Question

A satellite is in an elliptic orbit around the earth with
aphelion of 6R and perihelion of 2 R where R= 6400 km is
the radius of the earth. Find eccentricity of the orbit. Find
the velocity of the satellite at apogee and perigee. What
should be done if this satellite has to be transferred to a
circular orbit of radius OR?
[G = 6.67 x 10-11 SI units and M = 6 x 1024 kg]​

Answer 1

Explanation:

Let ra and rp denote distance of aphelion and perihelion of the elliptical orbit of the satellite.

ra=a(1+e)  and  rp=(1−e)  (a is semi major axis of ellipse)

As ra=bl  and  rp=2R

a(1−e)a(1+e)=2R6R=3  where e=21

So eccentricity =21