Hello everyone,
I have this MATLAB function satellit(t,x,model) provides the system of differential equations for the orbit elements x = (a e i O w M) of a satellite in an Earth orbit.
I have to write a function to compute the orbit of a satellite. In this function the user should provide model initial position x(0) and flight time tf. Finally I have to plot the satellite orbit in cartesian coordinates. However I'm struggling to do it. Could anyone help me ?
function dx = satellit(t,x,model)dx = zeros(6,1);a = x(1); % semi-major axis [km]
e = x(2); % eccentricity
i = x(3); % inclination [rad]
O = x(4); % longitude of the ascending node [rad]
w = x(5); % argument of periapsis [rad]
M = x(6); % mean anomaly [rad]
GM = 398600.4418; % graviational parameter in km^3/s^2
R = 6378.1370; % radius at equator in km
J2 = 0.0010826267d0; % Earth's J2 (WGS-84)
J3 = -0.0000025327d0; % Earth's J3 (WGS-84)
J4 = -0.0000016196d0; % Earth's J4 (WGS-84)
ac = a*a*a;n = sqrt(GM/ac);
Thanks in advance
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