An emergency supply ship is being sent from earth orbit around the sun (circular orbit around the sun with a radius of 1 AU) to Mars using a hyperbolic transfer orbit. The hyperbolic orbit has a periapsis radius R_p of 1 AU and hyperbolic excess energy of 300 km^2/s^2. Assume the ship has already escaped from earth.
The nuclear thermal rocket has a specific impulse of 900 s and thrust of 30000 N. The vehicle structural mass M_s is 1000 kg and payload mass M_L is 1000 kg.
a) sketch the orbit transfer, label 2 trajectories, noting location and direction of velocity change delta V
B) what is the delta v
C) what are the initial mass, burn out mass and propellant mass used.