2. determine the following orbital parameters associated with a spacecraft in various orbits around the sun:
a) velocity of a spacecraft in circular orbit around the sun at the mean radius of jupiter measured from the sun,
b) minimum velocity change required to modify the trajectory of the spacecraft in question 2a to an elliptical trajectory that has a perihelion (at the mean radius of earth from the sun (i. e., 1 au),
c) time required to transit from jupiter to earth along the trajectory in question 2b,
d) velocity change required at perihelion to circularize the orbit around the sun at the mean radius of earth.