like.txt';    % TLE file name
+% Open the TLE file and read TLE elements
+fid = fopen(fname, 'rb');
+while ~feof(fid)
+% Reading TLE File
+L1 = fscanf(fid,'%23c%*s',1);
+L2 = fscanf(fid,'%d%6d%*c%5d%*3c%*2f%f%f%5d%*c%*d%5d%*c%*d%d%5d',[1,9]);
+L3 = fscanf(fid,'%d%6d%f%f%f%f%f%f%f%f',[1,9]);
+epoch       = L2(1,4)*24*3600;        % Epoch Date and Julian Date Fraction
+Db          = L2(1,5);                % Ballistic Coefficient
+i           = L3(1,3);                % Inclination [deg]
+RAAN        = L3(1,4);        % Right Ascension of the Ascending Node [deg]
+e           = L3(1,5)/1e7;            % Eccentricity
+omega       = L3(1,6);                % Argument of periapsis [deg]
+M           = L3(1,7);                % Mean anomaly [deg]
+n           = L3(1,8);                % Mean motion [Revs/day]
+% Orbital parametres
+a = (mu/(n*2*pi/(24*3600))^2)^(1/3);         % Semi-major axis [km]
+% T=3600*24;
+T = 2*pi*sqrt(a^3/mu);                    % Period in [min]
+rp = a*(1-e);
+h = (mu*rp*(1 + e))^0.5;                     % Angular momentum
+E = keplerEq(M*pi/180,e,eps);
+theta =  acos((cos(E) -e)/(1 - e*cos(E)))*180/pi;    % [deg] True anomaly
+
+E = 2*atan(tand(theta/2)*((1-e)/(1+e))^0.5);
+M = E  - e*sin(E);
+t0 = M/(2*pi)*T;
+end

STUDSAT2like.txt

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+STUDSAT2 LIKE              
+1 99999U          17212.27083333 -.00000681  00000-0 -73551-4 0 00002
+2 99999 097.7872 145.0781 0010609 271.6166 088.3814 14.88384880000013

keplerEq.m

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+function E = keplerEq(M,e,eps)
+En  = M;
+Ens = En - (En-e*sin(En)- M)/(1 - e*cos(En));
+while ( abs(Ens-En) > eps )
+    En = Ens;
+    Ens = En - (En - e*sin(En) - M)/(1 - e*cos(En));
+end;
+E = Ens;
+end