Using MATLAB, generate values of r, by varying the true anomaly, and plot them (on the Cartesian, XY, plane) to generate orbits for the following conditions:

a = 7000 km, and e = 0 a = 7000 km, and e = 0.5 a = 10000 km, and e = 0.1 a = 15000 km, and e = 0.9 (The eccentricity e, & the semi-major axis, a (km))

Plot all four orbits on the same graph.