Orbits and Propagators - AGI

Diseño de Vehículos Espaciales 1DVE1‐T07‐51% NR loopdE = 1.0;E = M % first guess for Eiter = 0; % iteration counterwhile(dE > tol)iter = iter + 1;Eold = E;E = E + (M+e*sin(E) - E)/(1.0-e*cos(E));dE = abs(Eold-E);enditer >> 4E*180/pi >> 143.9 deg% from E to true anomaly:cE = cos(E);sE = sin(E);cth = (e-cE)/(e*cE-1.0);sth = sqrt(1.0-e*e)*sE/(1.0-e*cE);th = atan2(sth,cth)*180/pi % true anomaly (deg) >> 155.9 deg