Question Completion Status:

Find the total velocity increment required for Hohmann transfer between orbit A and B through a transfer elliptical orbit, where orbit A radius is $6,567km$ and orbit $B$ radius is $72,160km.$ Gravitational constant G is $6\mathrm{.}67430{10}^{-11}{m}^{3}k{g}^{-1}{s}^{-2},$ Mass of Earth is $5\mathrm{.}972{10}^{24}kg,$ and the standard gravitational parameter, $)=(GM$ is $3\mathrm{.}986{10}^{14}\frac{m^3}{s^2}.$

$1+$ecos$$

$At$ Perigee : $r=a(1-e)$

$At$ Apogee: $r=a(1+e)$

$,u_{\text{e}\text{l}\text{l}\text{i}\text{p}}=\sqrt[\phantom{2}]{(\frac{2}{r}-\frac{1}{a})}$

$u_{\text{p}\text{e}\text{r}\text{i}\text{g}\text{e}\text{e}}=\sqrt[\phantom{2}]{\frac{2}{r_a+r_p}*\frac{r_a}{r_p}}=\sqrt[\phantom{2}]{\frac{}{a}*\frac{1+e}{1-e}}$

$u_{\text{a}\text{p}\text{o}\text{g}\text{e}\text{e}}=\sqrt[\phantom{2}]{\frac{2}{r_a+r_p}*\frac{r_p}{r_a}}=\sqrt[\phantom{2}]{\frac{}{a}*\frac{1-e}{1+e}}$

Period of an orbit $[$time$]$

$P=2\sqrt[\phantom{2}]{\frac{a^2}{}},$ where $=GM$ and $a$ : length of semi$-$major axis

Circular Orbit

$u_{\text{c}\text{i}\text{r}\text{c}\text{u}}=\sqrt[\phantom{2}]{\frac{}{r}},$ where $=GM$