A 20000kg spacecraft carrying 17000kg of fuel starts at the surface pf the earth, (Mass=6*1024kg, radius of 6.3*10^6 m). The liquid oxygen and kerosene rocket provides an exhaust velocity of 3500m/s.
a.) How much high can the rocket go above the earth's surface?
b.)Once the rocket reaches a height of 500km, an explosive device blows its 500kg payload off and the spent rocket booster falls straight back to earth. What is the velocity of the payload?
c.)What will be the height of the stable orbit for the payload?
The Attempt at a Solution
Isp = Vexit/g0
Isp = Itotal/(mass propellant * g0)
delta V = Vexhaust* ln(m0/mf)
Plugging into the rocket equation, you get delta v = 6639 m/s. Isp = 356 seconds. I total = 59500000. I'm stuck here.