Determine an interplanetary Mars$-$Earth mission that uses a heliocentric Hohmann transfer. Assume the planets are coplanar concentric orbits using Earth$-$Sun distance of $1$ AU and Mars$-$Sun distance of $1\mathrm{.}524$ AU$.$ Determine the following parameters:a$.$ Hyperbolic departure velocity V$+$ in km$/$secb$.$ Hyperbolic arrival velocity V$-$ in km$/$secc$.$ Hohmann transfer flight time in daysd. Phase angle at departure