Perform the initial sizing of a rocket to carry a 10,000 kg payload to the Moon. The rocket will depart KSC and put the payload in a 2,000 m lunar equatorial orbit. Determine the parameters for your rocket such as, number of stages, total mass, propellant mass, engine & tank masses for each stage, burn time and mdot of each stage. For now, assume the stages to reach LEO have an Isp of 400 s and the stages to go from LEO to lunar orbit have an Isp of 350 s. I need a matlab or excel program to do the calculations. Preferably excel but matlab is fine if its easier for you. I also need the lamda and epsilon valuse for each stage.(Perform for 3 stages and 4 and compare results)