Write a MatLab code to plot the trajectory of a satellite orbiting the Moon using the Euler's time stepping method. You may assume that all orbits are coplanar and that the Earth is a stationary reference frame. For the initial condition, assume that all orbiting bodies are lined up along the x-axis with the satellite furthest from the Earth. In addition, use the semimajor axis values for an initial circular orbital velocities moving in counter-clockwise orbit. Set the time step increment to be 1/50000th of the initial orbital period of the satellite around the moon (TP0 ). (Hint: Separately keep track of the Moon and Satellite in the ECI frame) a. Plot the trajectory of the Satellite with an initial lunar altitude of 500 km in ECI coordinate for a period of 5 days. b. Now, with the satellite at an initial lunar altitude of 15000 km, plot the trajectory of the Satellite relative to the moon for a period of 5 days. Compare your results to the twobody approximation.