In this problem you are going to practice putting together simulations of spacecraft trajectories using \textbf{MATLAB} and the \texttt{ode45} function. Simulate and plot the trajectory of a 100 kg spacecraft around Earth in two dimensions in a frame fixed at the center of the Earth from the initial states below, which are given in a planetocentric frame (i.e., the frame's origin is at the center of mass of the planet). Simulate both cases until the spacecraft completes exactly one orbit around the Earth, which will require you to come up with an appropriate event condition for an \texttt{ode45} event function. In both cases, report results in the planetocentric frame. Assume that the mass of Earth is \( 5.972 \times 10^{24} \, \text{kg} \) and \( G = 6.674 \times 10^{-11} \, \text{m}^3/\text{kg} \, \text{s}^2 \). \medskip \textbf{Initial state 1:} \( x = 7000 \, \text{km}, \, y = 0 \, \text{km}, \, v_x = 0 \, \text{km/s}, \, v_y = 7.55 \, \text{km/s} \) \textbf{Initial state 2:} \( x = 7000 \, \text{km}, \, y = 0 \, \text{km}, \, v_x = 0 \, \text{km/s}, \, v_y = 10 \, \text{km/s} \) \medskip Visually analyze the trajectories for both initial