01 Aspace shuttle type vehicle is used to launch a payload that includes a satellite into space. The first stage involves the core engines and the two solid rocket boosters propelling the spacecraft. At the end of the first stage, the solid rocket boosters are jettisoned. The second stage involves just the core engines propelling the spacecraft until burnont of the core engines. The masses, exhaust veloeities and burn times for each section of the lannch vehicle are included in the table below. External tank feeding core For each booster: Orbiter + Payload: engines: e = 721000 kg gy = 503500 kg g = 126000 kg My = 29900 kg Mgy = 86200 kg Covhe = 4460 m/s Coxhp = 2640 m/s by =480 % tpp=125% where my, is the mass of fuel in the core tank, m, is the mass of the core tank, , . is the effective exhaust gas velocity from the core engines, ty, - is the total burn time of the core engines, my, is the mass of fuel in one booster rocket, mgy, is the mass of one booster rocket's structure, C., ;, is the effective exhaust gas velocity from one booster rocket, , , is the total burn time of one booster rocket, and iy, is the mass of the orbiter and payload. a) Determine the mass flow rate of the exhaust gas from each booster rocket and from the core engines. h) Determine the mass of fuel burned by the core engines from the external tank at the point when the boosters have burned out. What fraction of the total amount of fuel is taken from the external tank by the time the solid rocket boosters have burned out. ) What is the fraction of the fuel left in the external tank at the point when the boosters have burned out and how much fuel is this in kilograms. d) How long will the core engine continue to burn fuel after the boosters have burned out. e) Find the average exhaust gas velocity for stage one. f) Find delta V for the first stage. g) Then, the two solid rocket boosters my, are jettisoned. Find delta V for the second stage. h) Find the delta V for the entire rocket. [ / 50)