A $2000-$kg spacecraft is in a $480$ x $800$ km earth orbit as shown in the figure to the right.$$ Find:

a$)$The $$v required a perigee A to place the spacecraft in a $480$ x $16000$ km transfer ellipse $($orbit $2)$

b$)$The $$v $($apogee kick$)$ required at B of the transfer orbit to establish a $16,000$ km circular orbital altitude

c$)$The total required propellant if the specific impulse I$\_$sp is $300$ s

d$)$ computing the propellant mass if the transfer starts from apogee.

$[$ANS$.1298\mathrm{.}5$ kg$]$