Consider an elliptical orbit with the orbit period equal one half of

a sidereal day and eccentricity perigee altitude $h_p=1600km.$

$($This is a $12-$hr Molniya orbit.$)$

Calculate the angle $($figure$)$ from the orbit apogee to a point

where the satellite is $t_a=1\mathrm{.}6hr$ before reaching the apogee in

its orbital motion.

Calculate

a$)$ satellite mean motion, $n$

b$)$ satellite mean anomaly, $M,$ in the point of interest

c$)$ satellite eccentric anomaly, $E,$ in the point of interest

d$)$ true anomaly, $v,$ in the point of interest

e$)$ angle $$ in the point of interest