please show how to input into matlab $(10$ pts$)$ Given a satellite in an elliptical Earth orbit, with an initial ${}_0=42$deg true anomaly, and an

initial position and velocity of:

$\frac{?}{\text{b}\text{a}\text{r}}(r{)}_0=\left[\begin{array}{ccc}-3640\mathrm{.}3744& -3460\mathrm{.}0807& 4967\mathrm{.}8191\end{array}\right]km\frac{?}{b}$

$ar(v{)}_0=\left[\begin{array}{ccc}5\mathrm{.}532131& -5\mathrm{.}144368& 0\mathrm{.}647898\end{array}\right]k\frac{m}{s}$

Compute the position $\frac{?}{\text{b}\text{a}\text{r}}(r)$ and velocity $\frac{?}{\text{b}\text{a}\text{r}}(v)$ at a delta true anomaly $=148$ later.

Solution:

$r=\left[\begin{array}{ccc}6109\mathrm{.}728809& 442\mathrm{.}971578& -4110\mathrm{.}590719\end{array}\right]km$

$v=\left[\begin{array}{ccc}-2\mathrm{.}588959& 6\mathrm{.}010448& -3\mathrm{.}142376\end{array}\right]k\frac{m}{s}$