Problem $4$

Determine an interplanetary Mars $-$ Earth return mission that uses a heliocentric Hohmann transfer. Assume coplanar concentric planetary orbits. Determine the following parameters:

Mars semi major axis is $1\mathrm{.}52368$ AU

a$)$ Hyperbolic departure velocity, $v_{}^{+}$in $k\frac{m}{s}$

b$)$ Hyperbolic arrival velocity, $v_{}-$ in km$/$s

c$)$ Hohmann$-$transfer flight time in days

d$)$ Phase angle at departure