1. The problem statement, all variables and given/known data Given: Initial orbital elements of a satellite a=6652.555663km; e=0.075; i=28.5 degrees; Ω=40 degrees; w=30 degrees; n=0 degrees; Tasks(using MATLAB): 1. Convert orbital elements to position and velocity vectors 2. Use these vectors to initialize the Runge-Kutta method 3. Set up the Runge Kutta method to integrate equations in vector-matrix form 4. Numerically integrate the equations of motion for 5400 seconds, in increments of 10 seconds. 5. Plot position and velocity of the satellite over the 5400 seconds. 2. Relevant equations r = √(x2+y2+z2) ¨r = −(µ/r3)r 3. The attempt at a solution I have calculated the starting position and velocity vectors in MATLAB which results in: v = -7.2785 2.1832 3.4483 r = 1.0e+03 * 2.3443 5.4969 1.4681 but I am not sure what I am supposed to use as my vector-matrix equations for the Runge-Kutta integration. I know the two body equation of motion(shown above) will be used in it's component forms, but I'm supposed to use state space or something? I have yet to take system dynamics and controls so this concept is completely foreign to me. Any help would be very much appreciated.